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    • 专利摘要:
    APPARATUS AND PROCESS TO TEST AN INDUSTRIAL GAS TURBINE ENGINE AND COMPONENTS OF THE SAME.The present invention relates to a system and process for testing a gas turbine engine or component thereof, especially for a large air gas turbine engine and for a process for testing a large industrial gas turbine engine that require large pressure ratios and flow capacity. The system and process may include the use of a large compressed air storage tank to supply compressed air to the test system. In addition, the system and process may also include the use of a preheating system, which may include a heater and a heat exchange device, to heat the compressed air in the compressed air storage tank to a temperature suitable to simulate normal operation of the gas turbine engine mechanism or component thereof.
    公开号:BR112013025204A2
    申请号:R112013025204-9
    申请日:2012-03-15
    公开日:2020-10-20
    发明作者:Joseph D. Brostmeyer
    申请人:Florida Turbine Technologies, Inc.；
    IPC主号:
    专利说明:

    Invention Patent Descriptive Report for "APPLIANCE AND PROCESS FOR TESTING A INDUSTRIAL GAS TURBINE ENGINE AND COMPONENTS OF THE SAME".
    FIELD OF THE INVENTION 5 The present invention relates, in general, to a system and a process for testing a component of a gas turbine engine, especially for a large industrial or aircraft gas turbine engine and for a process for testing a large industrial gas turbine engine or component that requires large pressure ratios and flow capacity.
    BACKGROUND OF THE INVENTION A large structure heavy duty industrial gas turbine engine (IGT) is typically used to drive an electrical generator and produce electrical energy. These engines can produce more than 200 MW of electricity. For example, a large-structure industrial gas turbine engine can produce almost 300 MW of electricity. An IGT engine will have a compressor with multiple rows or stages of rotor blades and stator vanes, a combustor with multiple tubular combustors arranged in an annular arrangement (also called an annular tubular combustor), and a turbine with multiple rows of rotor blades and stator blades. An aircraft engine typically has an annular combustion instead of multiple tubular combustors arranged in an annular arrangement like in IGT engines. The biggest obstacle in introducing new technologies in large-scale power-generating gas turbine engines is the risk that the new technology may fail during engine operation and result in tens of millions of dollars in equipment damage and possibly the reserve electricity cost during the downtime of the power plant. Because an owner of one of these engines is very reluctant to allow the engine to be used in testing new technology and, as a result, it is very difficult to introduce new technologies into a public power generation plant, most manufacturers of Power generation has test facilities to test the components as much as possible before starting production.
    Unfortunately, the cost of testing and testing facilities prohibits extensive testing and generally only allows infant mortality problems to be discovered before the installation of a new gas turbine engine at the utility site.
    Testing a large IGT engine as a whole or testing a part or component of the engine is both very expensive and very difficult.
    When a large engine is tested, the energy generated must be dissipated, such as using the energy immediately or storing it for future use.
    One method of dissipating the energy produced is to use it to drive an electric generator.
    The energy produced from the electric generator can be supplied back to an electrical grid.
    However, the engine test can only take a few hours.
    Supplying that large amount of electricity to the grid for a few hours and then stopping can cause significant problems for the power company, especially if the gas turbine engine is tripped due to a problem during the test.
    Another problem with testing industrial engines is that the cost of testing is very high.
    In some IGT engine test beds, instead of using an electric generator to supply the resistance load, a water break or electric heater resistors can be used to dissipate the load produced by the engine.
    These means of dissipating the load have advantages over the production of electrical energy described above in which a disturbance to the electrical network is not produced.
    However, the disadvantage is that all the energy produced is lost.
    Testing the combustion or turbine component of a large industrial or overhead engine requires a high flow rate of high pressure air.
    Test times can last for many hours depending on the warm-up time required to achieve stable test conditions and the number of measurement points required for a complete data set.
    A typical facility is located in Cologne, Germany, operated by the German Aerospace Center (DLR). This installation provides flow rates and pressures that are limited by the size of the compressors in the installation.
    Therefore, large engine fuels are often tested in segments and large industrial gas turbine combustors are tested as individual cylinders.
    The complete annular combustion test for industrial gas turbines or large engine, although desirable for the development of the combustion, is not possible due to pressure and flow limitations in installations such as DLR.
    Future component testing requires even higher flow and higher pressures, and building a test facility with compressors large enough to supply the desired pressure and flow levels for complete multi-hour annular testing would require a large capital investment, for example , as much as 400 million dollars.
    In a power plant that uses an IGT engine to start a generator and produce electricity, the electricity required by the local community ranges from high loads (peak loads) to low loads such as during cold days or at night.
    One process to match the electrical supply with the demand of an electric power plant is to make use of the compressed air energy storage system (CAES). In these CAES facilities, during low load times, instead of shutting down an engine, the engine is used to drive a compressor instead of an electric generator to produce high pressure air that is then stored inside as an underground cave. , such as an artificial salt extraction cave. The compressed air is then supplied to the combustor to be burned with fuel and produce a stream of hot gas that is passed through the turbine to drive the electric generator.
    This system replaces the use of a compressor with the use of compressed air stored inside the reservoir.
    The conditions under which testing of these large engines and their components occur must be considered.
    When testing a gas turbine engine such as a large industrial engine or an aircraft engine or a component of one of these engines, the engine or component needs to be tested in a different operating condition in addition to
    steady state condition. Partial engine load conditions need to be tested and such tests require different compressed air and fuel flows. In addition, engine loads vary during the test process from full load in steady state condition to partial loads. Therefore, the amount of energy dissipated varies during the engine test process.
    SUMMARY OF THE INVENTION The present invention provides a process and system for testing a gas turbine engine or a component thereof. The process includes providing a test object, at least a compressed air reservoir that has a total volume of at least 10,000 m3, at least a portion of the volume containing compressed air, placing the test object so that it is in fluid communication with at least one compressed air reservoir, provide a heating device upstream of the test object and downstream of the compressed air reservoir and direct the compressed air from the compressed air reservoir through the heating device and to the inside of the test object. The test object can be a gas turbine engine, a combustor, a compressor, a turbine or a combination thereof. The gas turbine engine can be an industrial gas turbine engine or an overhead engine that includes high Mach number engines such as aspirated propulsion engines. The heating device heats the compressed air in the compressed air tank to a temperature between approximately 300 ° C and approximately 900 ° C before the compressed air enters the test object. To test high Mach number engines, temperatures of more than 2,000 ° C may be required for air entering the test object. The process may additionally include providing a heat exchange device that has a first flow path and a second flow path, the first and second flow paths being in thermal communication with each other, directing the compressed air to from the compressed air reservoir to the first flow path, directing compressed air from the first flow path to the test object and direct compressed air from the test object to the second flow path. The process can additionally include providing a heater upstream of the test object, which can additionally heat up the compressed air in the first flow path before the compressed air enters the test object. The heater and the heat exchange device can together heat the compressed air in the compressed air tank to a temperature between approximately 300 ° C and approximately 900 ° C before the compressed air enters the test object. The heating device can be an electric heater, a plurality of electric heaters arranged in series, a gas powered heater, a plurality of gas powered heaters arranged in series, a heat exchange device, a heating device thermal storage, a high pressure combustion heater or a combination thereof. The process may additionally include providing an air compressor downstream of the test object, operating the test object, the test object providing power to the compressor to produce compressed air, and storing compressed air in at least one reservoir compressed air. The compressed air has a pressure between approximately 1 MPa (10 bar) to approximately 20 MPa (200 bar). In addition, the at least one compressed air tank can include a low pressure compressed air tank, a medium pressure tank and a high pressure tank, used to test test objects under various conditions. The low pressure reservoir can contain compressed air between approximately 1 to 2 MPa (10 to 20 bar), the medium pressure reservoir can contain compressed air between approximately 2 to 5 MPa (20 to 50 bar) and the high pressure reservoir can contain compressed air between approximately 5 to 20 MPa (50 to 200 bar). The facility for testing a gas turbine engine or component includes one or more compressed air tanks that have a total volume of approximately 10,000 m3 to approximately
    1,000,000 m3 one or more air flow paths in fluid communication with one or more compressed air reservoirs and a heating device downstream of one or more compressed air reservoirs are in thermal communication with at least one path air flow. The test facility may additionally include a test chamber that has a first end and a second end, the first end of which is in fluid communication with the compressed air storage tank, a vacuum chamber in fluid communication with the second end of the test chamber and a vacuum pump in fluid communication with the vacuum chamber, in which a directional air flow is generated in the test chamber from the first end to the second end of at least one of the vacuum chamber and the compressed air reservoir. The compressed air reservoir contains at least some compressed air, the heating device heating the compressed air in the compressed air reservoir in at least one air flow path to a temperature between approximately 300 ° C and approximately 900 ° C. The test installation may additionally include a heat exchange device that has a first flow path and a second flow path, the first flow path and the second flow path being in thermal communication between itself and the first flow path is upstream of the heating device and the second flow path is downstream of the heating device.
    BRIEF DESCRIPTION OF THE DRAWINGS A more complete understanding of the present invention and its inherent advantages and resources will be more readily understood by reference to the following detailed description when considered in conjunction with the accompanying drawings in which: Figure 1A shows a first schematic view a gas turbine engine component testing facility using an underground compressed air reservoir; Figure 1B shows a second schematic view of a gas turbine engine component testing facility using an underground compressed air reservoir; Figure 1C shows a schematic view of an embodiment of a heating system; Figure 2 shows a schematic view of a compressed air energy storage facility with a gas turbine engine located nearby to test the engine or to test a component 5 of a gas turbine engine of the present invention; Figure 3 shows a schematic view of a turbine comprising an engine for testing according to the present invention; Figure 4 shows a schematic view of a compressor component of a test engine according to the present invention; Figure 5 shows a schematic view of a combustion component of an engine for testing according to the present invention; Figure 6 shows a schematic view of an air component or air vehicle inside an air tunnel for testing in accordance with the present invention; Figure 7 shows a schematic view of an engine test installation of the present invention with a thermal heat storage device; and Figure 8 shows a schematic view of an engine test facility of the present invention with three compressed air reservoirs to retain different compressed air pressures.
    DETAILED DESCRIPTION OF THE INVENTION Referring now to Figure 1A, a test facility 10 and a process for testing a turbine component module or combustion component module for an air or industrial gas turbine engine is shown. The installation can, in general, include a compressor 11, into which uncompressed air can flow (the air flow is indicated by the figures by arrows) through which the compressed air can be produced (air flow path (b)). The compressor 11 can be driven by an engine or motor 12. Compressed air is stored inside a large compressed air storage reservoir 13, which is an artificial underground cave and used to supply the high flow rate and pressure required to test a motor or component module (which can be referred to in this document as a "test object 17") under normal engine operating conditions (airflow path (a)). The compressed air storage reservoir of the present invention is a single volume storage reservoir of at least 10,000 m3 in size and not formed from several smaller reservoirs.
    The compressor 11 can be small compared to the compressor used in the real gas turbine engine on which the combustion is being tested (for example, one third of the size), which can also reduce the total installation cost.
    In addition, since the compressed air storage tank 13 can be filled over a period of time, the compressor 11 can be operated for several days to fill the storage tank 13 with compressed air. enough for the next test to be performed.
    The engine or engine 12 can be an electric engine (or a diesel or gas powered engine can be used) or a small gas turbine engine, which can drive compressor 11. Compressed air storage tank 13 can be used to store the compressed air from the compressor 11 and is located below the ground due to its large volume requirements.
    For example, storage reservoir 13 can be a pre-existing artificial underground storage facility such as a mined salt cave, or it can be formed from a salt mine using a solution to create a cavity within the salt bed or salt dome that has the capacity to store compressed air for testing the engine or component module.
    A natural underground cavern alone would not have the capacity to store high pressure air useful for testing a gas turbine engine component without additional structural considerations, for example, withstanding high pressures of approximately 20 MPa (200 bar ) and the prevention of high rate leaks.
    Or, if the engine test facility is located in a CAES facility, the storage tank for the CAES facility can be used as the compressed air source for the engine test or engine component.
    For simplicity, the compressed air storage reservoir 13 is portrayed as a plenum surrounded by rock.
    The compressed air storage tank
    Moisture 13 should be able to store enough compressed air at a high pressure (for example, 5 to 20 MPa (50 to 200 bar)) and a high flow rate (for example, in excess of 100 kilograms per second) so that the combustion can be properly tested. For example, hundreds of hours of testing are required in the development process to properly adjust the combustion so that stable operation can be achieved at low emission levels. Typical test durations for a combustor are approximately two to twelve hours. As a non-limiting example, the compressed air storage reservoir 13 may be able to retain a volume of compressed air above 10,000 m3 at a pressure of up to approximately 20 MPa (200 bar). The largest air storage facility for aerodynamic testing at the moment is the 2.44 meter (8 ft) High Temperature Tunnel at NASA's Langley Research Center in Hampton, Virginia, which uses a variety of compressed air storage containers from high pressure connected together for a total field storage volume of 1,104 m3 (39,000 ft3) rated at 41.37 MPa (6,000 psig). This system is connected to a storage field of 41.37 MPa (6,000 psig) that has a volume of 396 m3 (14,000 ft3), giving a total available volume of
    1,500 m3 (53,000 ft3). This facility is used to test high Mach number test vehicles and aspirated propulsion engines. Due to the high airflow requirements required, but limited compressed air storage capacity, test times are limited to less than two minutes. Test facility 10 may additionally include one or more air pressure regulating valves 14 to control air pressure as it exits various components of facility 10 (for example, storage vessel 13 or test object 17), a heating device 15 for heating compressed air flowing from the reservoir 13 to a temperature that would normally be passed into the combustion, the turbine component or another component of a gas turbine engine, a fuel source 16 such as natural gas
    fuel, hydrogen or jet fuel to be burned with heated compressed air, one or more test objects 17 (for example, a combustion 18 and a diffuser or turbine 19), each of which has an inlet and an outlet .
    The heating device 15 (which may include one or more heaters) is used to preheat the relatively cold compressed air in the storage reservoir 13 to a temperature that would simulate the output of a compressor that would normally be used to supply the compressed air. to the engine component to be tested.
    Although not shown in Figure 1A, an exhaust discharge device 20 can be used to discharge the combustion exhaust (air flow path (c)). An air pressure regulating valve 14 can be positioned to control the release of compressed air from the storage reservoir 13 that will flow into the test object 17 and / or another air pressure regulating valve 14 can be positioned to control the release of air leaving the test object 17. Additionally, one or more water injection ports (not shown) can be included in or near the exit of the test object 17 to cool the hot air leaving the test object test 17 of damaging the pressure regulating valve 14 downstream of the test object 17. A heating device 15 can be used to heat the air before it enters the test object 17. Compressed air released from the storage tank 13 can be relatively cold air.
    For example, CAES facilities typically store air at a temperature of 50 ° C or less.
    Since the c ombustor module test requires that the compressed air be at a temperature between approximately 300 ° C to approximately 900 ° C, the heating device 15 can be used to heat the compressed air in the air reservoir. storage temperature to an appropriate temperature for testing.
    The heating device 15 shown in Figure 1A can be a gas or electric powered heater, but any one of several heating devices can be used, such as one or more gas or electric powered heaters, a heat exchanger ( as shown and described in Figure 1B), a heat exchange device (as shown and described in
    Figure 7), or a high pressure combustion heater.
    A high-pressure combustion heater (as shown and described in Figure 1C) can burn a fuel source 16 with compressed air, which may require a smaller heater that would otherwise be required if even atmospheric air was burned.
    Any of these heating devices 15 can be included in installation 10 either alone or in combination with another heating device 15, as long as the compressed air is heated sufficiently to an optimum temperature for testing an engine or component. of engine.
    The test installation 10 can contain one or more temperature and / or pressure sensors (not shown) to measure the operating parameters of any component of the installation 10. These parameters can be adjusted using one or more valves, levers , handle, buttons, user input devices (such as a computer or keyboard), displays, or other devices to regulate such parameters as temperature, pressure, flow rate and test object operation.
    For example, if gas powered or electric heaters are used, the heaters can be arranged in a series to incrementally heat the air, with one or more (perhaps less expensive) heaters heating the cold air coming out of the reservoir. storage of compressed air 13 and one or more (perhaps more expensive, due to the materials required to withstand high temperatures) heaters that bring preheated air to very high temperatures (for example, approximately 700 ° C to approximately 900 ° C) . As another non-limiting example, a gas or electric heater can be used in addition to a heat exchange device, so that the gas or electric powered heater is optionally used to adjust the temperature of the air before it enters the test object 17. Test facility 10 can be used to test various types of modern engine combustion engines, such as those using the annular cylinder combustion, those using the annular and combustion combustion - silo res.
    The combustion test can be performed without burning a fuel in the combustion or can be tested under normal operating conditions
    more by burning the fuel normally inside the combustor by injecting the fuel through the injectors and into the combustor to be burned with the compressed air from the storage tank 13. Overhead engines typically use an annular combustor, whereas 5 industrial engines use an annular arrangement of tubular combustors commonly referred to as an annular cylinder combustor.
    To reduce the airflow requirement when testing annular and annular cylinder combustors, only a small section of the combustor can be used in prior art installations due to the lack of flow capacity in existing test facilities, including the DLR installation in Coogne, Germany, and the NRC Gas Turbine Lab in Ottawa, Canada.
    However, an error is produced when testing only one section of the combustion.
    To produce a complete and accurate test of the combustion, the entire combustion needs to be tested for flow.
    For the silo-type combustion, that combustion cannot be cut out so that a portion of the combustion can be tested for the flow that would represent the entire combustion.
    To test the silo-type or overhead annular combustion, the entire combustion should be tested for flow and therefore a high flow rate is required.
    With the enormous storage capacity of the underground storage tank system of test facility 10 described in this document, the complete optimum test of combustors of any type can be performed using the required high flow rates (such as 100 at 400 kg / s or more) and pressures if the high cost of large compressors used in prior art engine testing facilities.
    Due to the much larger storage volume of the underground salt extraction cave, the engine component can be tested for a long period of time, for example, up to several days.
    For example, some combustion components require longer periods of time to check durability and resistance parameters.
    A multi-purpose aspirated propulsion engine may require a few hundred hours of total test time to qualify engine system durability and performance.
    Prior art test facilities using multiple smaller compressed air containers can only support a test time of a few minutes.
    With the combustion test installation as described and shown in Figure 1A, even an older combustor from an older engine can be tested to improve the performance of the combustion.
    The older engines used in the annular or silo type combustion would be ideal for use with the economically effective test installation 10. Additionally, modifications to the combustion can be implemented and then tested at a lower cost, making such improvements more cost-effective than previously possible.
    Referring now to Figure 1B, installation 10 is shown, with an alternative heating system modality.
    As shown and described in Figure 1A, a heating device 15 or combination of heating devices can be used upstream of test object 17 (such as a combustor as shown in Figure 1C) to heat the compressed air flowing from the storage tank 13 (air flow path (a)) for a temperature (simulate the temperature emission of a real compressor) that would normally be passed into the combustion of a real engine.
    Consequently, the test installation 10 can additionally include a heat or heat exchange device 22. In such a configuration, the compressed air from the storage reservoir 13 and hot air discharged from the test object 17 each passes through a path flow 22a, 22b in the heat exchange device 22 and are in thermal communication with each other.
    These flow paths 22a, 22b can direct air in the same or opposite directions (counterflow paths). The temperature of the air in the first flow path 22a can be affected thermally by the temperature of the air in the second flow path 22b, which can be determined by the operation of the test object 17 (such as oscillation due to the rapid compromise of a combustor). For example, at low combustion burning temperatures, the air temperature in the second flow path 22b may not be sufficient to heat the one in the first flow path 22a to an appropriate temperature.
    Therefore,
    a heating device 15 such as a gas or electric powered heater may be required to adjust the temperature of the air leaving the first flow path 22a of the heat exchange device 22 before the air enters the test object 17. 5 How a non-limiting example, compressed air can be stored in reservoir 13 at a pressure of approximately 7.2 MPa (72 bar) and a temperature of approximately 50 ° C.
    This compressed air can pass from the storage reservoir 13 through the heat exchange device 22 (through the first flow path 22a) at, for example, a flow rate of 100 kg / s.
    Within the heat exchange device 22, the compressed air from the storage reservoir 13 can be heated by the hot air that is discharged from the test object 17 (such as a combustor 18, as shown in Figure 1B). Since the compressed air leaves the heat exchange device 22 as hot air, the hot air can have a pressure of approximately 6.8 MPa (68 bar) and a temperature of approximately 700 ° C.
    The hot air can then pass through a heating device 15 (such as a gas or electric heater) that can adjust the temperature (and decrease the pressure) of the hot air, for example, to approximately 900 ° C in a pressure of approximately 6.6 MPa (66 bar). After passing through the heater 15, the hot air can then pass into the test object 17, to which a fuel can be added (for example, 3 kg / s) to produce a stream of hot gas coming out of the test object 17 at a temperature of, for example, approximately 2,000 ° C at a pressure of approximately 5.6 MPa (56 bar). This hot air leaving the test object 17 can then pass through the heat exchange device 22 (through the second flow path 22b), where it heats the compressed air coming from the storage reservoir 13, which also flows through the heat exchange device 22. That is, the compressed air within a first flow path 22a can be thermally affected by hot air within a second flow path 22b within the heat exchange device 22. Additionally, the hot air coming out of the heat exchange device 22 (air flow path (c)) can be cooled, for example, to approximately 2,000 ° C to a safe temperature for the exhaust flue used (for example, an exhaust discharge device 20 as shown in Figure 1A). The cooling of the hot air 5 can occur because of the thermal effect in the second flow path 22b by the cooler compressed air within the first flow path 22a. It will be understood that these pressures, temperatures and flow rates could vary depending on the test object 17, the storage tank 13 used, the heating device 15 used, etc. Referring now to Figure 1C, a high pressure combustion heater 23 is shown. The high pressure combustion heater 23 may include an internal duct 24 positioned within an external duct 26 through which the compressed air from the compressed air storage reservoir 13 can be passed. Air can be passed through both inner duct 24 and outer duct 26 in parallel, that is, in the same direction or in a counterflow direction. The conduits 24, 26 can each have an inlet end 24a, 26a and an outlet end 24b, 26b. In addition, ducts 24, 26 can be coaxial and tubular (circular in cross-section), but can be of any shape as long as compressed air can flow from the inlet end to the outlet end. Inner duct 24 may include a first combustion zone 28 which has a first fuel injector 30. The first combustion zone 28 may not be a self-ignition combustion zone and may include a flame holder or a recirculation zone 32 in order to maintain combustion inside the inner duct chamber 24. In one embodiment, the temperature of the first combustion zone 28 can be approximately
    1,120 ° C. Inner duct 24 may additionally include a second combustion zone 34 which has a second fuel injector 36 and which is located downstream of the first combustion zone 28 and the first fuel injector 30. The second combustion zone 34 can be an auto-ignition combustion zone because the flow of hot compressed air from the first combustion zone 28 can be hot enough to self-ignite the fuel.
    In one embodiment, the temperature of the second combustion zone 34 can be approximately 1120 ° C.
    The second combustion zone 34 may be colder than the first combustion zone 5 because the cooler air that passes through the external duct is being heated by the hot gas flow from the two combustion zones 28, 34 The hot gas that passes through the internal duct 24 is used to preheat the cooler compressed air in the storage reservoir 13 that passes through the external duct 26 and then into the test component 17 (for example, a combustor ). The hot gas stream does not mix with the preheated compressed air in the storage tank 13, but is instead discharged from the high pressure combustion heater 23 at outlet 24b (air flow path (c)) . This keeps the oxygen content of the compressed air in reservoir 13 high for use in testing test component 17 (for example, a combustor). The flared gas flow from the internal duct is low or without oxygen, and therefore is not discharged into the test component 17. In one embodiment, approximately 30% of the total compressed air in the compressed air storage tank 13 can flow through the internal duct 24 and through the first and second combustion zones 28, 34. The remaining approximately 70% of the compressed air can flow through the external duct 26 and be heated from the flow of hot compressed air in the duct internal 24. For example, the external duct 26 may have a diameter that is approximately 50% larger than the internal duct 24 to achieve this flow of uneven volumes of compressed air through the internal and external ducts 24, 26. Additional or al - ternatively, the inlet end 24a, 26a of the inner and outer ducts 24, 26 could include one or more deflectors or the like to direct the appropriate volume of compressed air to each of the ducts s internal and external 24, 26. The internal conduit 24 can be composed of a highly thermo-conductive material (for example, most high temperature resistant nickel alloys) in order to promote a transfer rate.
    high heat resistance for external duct 24. Referring now to Figure 2, test facility 10 can be established next to a compressed air energy storage facility (CAES) so that during the test the engine can supply the 5 installation of CAES with compressed air or the installation of CAES can supply the engine test installation with compressed air for testing an engine or component thereof.
    In other words, the CAES installation and the test installation 10 can share a compressed air storage reservoir 13, each of which contributes compressed air to or using compressed air from the same storage reservoir. to 13 (air flow paths (a) and (b)). In addition, the compressed air storage reservoir 13 of a typical CAES installation may be of a size suitable for storing and supplying compressed air sufficient to test large motors or components thereof for a length of time in excess of that is currently available.
    For example, a CAES storage reservoir 13 can accommodate more than 10,000 m3 (for example, up to approximately 1,000,000 m3) of compressed air at a pressure of up to 20 MPa (200 bar), a supply that is effective for testing a large engine for several hours for a few days, instead of just a few minutes.
    In addition, a CAES installation can operate at a minimum pressure of 2 MPa (20 bar) and a maximum pressure of 10 MPa (100 bar). However, it is contemplated that non-CAES 13 compressed air storage tanks (or future CAES compressed air storage tanks) can accommodate compressed air that has a pressure of up to 20 MPa (200 bar). Figure 2 shows a non-limiting example of collaboration between a CAES facility and a test facility 10, with a CAES facility communicating with a power plant and located next to a large extracted cave or old salt mine that can be used as a compressed air storage tank 13. Test object 17 can be an engine 42 such as a large industrial gas turbine engine that includes a compressor 44, a combustion 18 and a turbine 19 to produce mechanical work that is used to drive a compressor 11 to fill the compressed air storage tank 13. Alternatively, the test object 17 can be a component of a gas turbine engine such as a combustion engine or a turbine.
    The compressor 11 can supply a load to the engine during the test.
    The CAES installation can, in general, include an electric motor / electric generator 52 to drive a compressor 54 to resupply the compressed air storage reservoir 13 with compressed air.
    Alternatively, the compressed air stored inside storage reservoir 13 can be used to drive a turbine 58 that drives electrical generator 52 to produce electrical energy for the power grid.
    An optional combustor 60 can be used to burn compressed air from the reservoir with a fuel and produce a stream of hot gas which is then passed through turbine 58 to produce electricity from generator 52. For example, on low demand by electrical energy, the CAES facility can be used to drive a compressor 54 to produce compressed air to be stored within the storage reservoir 13. Therefore, the load is not wasted, but is instead converted into compressed air for storage in the reservoir. 13. On peak demand, the stored compressed air can then be supplied to the power plant.
    The test installation 10 shown in Figure 2 may additionally include several air paths.
    The air flow path (a) represents a flow path through which compressed air is directed from storage reservoir 13 (for example, to be used by the power plant associated with the installation of CAES or to be recycled back into test object 17 for further testing). The air flow path (b) represents a flow path through which compressed air is delivered to storage reservoir 13 (for example, compressed air generated by the CAES facility or test object 17). The air flow path (c) represents air being vented away from test facility 10 or otherwise dissipated.
    Additionally, an air flow valve 64 can be used to prevent compressed air from discharging from the storage tank.
    zoning 13 back into the compressor 11. A CAES facility as currently operated in McIntosh, Alabama or Huntorf, Germany is sufficient for a large engine 10 test facility. In addition, a 5 hydrogen production source is available from McIntosh, Alabama, a CAES facility, which could be used for testing hydrogen combustion.
    The association between test facility 10 and a CAES facility can not only reduce the costs associated with building and maintaining test facility 10, but can also contribute valuable energy to the CAES facility and its associated power plant.
    Therefore, the effectiveness of both installations can be improved.
    Additionally, since test facility 10 is not connected to the mains, there will be no effect on the mains if the gas turbine being tested trips.
    However, although it is beneficial to establish a test facility 10 in association with a CAES facility, it is not necessary.
    Alternatively, a compressed air storage reservoir 13 of sufficient size can be constructed from an underground cave (and made capable of containing high pressures with limited leakage). The compressed air storage tank 13 would ideally be of such a size (for example, between approximately 10,000 m3 and approximately 1,000,000 m3) that it would allow a large industrial or air gas turbine engine to be tested over a long period of time. time, such as a few days.
    The storage reservoir 13 may, in turn, also have the capacity to store a significant amount of the compressed air generated from the test.
    The stored compressed air can then be recycled at installation 10 for testing the engine or additional component.
    Additionally or alternatively, compressed air could be used for other industrial applications in addition to power generation.
    If the compressed air storage reservoir 13 is part of a CAES facility or is built, the large volume of the reservoir or, in fact, several smaller reservoirs in fluid communication with each other (which has a total volume from, for example, approximately 10,000 m3 to approximately 1,000,000 m3), allows the use of a much smaller compressor 11 to produce compressed air than in prior art engine testing facilities. For example, compressor 11 can be one-third the size normally required to supply that somewhat large volume of compressed air, and the smaller compressor 11 can be operated for a longer period of time (for example 72 hours) to supply the required volume and pressure of compressed air in the storage tank
    13. Therefore, the cost of installation 10 can be reduced significantly because more expensive and larger compression is not required to produce a sufficient volume of compressed air for the test. Referring now to Figures 3 to 5, a single engine component can be used as a test object 17. Figure 3 shows a simplified schematic representation of a method for testing a turbine 19; Figure 4 shows a simplified schematic representation of a method for testing a compressor 11; and Figure 5 shows a simplified schematic representation of a method for testing a combustor
    18. For any of these methods, large volume and high pressure compressed air (for example, approximately 10,000 m3 to approximately 1,000,000 m3 and up to approximately 20 MPa (200 bar)) can be supplied from the reservoir compressed air storage 13 from a CAES facility or an artificial storage tank of sufficient size and structural characteristics. Therefore, a large capital investment in equipment and construction is not required (for example, the required infrastructure may already exist in a CAES power plant). It has been estimated that a new compressor installation has the capacity to supply these pressures and volumes of compressed air to test an engine combustion would cost approximately 400 million dollars. Referring now to Figure 3, compressed air from storage reservoir 13 can be used to drive a turbine module 19 for testing. The airflow path (a) represents an airflow path through which the stored compressed air can be supplied to the inside of test facility 10 in a storage tank 13. An optional combustor (not shown) it can also be used to produce a stream of hot gas that is passed through the turbine to recreate a normal operating condition.
    A compressor 11 can be driven by turbine 19 during testing and used to provide a load on turbine 5 during testing.
    This, in turn, can produce compressed air that can be replenished to the storage reservoir 13. The air flow paths (b) and (c) represent air flow paths through which compressed air generated by the test can be supplied to storage reservoir 13 or for other use.
    In addition, one or more heating devices 15, as described and shown in Figures 1A and 1B, can be used to heat the compressed air that comes from the storage reservoir 13 before the compressed air enters the turbine 19. For example For example, compressed air can be stored in a CAES 13 installation storage tank at a temperature of 50 ° C and below.
    The one or more heating devices 15 can be used to heat the air to an optimum temperature for use in the test, for example, between approximately 300 ° C and approximately 900 ° C.
    Before the compressed air from the storage tank 13 enters the test object 17, the temperature and pressure characteristics of the compressed air should simulate the characteristics of compressed air that would be passed into a compressor combustion in an engine gas turbine in real conditions.
    Referring now to Figure 4, a compressor 11 can be tested under normal operating conditions for a long period of time (for example, several hours for a few days). The compressor 11 can be driven by a motor or motor 12, such as a gas or electric motor and generate compressed air which is then stored inside the compressed air storage reservoir 13 or placed for other use (flow paths of air (b) and (c)). Referring now to Figure 5, a combustor 18 can be tested with the use of compressed air from storage reservoir 13 (airflow jacket (a)). One or more heating devices 15 can be used to preheat the compressed air before it enters the combustion 18 and fuel can be mixed and burned with the compressed air inside the combustion 18 for the testing process.
    Multiple types of heaters can be used together, including externally ignited electric heaters or heaters.
    Optionally, a gaseous fuel source 16 can be used (for example, gaseous fuels such as CH4 or H2). The fuel can be compressed together with air from the compressed air storage tank 13 and then used, for example, to test the combustion 18 by passing compressed and combustible air into the combustion 18 and ignited.
    The resulting hot gas stream can then, for example, be passed through a turbine 19 to test, as shown in Figure 3. A great benefit of the present invention over the prior art test facility using multiple storage vessels of smaller compressed air like NASA's Langley facility is that longer test periods and high Mach numbers can be accomplished.
    NASA's Langley Facility can only perform high Mach number tests for less than two minutes due to limited compressed air storage capacity.
    With the large underground storage tank of the present invention, a large volume of compressed air at the required pressure can be supplied for long periods of time for testing the high Mach number suitable, for example, in a fuselage design.
    Referring now to Figure 6, specialty tests, such as aerodynamic test in a wind tunnel or high Mach number test (such as hypersonic Mach test and test up to Mach 10), can be performed using the test 10 with a low capital equipment cost.
    In one example, as shown in Figure 6, a vacuum chamber 66 associated with a vacuum pump 68 can be used in addition to the compressed air storage reservoir 13. Vacuum chamber 66 can be constructed similarly to the storage reservoir. - compressed air 13 and can be of a similar size.
    That is, the vacuum chamber 66 can be artificial (such as by solution mining). The vacuum pump 68 can gradually (for example, over the space of a week) create a very low pressure inside the vacuum chamber 66, so that that chamber 66 can be entirely or almost entirely free of air over time that a vacuum is required to test. 5 Similar to the compressor, the vacuum pump 68 can be relatively small, as well as having the capacity to supply approximately 1% to approximately 15% of the vacuum pressure actually needed to test. This is because the large vacuum chamber 66 can function as a vacuum. The air flow path (d) represents a flow path through which air exits wind tunnel 70 and flows into the vacuum chamber
    66. The large volume of air in the vacuum chamber 66 can be used to vary a pressure for testing high Mach number of aircraft or engines in a wind tunnel with a low capital equipment cost. The vacuum chamber 66 used for the high Mach number test can be of a size to provide sufficient airflow at a speed sufficient to produce an airflow of up to Mach 10. However, the test installation 10 it may also have the ability to test a high Mach number without including a vacuum chamber 66 or vacuum pump 68. In order to conduct aerodynamic testing of an engine, component of the same or an entire aircraft or other vehicle, a tunnel of wind 70 which has an inlet 70a and an outlet 70b can be used. For example, compressed air can be supplied (air flow path (a)) to the inlet end 70a of a wind tunnel 70 (or similar type of chamber sized to contain a large object being tested) from storage reservoir 13 and discharged from outlet end 70b of the wind tunnel (airflow path (c)). Alternatively or additionally, air can be pushed from the wind tunnel 70 into the vacuum chamber 66 (air flow path (d)) at an outlet end 70b. Alternatively or in addition, a bypass line 71 can be used in conjunction with a flow ejector 72 and one or more regulating valves
    14. The bypass line 71 can take the place of a vacuum chamber 66 and vacuum pump 68 so that the vacuum chamber 66 and the vacuum pump
    68 are not required for testing. The wind tunnel 70 may include an inlet valve and an outlet valve (not shown) to control the amount of compressed air entering the inlet end 70a and / or the amount of air removed by the vacuum chamber 66 in the outlet end 70b. The bypass line 71 is in fluid communication with the exhaust line (airflow path (c)) from the outlet end 70b of the wind tunnel 70, and does not supply air to the wind tunnel 70 (such as through the end inlet 70a). As compressed air flows from bypass line 71 into the airflow path (c), any compressed air within wind tunnel 70 (as supplied from storage reservoir 13 via the air flow (a)) will be extracted from the wind tunnel 70 and into the air flow path (c), for the same effect as with the use of vacuum chamber 66 and vacuum pump 68. Therefore large size of storage reservoir 13 of at least
    10,000 m3, a large amount of compressed air can be used to supply the high Mach number air to the wind tunnel to test the air component at these high Mach numbers for long periods of time that cannot be accomplished using the prior art test facility with numerous compressed air bottles. A heater to heat the compressed air to the appropriate temperature for testing high Mach numbers can also be used and located between the compressed air storage reservoir 13 and the entrance to the wind tunnel 70. Referring now to Figure 7, a alternative mode of test installation 10 is shown. The heating device 15 can be a thermal storage device 73 used to store heat from the hot compressed air produced in the compressor 11 as it passes into the compressed air storage tank 13 (air flow path (b)) or how it is ventilated or otherwise dissipated (air flow path (c)). Additionally or alternatively, the thermal storage device 73 can be used to store heat from the hot compressed air as it is ventilated from the installation 10. The thermal storage device 73 can be composed of a material that has a high heat capacity and high thermal conductivity.
    The material can be a solid or semi-solid or phase-changing material, such as alumina, ZnCl2 + KCl, NaNO3, KNO3, MgCl + NaCl, or NaCl.
    The heat from the hot compressed air can be stored in the thermal storage device 73 and used later to heat the compressed air for testing as it passes through the thermal storage device 73 from the compressed air storage tank. - wet 13 (airflow path (a)) for test component 17. Thermal storage device 73 can be used in addition to another heating device 15 such as a gas or electric heater or a heat exchange device 22 (not shown in Figure 7). In addition, the thermal storage device 73 can function as a gas or electric powered heater or heat exchange device, or it can be used to adjust the temperature of the air entering the test object as necessary 17 Test object 17 can be, for example, an engine 42 which has a compressor 44, combustion 18 and turbine 19, which can supply power to compressor 11. Or, test object 17 can be a component of engine 42. Referring to Referring now to Figure 8, an additional alternative mode of test installation 10 is shown, including multiple compressed air reservoirs, each holding compressed air that has a different pressure.
    A gas turbine engine (test engine 42), which can include a compressor 44, a combustor 18 and a turbine 19, can drive, for example, a low pressure compressor 74, a medium pressure compressor 76 and a high pressure compressor 78. Each of the compressors 74 to 78 can be in fluid communication with a separate compressed air storage tank 80, 28, 84. For example, a first flow path 86a can connect a first compressed air storage reservoir 80 to the low pressure compressor 74, a second flow path 86b can connect a second compressed air storage reservoir 82 to the medium pressure compressor 76 and a third flow path 86c can connect a third
    compressed air storage tank 84 to high pressure compressor 78 (represented by air flow paths (b)). However, any number of additional compressors can be included, each one to generate compressed air at a different pressure and being connected to a different compressed air storage tank and any variety of connections and flow paths can be included. be used.
    In addition, each of the compressed air storage tanks 80, 82, 84 could also be in fluid communication with a test object 17 (not shown in Figure 8). In addition, the first flow path 88a, second flow path 88b and third flow path 88c can connect compressed air storage tanks 80, 82, 84 to a discharge point 90 (air flow paths (c )). Different volumes of compressed air that have different pressures can be used to test different components or phases of operation of a component or an engine.
    For example, the low pressure reservoir 80 could be used to store compressed air at 1 to 2 MPa (10 to 20 bar), the medium pressure reservoir 82 could be used to store compressed air at 2 to 5 MPa (20 to 50 bar). bar) and the high pressure reservoir 84 could be used to store compressed air at 5 to 20 MPa (50 to 200 bar) (or greater). The use of different pressure reservoirs can improve the efficiency of the test facility 10 because compressed air of an appropriate pressure may be available to invest energy to pressurize the depressurized air from a single storage reservoir.
    For example, in other test facilities when low pressure compressed air is required for a test and the only compressed air available is high pressure compressed air, then the pressure of high pressure compressed air must be lowered in order to to accommodate optimal test conditions.
    In the process, however, the high pressure compressed air loses energy as the pressure is lowered.
    In addition, multiple pressure reservoirs can be used to produce different loads during the engine test process.
    When a low load is required, test motor 42 can be used to drive low pressure compressor 74. When a high load is required, test motor 42 can be used to drive high pressure compressor 78. Or, a combination of compressors can be started at the same time to deliver even greater loads to the engine.
    Other modalities are also contemplated.
    For example, 5 a brine solution can be stored in reservoir 13 instead of compressed air and used to drive an electric generator and produce electrical energy.
    Brine is preferred over pure water because water, unlike a saturated brine solution, would dissolve the salt walls of certain types of artificial or naturally occurring caves.
    In addition, when completely saturated with salt, the brine solution has a specific gravity of 1.2 compared to water, so it provides 20% more energy to equipment of the same size.
    In addition, two caves can be used at different elevations so that a large pressure difference could be used for energy production.
    For example, a first cave may be located 152.4 meters (500 feet) below the ground, while a second cave may be located 457.2 meters (1,500 feet) below the ground.
    This can produce a pressure head equal to 304.8 meters (1,000 feet). The saturated brine solution could be pumped from the lower cave during low energy demand and into the upper elevation cave for storage until peak demand.
    At peak demand, the brine solution is allowed to flow down and into the lower cavity through a turbine (such as a Francis turbine) that will be used to drive an electric generator and produce electricity.
    Because of the higher specific gravity (compared to water) more energy can be extracted from the brine solution.
    In another embodiment, instead of a salt cave with a salt brine solution, an oil storage cave can be used for the pressure head to drive the turbine and electric generator.
    For example, salt caves are currently used for the United States Strategic Petroleum Reserve.
    The pumped storage facility could be used for storing fluid high energy for daily use and for storing chemical energy over the long term for emergencies.
    Fuel or oil stored in a storage tank can be used to drive the turbine and electric generator.
    Additionally, fuel or oil in a reservoir 5 can be pumped to a higher elevation during low demand and then discharged into a lower reservoir through a turbine to drive the electric generator during peak demand.
    In yet another embodiment, the energy of a large gas turbine engine during testing can be dissipated and stored by pumping a liquid (such as a brine solution) between two caves in different elevations.
    A turbine can be used to drive a pump that would pump a brine solution from a lower level cave to an upper level cave to dissipate the energy being produced by the test engine.
    Then, the brine solution can be passed through another turbine from the upper to the lower elevation to drive the turbine and an electric generator connected to the turbine to produce electrical energy.
    For example, the turbine can be connected to a Francis turbine through a speed reduction gear to pump the fluid up to the upper elevation cave or storage reservoir.
    The same or a second Francis turbine can also be used to drive the electric generator when the liquid flows into the lower elevation cave.
    It will be appreciated by persons skilled in the art that the present invention is not limited to what has been shown particularly and described in the present document above.
    In addition, unless otherwise noted, it should be noted that all attached drawings are not to scale.
    A variety of modifications and variations are possible in light of the above teachings without departing from the scope and spirit of the invention, which is limited only by the following claims.
    权利要求:
    Claims (21)
    [1]
    1. A process for testing a component of a gas turbine engine that comprises: providing a test object; 5 supply at least one compressed air reservoir that has a total volume of at least 10,000 m3; place the test object in fluid communication with at least a compressed air reservoir; provide a heating device upstream of the test object and downstream of the compressed air tank; and direct the compressed air from the compressed air tank through the heating device and into the test object.
    [2]
    2. Process according to claim 1, wherein the test object is at least one of a gas turbine engine, a combustion engine, a compressor and a turbine.
    [3]
    Process according to claim 1, wherein the heating device heats the compressed air from the compressed air reservoir to a temperature between approximately 300 ° C and approximately 900 ° C before the compressed air enters not the test object.
    [4]
    4. Process according to claim 1, which further comprises: providing a heat exchange device that has a first flow path and a second flow path, the first flow path and the second flow path being in thermal communication with each other; direct compressed air from the compressed air reservoir into the first flow path; direct compressed air from the first flow path to the test object; and direct compressed air from the test object to the second flow path.
    [5]
    A process according to claim 4, which further comprises: providing a heater upstream of the test object; direct compressed air from the first flow path to the heater; 5 direct compressed air from the heater to the test object; and direct compressed air from the test object to the second flow path.
    [6]
    6. Process according to claim 5, in which the heater and the heat exchange device heat the compressed air in the compressed air tank to a temperature between approximately 300 ° C and approximately 900 ° C before compressed air enters the test object.
    [7]
    7. Process according to claim 1, wherein the heating device is at least one of an electric heater, a plurality of electric heaters arranged in series, a gas powered heater, a plurality of gas powered heaters arranged in series, a heat exchange device, a thermal storage device and a high pressure combustion heater.
    [8]
    A process according to claim 1, which further comprises: providing an air compressor downstream of the test object; operate the test object, the test object supplying power to the compressor to produce compressed air; and storing the compressed air in at least one compressed air reservoir.
    [9]
    Process according to claim 8, in which the compressed air has a pressure between approximately 1 MPa (10 bar) to approximately 20 MPa (200 bar).
    [10]
    Process according to claim 1, wherein the at least one compressed air reservoir includes a low pressure compressed air reservoir, a medium pressure compressed air reservoir
    Diana and a high pressure compressed air reservoir.
    [11]
    11. Process according to claim 10, which further comprises: operating a low pressure compressor with the test object 5 to produce a low pressure compressed air, the compressed air having a pressure between approximately 1 MPa (10 bar) to approximately 2 MPa (20 bar); activate a medium pressure compressor with the test object to produce a medium pressure compressed air, the compressed air having a pressure between approximately 2 MPa (20 bar) to approximately 5 MPa (50 bar); and start a high-pressure compressor with the test object to produce high-pressure compressed air, the compressed air having a pressure between approximately 5 MPa (50 bar) and approximately 20 MPa (200 bar); and store the low pressure compressed air in the low pressure compressed air reservoir, store the medium pressure compressed air in the medium pressure compressed air reservoir and store the high pressure compressed air in the high pressure compressed air reservoir .
    [12]
    A process according to claim 11, which further comprises: using low pressure compressed air to test a test object under low pressure conditions; use medium pressure compressed air to test a test object under medium pressure conditions; and use high pressure compressed air to test a test object under high pressure conditions.
    [13]
    13. Test installation for a large-frame gas turbine engine or components thereof, the test installation comprising: one or more compressed air tanks that have a total volume of approximately 10,000 m3 to approximately 1,000. 000 m3; one or more air flow paths in fluid communication with one or more compressed air reservoirs; and a heating device downstream of the one or more reservoirs of compressed air being in thermal communication with at least one airflow path.
    [14]
    Test installation according to claim 13, further comprising: a test chamber having a first end and a second end, the first end of which is in fluid communication with the compressed air storage tank ; a vacuum chamber in fluid communication with the second end of the test chamber; and a vacuum pump in fluid communication with the vacuum chamber, in which a directional air flow is generated in the test chamber from the first end to the second end of at least one of the vacuum chamber and the air reservoir. compressed.
    [15]
    15. Test installation according to claim 13, in which the compressed air reservoir contains at least some compressed air, the heating device heating the compressed air in the compressed air reservoir in at least one airflow path to a temperature between approximately 300 ° C and approximately 900 ° C.
    [16]
    A test installation according to claim 13, which further comprises: a heat exchange device having a first flow path and a second flow path, the first flow path and the second flow path they are in thermal communication with each other and the first flow path is upstream of the heating device and the second flow path is downstream of the heating device.
    [17]
    17. Test installation according to claim 16, in which the compressed air tank contains at least some compressed air, the heating device and the heat exchange device heating the compressed air in the air tank compressed in at least one airflow path to a temperature between approximately 300 5 ° C and approximately 900 ° C.
    [18]
    A test facility according to claim 13, wherein the heating device is at least one of an electric heater, a plurality of electric heaters arranged in series, a gas powered heater, a plurality of gas powered heaters arranged in series, a heat exchange device, a thermal storage device and a high pressure combustion heater.
    [19]
    19. Test facility according to claim 13, wherein the one or more compressed air reservoirs is an underground plenum.
    [20]
    A test installation according to claim 13, further comprising: a low pressure compressor that produces low pressure compressed air having a pressure between approximately 1 MPa (10 bar) and 2 MPa (20 bar); a medium pressure compressor that produces medium pressure compressed air that has a pressure between approximately 2 MPa (20 bar) and approximately 5 MPa (50 bar); and a high pressure compressor that produces high pressure compressed air that has a pressure between approximately 5 MPa (50 bar) and approximately 20 MPa (200 bar), the one or more compressed air reservoirs that includes: a compressed air reservoir low pressure in fluid communication with the low pressure compressor; a medium pressure compressed air reservoir in fluid communication with the medium pressure compressor; and a high pressure compressed air reservoir in fluid communication with the high pressure compressor.
    [21]
    21. Test installation for a gas turbine engine or engine
    components of the same which comprise: a test object, the test object having an optimum operating temperature; at least one compressed air reservoir that has a total volume of at least 10,000 m3, at least a portion of the volume that contains compressed air; a heating device upstream of the test object and downstream of at least one compressed air reservoir; and a heat exchange device that has a first flow path and a second flow path, the first flow path and the second flow path being in thermal communication with each other, the first flow path being upstream of the heating device and the second flow path is downstream of the heating device. the heat exchange device that heats the compressed air in the compressed air tank to a temperature between approximately 300 ° C and approximately 900 ° C, and the heating device that additionally heats the compressed air in the first flow path when the heat exchanger heats the compressed air to a temperature lower than the optimum operating temperature of the test object.
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    同族专利:
    公开号 | 公开日
    AU2012237974A1|2013-10-24|
    PT2691757T|2017-06-06|
    MX2013011269A|2014-03-27|
    US9200983B2|2015-12-01|
    WO2012134824A1|2012-10-04|
    RU2013148004A|2015-05-10|
    AU2012237974B2|2015-08-13|
    CN103597333A|2014-02-19|
    US20140053641A1|2014-02-27|
    CA2831668C|2016-06-21|
    EP2691757B1|2017-05-03|
    PL2691757T3|2017-09-29|
    EP2691757A1|2014-02-05|
    CN103597333B|2017-03-29|
    CA2831668A1|2012-10-04|
    DK2691757T3|2017-05-22|
    MX339093B|2016-05-10|
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    WO2018164713A1|2017-03-08|2018-09-13|Florida Turbine Technologies, Inc.|Apparatus and process for testing a large combustor using a caes facility|
    CN107764553A|2017-10-23|2018-03-06|北京理工大学|A kind of adjustable air inlet heating device pilot system|
    RU2725114C1|2019-10-24|2020-06-29|Акционерное общество "Корпорация "Тактическое ракетное вооружение"|Method of testing performance of gas reducers of aircrafts and pneumatic test bench for its implementation|
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    法律状态:
    2020-11-03| B06F| Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]|
    2020-12-15| B06U| Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]|
    2021-03-30| B11B| Dismissal acc. art. 36, par 1 of ipl - no reply within 90 days to fullfil the necessary requirements|
    2021-11-23| B350| Update of information on the portal [chapter 15.35 patent gazette]|
    优先权:
    申请号 | 申请日 | 专利标题
    US201161468771P| true| 2011-03-29|2011-03-29|
    US61/468,771|2011-03-29|
    US201113108029A| true| 2011-05-16|2011-05-16|
    US13/108,029|2011-05-16|
    US201161561956P| true| 2011-11-21|2011-11-21|
    US61/561,956|2011-11-21|
    US201161569378P| true| 2011-12-12|2011-12-12|
    US61/569,378|2011-12-12|
    US201261587022P| true| 2012-01-16|2012-01-16|
    US61/587,022|2012-01-16|
    US201213410051A| true| 2012-03-01|2012-03-01|
    US13/410,051|2012-03-01|
    PCT/US2012/029231|WO2012134824A1|2011-03-29|2012-03-15|Apparatus and process for testing an industrial gas turbine engine and components thereof|
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