• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    Description of an integrated hybrid emergency power system with various functions. A hybrid emergency power system may have an auxiliary power supply unit and an emergency power supply unit. The emergency power unit may have a fuel cell. The emergency power unit may have an engine. The emergency power supply unit can be connected to the auxiliary power supply unit by an apparatus for improving the efficiency of the emergency power supply unit. In this way, the operating efficiency of the emergency power unit can be improved.
    公开号:FR3021630A1
    申请号:FR1553497
    申请日:2015-04-20
    公开日:2015-12-04
    发明作者:Lubomir A Ribarov；Jr Leo J Veilleux
    申请人:Hamilton Sundstrand Corp；
    IPC主号:
    专利说明:

    [0001] The present invention relates to the field of electric power generation. More particularly, the present invention relates to an airborne emergency power system capable of operating in the event of an aircraft engine failure. BACKGROUND Aircraft have used various emergency power units ("EPUs") to provide power in the event of engine failure. However, existing emergency power units have encountered operational challenges. For example, dynamic air turbines may be damaged during deployment in the wake of the aircraft. In addition, systems driven by the compressor bleed air can not operate if the main engine fails unless a low pressure coil generator operates during the autorotation spinning of (s) (the ) propeller (s) of the main engine, although this coil generator adds unwanted weight and complexity. In addition, solid propellant-based feed systems are unstable and prone to contamination and wear, and existing fuel-cell based emergency power units require high pressure pressure. air inlet close to atmospheric pressure and relatively high inlet temperatures. Thus, there is a need for advanced integrated hybrid UPEs to overcome these challenges while providing reliable on-board emergency power. SUMMARY OF THE INVENTION In accordance with the various aspects of the present invention, an integrated energy conversion system is described. 3021630 2 An energy conversion system may have an integrated emergency power supply unit, an auxiliary power supply unit (APU), and a power unit efficiency improvement device. emergency. The emergency power unit may have a fuel cell. The auxiliary power unit may have a motor and a generator in which the motor drives the generator to produce a power supply. The unit for improving the efficiency of the emergency power supply unit may have a heat exchanger and a bypass valve. The heat exchanger may be in fluid communication with the emergency power unit and the auxiliary power unit.
    [0002] According to one embodiment, the apparatus for improving the efficiency of the emergency supply unit comprises a first tube through which water can be conveyed from the fuel cell to the engine, in wherein the heat exchanger is configured to selectively heat the compressed air and deliver compressed air from the engine to the fuel cell; and wherein the bypass valve can selectively route compressed air from the engine to the fuel cell. According to one embodiment, the engine comprises a gas turbine. In one embodiment, the fuel cell comprises a hydrogen fuel cell. According to one embodiment, the fuel cell comprises: a fuel inlet including an opening configured to interconnect with a pipe through which fuel is conveyed from a fuel supply to the fuel cell; an oxygen inlet including an opening in fluid communication with the apparatus for improving the efficiency of the emergency supply unit; an exhaust gas outlet in fluid communication with an exhaust gas well; a waste water outlet in fluid communication with the first tube of the unit for improving the efficiency of the emergency supply unit through which water is conveyed from the unit emergency supply to the auxiliary power unit; and a power supply output connected to an electric bus of an aircraft.
    [0003] According to one embodiment, the auxiliary supply unit comprises: a gas turbine; and an electric generator, wherein the gas turbine drives the electric generator, and wherein the generator is connected to a power supply output connected to the electric bus of an aircraft. According to one embodiment, the apparatus for improving the efficiency of the emergency supply unit 10 comprises: a fluid interconnection between a waste water outlet of the emergency supply unit and the auxiliary supply unit through which water can be injected into the engine of the auxiliary power unit; and the heat exchanger comprising a first fluid path and a second fluid path, wherein the first fluid path can accept pressurized air from a purge air outlet of the turbine. gas, wherein the second fluid path can accept residues from a tailings outlet of the gas turbine, and wherein the pressurized air is reheated in response to the tailings and conveyed to the fuel cell of the emergency power supply unit. According to one embodiment, the exhaust gas well comprises a fire extinguishing system. According to one embodiment, the exhaust gas well comprises a fuel tank inerting system. According to one embodiment, wherein the integrated energy conversion system is installed in an aircraft.
    [0004] In some embodiments, an energy conversion system may have an emergency power unit having a fuel cell, and an apparatus for improving the efficiency of the power supply unit. emergency having a heat exchanger and a bypass valve. The heat exchanger may be in fluid communication with the emergency power unit. The heat exchanger can heat the compressed air that is sent to the inlet / air inlet of the emergency power unit. According to one embodiment, the apparatus for improving the efficiency of the emergency supply unit comprises: a first tube adapted to allow water to be conveyed from the fuel cell to an auxiliary power unit; and wherein the bypass valve selectively conveys compressed air to the emergency supply unit without warming. According to one embodiment, the emergency power supply unit comprises: a fuel cell comprising an opening interconnected with a pipe through which fuel is conveyed to the fuel cell; an oxygen inlet including an opening in fluid communication with the apparatus for improving the efficiency of the emergency supply unit; an exhaust gas outlet through which the exhaust gas is released from the fuel cell; and a waste water outlet in fluid communication with the first tube of the efficiency improving apparatus of the emergency supply unit through which water is released from the fuel cell. . According to one embodiment, the apparatus for improving the efficiency of the emergency power supply unit comprises: a fluid interconnection between a waste water outlet of the emergency supply unit and the auxiliary supply unit through which water can be injected into a motor of the auxiliary power unit; and wherein the heat exchanger comprises a first fluid path and a second fluid path, whereby the first fluid path can accept pressurized air from a bypass air outlet. the auxiliary supply unit motor, whereby the second fluid path can accept residues from an engine residue output of the auxiliary power unit.
    [0005] According to one embodiment, the fuel cell is a hydrogen fuel cell. BRIEF DESCRIPTION OF THE DRAWINGS A more complete understanding of the present invention may be derived by reference to the detailed description when contemplated in the context of the Figures, where like reference numerals refer to like elements throughout the Figures, and: FIG. 1 depicts a schematic of an exemplary embodiment of an integrated hybrid emergency power system; FIG. 2 discloses a fuel cell component of an integrated hybrid emergency power system; and FIG. 3 describes a component of an auxiliary power unit of an integrated hybrid emergency power system. DETAILED DESCRIPTION The following description is comprised of various exemplary embodiments only, and is not intended to limit the scope, applicability or configuration of the present invention in any way. Preferably, the following description is intended to provide an appropriate illustration for the implementation of various embodiments including the best mode. As noted later, various modifications may be made in the function and arrangement of the elements described in these embodiments without departing from the scope of the present invention. For the sake of brevity, conventional manufacturing and construction techniques may not be described in detail in the present invention. In addition, the connection lines indicated in the various figures contained in the present invention are intended to represent functional relationships and / or exemplary physical couplings between the different elements. It should be noted that many functional relationships or alternative or additional physical connections may be present in a practical construction method.
    [0006] In other embodiments, an integrated energy conversion system is described. Referring to Figure 1, an energy conversion system 2 may comprise an emergency power supply unit 4, and an auxiliary power supply unit 6. A power conversion system 2 may further comprise an apparatus to improve the efficiency of the emergency power supply unit 5. The apparatus for improving the efficiency of the emergency power supply unit 5 can be connected in fluid communication to the to the emergency power supply unit 4 and the auxiliary power supply unit 6 and can provide selective fluidic connectivity between the emergency power supply unit 4 and the auxiliary power supply unit 6 by which the efficiency of the emergency power supply unit 4 and / or the auxiliary power supply unit 6 can be improved. As used in the present invention, being connected in "fluid communication" or "fluid communication" means that a passage exists between the connected elements via which a fluid, including a liquid and / or a gas and / or or any other non-solid material, can move from one connected element to another connected element. With reference to Figures 1 and 2, an emergency power supply unit 4 may comprise a fuel cell 7. In addition, the emergency power supply unit 4 may have a plurality of fluidic, electrical, and electrical interconnections. or mechanical with other system elements. For example, the emergency power supply unit 4 may include a fuel inlet 14, an oxygen inlet (e.g., 02) 16, an exhaust gas outlet 12, a water outlet / outlet Waste water vapor 13, and an electrical power supply outlet 10. As used in the present invention, references to water also include water in non-liquid states, such as water vapor. One or more of the various inputs and outputs may be connected in fluid and / or electrical communication to the fuel cell 7 directly or via the efficiency improving apparatus of the emergency power supply unit 5.
    [0007] The fuel inlet 14 may comprise an orifice in fluid communication with a fuel supply 8. In other embodiments, the fuel inlet 14 comprises a tube, or a pipe, or an opening interconnected with a tube or a pipe through which the fuel can be fed from a fuel supply 8 to the fuel cell 7. The fuel supply 8 may comprise hydrogen (eg, H2). The oxygen inlet 16 may comprise a tube, or a pipe, or an opening interconnected with a tube or pipe in fluid communication with a source of oxygen-containing gas. Thus, the oxygen inlet 16 can convey oxygen to the fuel cell 7. In other embodiments, the oxygen can be introduced via the passage of the ambient air (which contains oxygen) from the ambient environment. In other embodiments, the air stream containing oxygen can be sucked through the introduction of conditioned air from the aircraft cabin. However, in many aircraft applications, for example, during normal high-altitude flight conditions, the air drawn from the ambient environment may have insufficient pressure, and / or insufficient temperature to provide a high level of pressure. Thus, in other embodiments, the oxygen inlet 16 is in fluid communication with the unit for improving the efficiency of the supply unit. In this way, the temperature and / or the pressure of the air can be conditioned before being introduced to the oxygen inlet 16.
    [0008] The power supply output 10 may comprise a conductive terminal in electrical communication with the fuel cell 7. The power supply output 10 may comprise a single conductor, or may comprise two conductors or may comprise any number of conductors. The power supply output 10 may supply power from the fuel cell 7 to an electric bus of an aircraft 36. The exhaust gas outlet 12 may comprise a tube, or a pipe, or an opening interconnected with a tube or pipe in fluid communication with an exhaust gas well 38. In this manner, the exhaust gas outlet 12 can convey the exhaust gas from the fuel cell 7 to the well. In other embodiments, the exhaust gas comprises nitrogen, for example, N 2. In addition, the exhaust well 38 may include a fire suppression system. Thus, the exhaust gas from the fuel cell 7 can be transformed, for example to charge a fire extinguishing system with nitrogen gas. In other embodiments, the exhaust gas well 38 includes an onboard fuel tank inerting system. For example, the exhaust gas from the fuel cell 7 can be transformed to supply a fuel tank with the exhaust gas. Since the exhaust gas may be a relatively nonreactive (eg, chemically inert) gas, such as N2, this results in the fuel cell dead space environment becoming relatively unreactive, decreasing the propensity to collect fuel vapors in the dead space and improving the safety of the aircraft. The water / waste water vapor outlet 13 may comprise a tube, a pipe, or an opening interconnected with a tube or pipe in fluid communication with an apparatus for improving the efficiency of the water treatment unit. As further described in the present invention, the apparatus for improving the efficiency of the emergency power supply unit 5 may comprise a fluidic interconnection between the water outlet. of waste water vapor 13 and an auxiliary supply unit 6 so that water can be injected into the auxiliary supply unit 6 to increase the performance of the auxiliary supply unit 6, for example , by densifying the air entering the engine 44 (with a momentary reference to FIG. 3) of the auxiliary supply unit 6 and / or by providing cooling, resulting in an improved thermodynamic cycle efficiency. With reference to Figures 1 and 3, a power conversion system 2 may also include an auxiliary power supply unit 6. The auxiliary power supply unit 6 may comprise a motor 44 and a generator 42, by which electricity can be generated. The motor 44 can be connected to the generator 42 via a shaft. The auxiliary power supply unit 6 may have several fluidic, electrical, and / or mechanical interconnections with other system elements. For example, the auxiliary supply unit 6 may comprise an air inlet 34, a fuel inlet 30, a water inlet 40, a purge air outlet 28, and a waste outlet 22. All the different inputs and outputs may be connected in fluidic and / or electrical communication with the elements of the motor 44 and / or the generator 42 of the auxiliary power supply unit 6. An auxiliary power supply unit 6 may comprise an input of Air 34. The air inlet 34 may comprise a tube, or a pipe, or an opening interconnected with a pipe or a pipe in fluid communication with an air source 35. For example, the air inlet 34 air 34 may include an engine inlet port 44 through which ambient air can be drawn into the engine 44 during combustion. An auxiliary power supply unit 6 may comprise a fuel inlet 30.
    [0009] The fuel inlet 30 may comprise an orifice in fluid communication with a fuel supply 18. The fuel inlet 30 may convey the fuel from the fuel supply 18 to the engine 44, where it is burned. with the air supplied through the air inlet 34. An auxiliary supply unit 6 may comprise an outlet of 10 residues 22. The outlet of residues 22 may be in fluid communication with the apparatus of Improving the Efficiency of the Emergency Feed Unit 5. The tailings outlet 22 can convey residues, for example, combustion products and / or unburned gases from the engine 44. The apparatus An improvement in the efficiency of the emergency power supply unit 5 can route the residues to an exhaust well 24 as later described in the present invention. An auxiliary power supply unit 6 may comprise a water inlet 40. As previously described in the present invention, the apparatus for improving the efficiency of the emergency power supply unit 5 may comprise an interconnection between a turbine inlet of a motor 44 of the auxiliary supply unit 6 and the outlet of water / waste water vapor 13 so that water / water vapor can be injected into the engine 44 of the auxiliary power unit 6 to increase the performance of the engine, for example, by densifying the air entering the engine and / or providing cooling. This water / steam is injected via the water inlet 40. The water inlet 40 includes an orifice into which water can be introduced and through which water can be conveyed to the water. motor 44 inlet port. The water / water vapor is introduced into an inlet port of the engine 44. The water cools the ambient air inlet (through cooling through evaporation), whereby the air is densified and thus, the combustion inside the motor 44 can be performed more efficiently. In some ground maintenance applications, injected water can be used in conjunction with conventional compressor washing devices / systems. The compressor wash improves the overall thermodynamic efficiency of the gas turbine engine by removing dirt / dust / sand / etc. agglomerated from the blades / blades of the compressor. An auxiliary supply unit 6 may comprise a purge air outlet 28. The purge air outlet 28 may comprise a tube, or a pipe, or an opening interconnected with the tube or a pipe through which the The air may be routed from the engine 44 prior to being burned and discharged out of the auxiliary supply unit 6. The purge air outlet 28 may be connected in fluid communication with the air conditioner. Thus, in this way, pressurized, hot and unburned air can be conveyed from the auxiliary supply unit 6 to the Emergency power supply unit 4. An auxiliary power supply unit 6 may comprise a power supply output 20. The power supply output 20 may comprise a conductive terminal in electrical communication with the generator 42. The output of power supply 20 can include a single conductor, or may comprise two conductors or may include any number of conductors. The power supply output 20 can supply a power supply from the generator 42 to an electric bus of an aircraft 36. Referring to FIG. 1, an energy conversion system 2 can comprise an aircraft improvement unit. Efficiency of the emergency power supply unit 5. The efficiency improvement unit of the emergency power supply unit 5 has different fluidic interconnections between the power supply unit. 6 and the emergency power supply unit 4. For example, an emergency power supply unit 4 may comprise a fuel cell 7, which can receive hydrogen and oxygen and generate heat. electricity, producing an effluent such as water and gas, for example, nitrogen gas. Thus, a fuel cell 7 (with a momentary reference to Figure 2) requires an input fuel and an input oxidant. However, the performance of a fuel cell 7 is often degraded significantly in the case where the oxidant is introduced at low pressure, or if the fuel cell 7 is operated at a low temperature. This may impose challenges during operation in an aircraft environment due to the decrease in ambient pressure and ambient temperature at altitudes above sea level (e.g. the tropopause). Accordingly, an apparatus for improving the efficiency of the emergency power supply unit 5 may comprise fluid connections by which the input pressure and the operating temperature of the fuel cell 7 are increased. An apparatus for improving the efficiency of the emergency power supply unit 5 can provide selective fluidic connectivity between the emergency power supply unit 4 and the auxiliary power supply unit 6. A An improvement in the efficiency of the emergency power supply unit 5 may include a heat exchanger 26 and a bypass valve 32. As used in the present invention, a heat exchanger may comprise a recuperator. The heat exchanger 26 may comprise at least two fluid paths not in fluid communication in which heat can be routed from one of the fluid paths to the other. The heat exchanger 26 can be connected to the waste outlet 22 of the auxiliary supply unit 6. The heat exchanger 26 can convey the hot exhaust stream leaving the engine 44 via the outlet 3021630 13 of the heat exchanger 26. However, the heat exchanger 26 can collect the heat from this exhaust stream and route it outside it, for example, to heat / preheat the exhaust stream. Air entering the oxygen inlet 16 of the emergency supply unit 4. Thus, the heat exchanger 26 can also receive compressed air from the purge air outlet 28. 44. The heat exchanger 26 can heat this air and subsequently route this air to the oxygen inlet 16 of the emergency supply unit 4. In this way, the unit of emergency power supply 4 can receive heated, unburned air which is pressurized by the engine 44. In other modes In one embodiment, a bypass valve 32 is disposed in connection with the heat exchanger 26. The bypass valve 32 can be actuated to allow the air from the purge air outlet 28 of the engine 44 to bypass the heat exchanger 26 and to directly reach the oxygen inlet 16 of the emergency supply unit 4. For example, during low-altitude operations (where the ambient air pressure and the temperatures are high), the air heating may be unnecessary, and thus the bypass valve 32 may be activated. As a result, the efficiency improving apparatus of the emergency power supply unit 5 can send air to the oxygen inlet 16 of the emergency power supply unit 4 which is at least either warmed up or under pressure. Similarly, the efficiency improving apparatus of the emergency power supply unit 5 can route the gas / fluid from the emergency power supply unit 4 to the control unit. Auxiliary supply 6. The apparatus for improving the efficiency of the emergency supply unit 5 may comprise a first tube 3 disposed between the water / waste water outlet 13 of the emergency supply unit 4 and the water inlet 40 of the auxiliary supply unit 6. The emergency supply unit 4 can produce water / water vapor, for example as the product of a chemical reaction (s) in the fuel cell 7. The first tube 3021630 14 can convey this water to the auxiliary supply unit 6 where it is injected into the fuel cell. 44. As previously described, this water can cool and / or densify the air entering the engine. Referring now to Figure 2, various aspects of an emergency power supply unit 45 comprising a fuel cell 7 are described. The fuel cell may be a hydrogen fuel cell and may include an anode 102, an electrolyte 104, and a cathode 106. At the anode 102, the hydrogen fuel is electrochemically dissociated in the presence of a catalyst in hydrogen ions and free electrons (2H2 -> 4H + + 4e-). The electrons flow out of the anode 102 to the power supply outlet 10. The hydrogen ions flow into the electrolyte 104 and are driven by concentration forces and potential forces to the cathode 106, where the oxygen gas is electrochemically combined in the presence of a catalyst with hydrogen ions and free electrons (routed from the circuit return path of the power supply output 10) to generate water (02 + 4H + + 4e-2H 2 O). Thus, the overall reaction in fuel cell 7 comprises 2H 2 + 02 2H 2 O + Energy. The amount of energy released is equivalent to the difference between the Gibbs free energy of the product and the Gibbs free energy of the reagents. This energy, routed via the power supply output 10 to the electric bus of the aircraft 36 (FIG 1) can be used to power aircraft systems.
    [0010] An emergency power supply unit 4 can also be used in reverse mode so that instead of generating electricity, electricity and water can be consumed and oxygen and hydrogen created. For example, when an aircraft is on the ground, the emergency power unit 4 can be used in reverse mode so that the fuel cell 7 generates oxygen, for example, for the pressurization of the cabin , and hydrogen, for example, for the fuel of the fuel cell 7 when it is used in conventional mode, for example, at altitude. For example, an external voltage can be applied to the power supply output 10, after which the power supply output 10 is actually used as a power supply unit. The water located at the cathode 106 can undergo electrolysis, forming hydrogen and oxide ions. The oxide ions are transported through the electrolyte 104 to the anode 102 where they are oxidized to form oxygen. In this reverse mode, the polarity of the battery is opposite to that used during normal operation. Thus, the fuel cell 7 operates according to the following equations. A cathodic reaction 106 may occur in which H 2 O + 2e-H2 + O 2. An anode reaction 102 may occur in which O 2 -10 1/2 O 2 + 2e-. Thus, the net reaction of the fuel cell can be H20 → 1/2 O2 + H2. In addition, the fuel cell 7 can not be a hydrogen fuel cell but may include other fuel cell configurations. For example, the fuel cell 7 may be an alkaline fuel cell, a phosphoric acid fuel cell, a proton exchange membrane fuel cell, a molten carbonate fuel cell, a direct alcohol fuel cell. , a methanol fuel cell, a solid oxide fuel cell, or any other type of fuel cell configured to provide desired operating characteristics. Referring now to FIG. 3, an auxiliary power supply unit 6 may comprise a motor 44 and a generator 42. The motor 44 may comprise a gas turbine 20 powered by the same fuel as the main engines of the aircraft, by for example, a kerosene type jet fuel such as Jet A, Jet A-1, JP-5, and / or JP-8. In another embodiment, the fuel may be a large cut or naphtha type jet fuel, such as Jet B and / or JP4. In addition, the fuel may be a synthetic fuel, such as a Fischer-Tropsch synthetic paraffinic kerosene fuel (FT-SPK), or bio-derived synthetic paraffinic kerosene (Bio-SPK), or may be 3021630 16 any other suitable fuel. In another embodiment, the motor 44 may comprise an internal reciprocating combustion engine, such as an engine based on an Otto cycle, a Diesel cycle, a Miller cycle, or an Atkinson cycle, or a rotary combustion engine. internal (eg, Wankel), or other internal combustion engine, or a continuous external combustion engine such as a gas turbine engine (based on the open Brayton cycle) powered by a different fuel from the aircraft engines , or any other heat engine. In addition, the motor 44 may be an internal combustion engine that is naturally aspirated or forced induction (either turbocharged or supercharged). The engine 44 may have a turbocharger which may be single or dual (twin) configuration using a centrifugal compressor directly coupled to either an axial flow turbine or a centrifugal flow turbine, and whose operation may be further improved. by structures such as: variable blade geometries, articulated relief valves, pressure relief / overpressure valves, and by methods such as: intermediate cooling, water spray injection, etc. The motor 44 may be mechanically connected to a generator 42 and may rotate the generator 42 (e.g., through a mechanical gearbox) through which electricity is generated. The generator 42 may be electrically connected to the power supply output 20 by internal wiring. Thus, the auxiliary power supply unit 6 can supply electricity via the power supply outlet 20 as previously described. A motor 44 may further be in fluid communication with the fuel inlet 30 of the auxiliary supply unit 6 so that the fuel is directed to the combustion chamber (s) of the engine 44 where it is burned. with an oxidant, such as air, sent via the air inlet 34 also in fluid communication with the engine 44. Similarly, as previously described, a motor 44 may be in fluid communication with the engine 44. water inlet 40 of the auxiliary supply unit 6 so that the water is directed towards the motor 44 so that the oxidant, such as air, sent via the air inlet 34 can be cooled and / or densified, so that the efficiency of the motor 44 is improved. In other embodiments, the purge air outlet 28 is in fluid communication with the motor 44, for example, with a compressor stage of a turbine engine, so that air under pressure but The unburnt can be vented to the purge air outlet 28 for use by other aircraft systems. Finally, the waste outlet 22 may be in fluid communication with the engine output stage 44, for example, with an output stage of a turbine engine, so that the combustion products can be discharged out of the engine. In other embodiments, the combustion products are conveyed via a heat exchanger 26 to an exhaust well 24. The exhaust well 24 may comprise a turbine exhaust, for example, a vent towards the external environment. Thus, the combustion products can be expelled from the aircraft.
    [0011] Since various aspects of a power conversion system 2 have been described, an energy conversion system 2 can be composed of many different materials or combinations of materials. For example, various components of the system may be composed of metal. For example, various aspects of an energy conversion system 2 may be made of metal, such as titanium, aluminum, steel, or stainless steel, although it may otherwise be composed of many other materials configured to provide a support, such as, for example, composite, ceramic, plastic, polymers, alloys, glass, binder, epoxy, polyester, acrylic, or any material or combination of materials having desired material properties, such as heat tolerance, strength, thickness, or weight. In other embodiments, various parts of the energy conversion systems 2 as described in the present invention are composed of different materials or combinations of materials, and / or may comprise coatings. In other embodiments, the energy conversion systems 2 may be composed of several materials, or any configuration of material suitable for improving or enhancing the resiliency and / or support of the system when subjected to wear in an operating environment of the aircraft or to satisfy other desired electromagnetic, chemical, physical, or material properties, for example, radar signature, heat generation, efficiency, electrical output, force, or a tolerance to heat.
    [0012] In other embodiments, various components may comprise an austenitic nickel-chromium-based alloy such as Inconel®, made available by the Special Metals Corporation of New Hartford, New York, USA. In other embodiments, various components may include ceramic matrix composite (CMC). In addition, various aspects may include a refractory metal, for example, a titanium alloy, for example titanium-zirconium-molybdenum (TZM). While the systems described in the present invention have been described in the context of aircraft applications; however, it will be appreciated in the light of the present invention that the systems described in the present invention can be used in other different applications, for example, in different vehicles, such as cars, trucks, buses, trains. , boats, and submersibles, space vehicles including orbital and sub-orbital vehicles with or without a pilot, or any other vehicle or device, or in connection with industrial processes, or propulsion systems, or any other system or process with a need for power generation. Advantages, other advantages and problem solutions have been described in the present invention with respect to specific embodiments. In addition, the connection lines indicated in the various figures contained in the present invention are intended to represent exemplary functional relationships and / or physical couplings between the various elements. It should be noted that many functional or alternative or additional physical connections may be present in a practical system. However, the strengths, advantages, solutions to problems, and all elements that may result in the presence or the strengthening of the presence of any asset, advantage, or solution must not be interpreted as features or elements of essential inventions, required or essential. In addition, when an expression similar to "at least one of A, B or C" is used, it is intended that the phrase be interpreted to mean that A alone may be present in one embodiment, that B alone may be present in one embodiment, that C alone may be present in one embodiment, or that any combination of the elements A, B and C may be presented in a single embodiment; for example, A and B, A and C, B and C, or A and B and C.
    [0013] The systems, methods and apparatus are described in the present invention. In the detailed description of the present invention, references to "other embodiments", "an embodiment", "an embodiment", "an exemplary embodiment", etc., indicate that the The disclosed embodiment may comprise a particular function, structure, or feature, but each embodiment may not necessarily include the particular function, structure, or feature. Moreover, these expressions do not necessarily refer to the same embodiment. Moreover, when a particular function, structure, or characteristic is described in the context of an embodiment, it is implied that the assignment of this function, structure, or feature in connection with other modes of realization, whether or not explicitly described, arises from the knowledge of a specialist in the field. After reading the description, the manner in which the description in other embodiments will become apparent will become apparent to a specialist in the field (s) concerned. As used in the present invention, the terms "comprises", "comprising", or any other variant thereof, are intended to cover a non-exclusive inclusion, so that a process, process, article, or a device that includes a list of items does not include only those items but may include other items not specifically listed or inherent in that process, process, article, or device.
    权利要求:
    Claims (15)
    [0001]
    REVENDICATIONS1. An integrated energy conversion system (2) comprising: an emergency power supply unit (4) comprising a fuel cell; an auxiliary power unit (6) comprising a motor and a generator in which the motor drives the generator to produce a power supply; and an apparatus for improving the efficiency of the emergency power supply unit (5) comprising a heat exchanger (26) and a bypass valve, the heat exchanger being in fluid communication with the unit emergency power supply and auxiliary power unit.
    [0002]
    An integrated energy conversion system according to claim 1, wherein the apparatus for improving the efficiency of the emergency supply unit comprises a first tube (3) through which the water can be fed from the fuel cell to the engine, wherein the heat exchanger is configured to selectively heat the compressed air and deliver compressed air from the engine to the fuel cell; and wherein the bypass valve can selectively route compressed air from the engine to the fuel cell.
    [0003]
    An integrated energy conversion system according to claim 1 or 2, wherein the engine comprises a gas turbine.
    [0004]
    An integrated energy conversion system according to any one of claims 1 to 3, wherein the fuel cell comprises a hydrogen fuel cell. 3021630 22
    [0005]
    An integrated energy conversion system according to any one of claims 2 to 4, wherein the fuel cell comprises: a fuel inlet (30) including an opening configured to interconnect with a pipe through which the fuel is fed from a fuel supply to the fuel cell; an oxygen inlet (16) including an opening in fluid communication with the efficiency improving apparatus of the emergency supply unit; an exhaust gas outlet (12) in fluid communication with an exhaust gas well; A waste water outlet (13) in fluid communication with the first tube of the efficiency improving apparatus of the emergency supply unit through which water is conveyed from the emergency power supply unit to the auxiliary power supply unit; and a power supply output connected to an electric bus of an aircraft. 15
    [0006]
    An integrated energy conversion system according to claim 5, wherein the auxiliary power unit comprises: a gas turbine; and an electric generator, wherein the gas turbine drives the electric generator, and wherein the generator is connected to a power supply output connected to the electric bus of an aircraft.
    [0007]
    The integrated energy conversion system of claim 6, wherein the emergency power supply efficiency improvement apparatus comprises: a fluid interconnection between a water outlet residual from the emergency power supply unit and the auxiliary power unit through which water can be injected into the engine of the auxiliary power unit; and the heat exchanger comprising a first fluid path and a second fluid path, wherein the first fluid path can accept pressurized air from a purge air outlet of the turbine. wherein the second fluid path can accept residues from a tailings outlet of the gas turbine, and wherein the pressurized air is reheated in response to the tailings and conveyed to the fuel cell of the gas turbine. emergency power supply unit.
    [0008]
    An integrated energy conversion system according to any one of claims 5 to 7, wherein the exhaust gas well comprises a fire extinguishing system.
    [0009]
    An integrated energy conversion system according to any of claims 5 to 8, wherein the exhaust gas well comprises a fuel tank inerting system. 20
    [0010]
    An integrated energy conversion system according to any one of claims 1 to 9, wherein the integrated energy conversion system is installed in an aircraft
    [0011]
    An integrated power conversion system comprising: an emergency power supply unit comprising a fuel cell; and an apparatus for improving the efficiency of the emergency power supply unit comprising a heat exchanger and a bypass valve, the heat exchanger being in fluid communication with the power supply unit. emergency, in which the heat exchanger heats the compressed air and sends the compressed air to an inlet of the emergency supply unit.
    [0012]
    An integrated energy conversion system according to claim 11, wherein the apparatus for improving the efficiency of the emergency power supply unit comprises: a first tube adapted to allow the water of be fed from the fuel cell to an auxiliary power unit; and wherein the bypass valve selectively conveys compressed air to the emergency supply unit without warming.
    [0013]
    An integrated power conversion system according to claim 12, wherein the emergency power supply unit comprises: a fuel cell comprising an opening interconnected with a pipe through which fuel is conveyed to the fuel cell ; an oxygen inlet including an opening in fluid communication with the apparatus for improving the efficiency of the emergency supply unit; An exhaust gas outlet through which the exhaust gas is released from the fuel cell; and a waste water outlet in fluid communication with the first tube of the unit for improving the efficiency of the emergency supply unit through which water is released from the fuel cell. 25 3021630 25
    [0014]
    An integrated power conversion system according to claim 13, wherein the apparatus for improving the efficiency of the emergency power supply unit comprises: a fluid interconnection between a waste water outlet of the the emergency supply unit and the auxiliary supply unit through which water can be injected into a motor of the auxiliary power unit; and wherein the heat exchanger comprises a first fluid path and a second fluid path, whereby the first fluid path can accept pressurized air from a motor bypass air outlet. the auxiliary supply unit, through which the second fluid path can accept residues from an engine residue output of the auxiliary power unit.
    [0015]
    The integrated energy conversion system of claim 14, wherein the fuel cell is a hydrogen fuel cell. 15
    类似技术:
    公开号 | 公开日 | 专利标题
    FR3021630A1|2015-12-04|
    Baroutaji et al.2019|Comprehensive investigation on hydrogen and fuel cell technology in the aviation and aerospace sectors
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    公开号 | 公开日
    FR3021630B1|2018-10-12|
    US20150349356A1|2015-12-03|
    US9871260B2|2018-01-16|
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    法律状态:
    2016-03-22| PLFP| Fee payment|Year of fee payment: 2 |
    2017-03-22| PLFP| Fee payment|Year of fee payment: 3 |
    2018-01-19| PLSC| Search report ready|Effective date: 20180119 |
    2018-03-22| PLFP| Fee payment|Year of fee payment: 4 |
    2020-03-19| PLFP| Fee payment|Year of fee payment: 6 |
    2021-03-23| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    US14/289,365|US9871260B2|2014-05-28|2014-05-28|Hybrid emergency power unit system|
    US14289365|2014-05-28|
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