• 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:
    The invention relates to a method for detecting leakage of fluid in a turbomachine (10). The turbomachine (10) comprises a high temperature fluid source, at least one fluid distribution pipe (14, 15) adapted to deliver said fluid to different parts of the turbomachine (10) and / or the aircraft (20). ) which is intended to be equipped by said turbomachine (10), a turbomachine compartment in which the distribution pipe (14, 15) is at least partly housed, said compartment having in operation a low temperature relative to the high temperature of the fluid supplied by the fluid source. The method comprises the following steps: measuring a temperature variation in the compartment between two instants to obtain a temperature gradient; and detecting a fluid leak if the temperature gradient is greater than or equal to a threshold temperature gradient. The invention further relates to a high temperature fluid distribution system for a turbomachine and a turbomachine (10) comprising such a fluid distribution system.
    公开号:FR3021350A1
    申请号:FR1454516
    申请日:2014-05-20
    公开日:2015-11-27
    发明作者:Alexandre Patrick Jacques Roger Everwyn；Arnaud Rodhain
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] TECHNICAL FIELD The invention relates to the field of turbomachines and in particular to the field of fluid distribution systems equipping such turbomachines. STATE OF THE PRIOR ART Fluid dispensing systems, in particular pressurized in the turbomachines, generally use a large number of pipes, some of which may be arranged at least in part in sensitive compartments of the turbomachines. Thus, because of the generally high temperature of these pressurized fluids, the slightest leakage of a pipe in one of these sensitive compartments of the turbomachine can be problematic and damage the turbomachine. This is particularly the case for the nacelle defrosting circuit (better known by its acronym NAI for Nacelle Anti Icing) and the pressurized air supply circuit of the starter, which are partly housed in a blower compartment (called in English). fan zone) located radially outside the fan casing of the turbomachine and inside the nacelle. Indeed, the blower of a turbomachine, and more particularly the blower compartment, may comprise elements of composite material (s) (s) with low temperature resistance. However, a leak in the blower compartment of the pressurized air passing through the NAI circuit can cause a sharp increase in the temperature in this compartment which is likely to exceed 350 ° C. At these temperatures, said elements of composite material (s) can keep their integrity only over a relatively short period of time, typically of the order of 15s.
    [0002] For these reasons, it is therefore necessary to set up fluid leak detection methods, whether at the level of the pipes or at the valves equipping said pipes. Such leak detection methods are known from documents FR 2987398 A1 and FR 2972485 A1. These two methods consist in checking the state of one or more valves of the pipelines of the fluid distribution system by monitoring in particular the pressure in the pipes. and / or in the sensitive compartment. Nevertheless, these two methods make it possible to respond only partially to the problem of monitoring leakage of fluid at high temperature in a sensitive compartment of the turbomachine. Indeed, if these methods allow for example the detection of a valve that would remain open and that could potentially generate, by this setting in constant communication, an increase in temperature in the sensitive compartment, they are not suitable for the detection of a leak that would be related to the breakage or untangling of a pipe of the pipeline. In addition, when the system has several pipes, these methods must be applied to each pipe passing through said sensitive compartment. It is also known from the prior art to install temperature sensors in the sensitive compartments. These temperature sensors allow the establishment of a fluid monitoring process in these sensitive compartments by detecting any abnormal rise in temperature. Such temperature monitoring therefore allows the detection of an unusual supply of high temperature fluids in the sensitive compartment which can come only from a high temperature fluid leak.
    [0003] Thus, such a leak detection method makes it possible to detect fluid leaks at high temperature regardless of the origin of these leaks and the number of ducts likely to leak. However, as shown in Figure 1, the temperature sensors used have a certain inertia. Indeed, Figure 1 is a graph showing the actual temperature 901 in the compartment during a fluid leak simulation in parallel with the temperature 902 measured by the temperature sensor. Thus, while the leakage of fluid results in a temperature rise in the almost instantaneous compartment (the total duration of the rise in temperature is less than 5s), the temperature sensor shows a much slower temperature rise (that is, it is of the order of 130-140s) since this sensor acts on the ambient temperature as a low pass filter having a high time constant. For example, for a threshold temperature of 120 ° C, considered critical for elements of composite material (s) with low temperature resistance, it takes nearly 15s to detect it while it is reached in the compartment in less than a second. If we add to this delay a latency period typically of 8s to process the information and that the turbomachine processing unit closes the valves of the pipe of the fluid distribution system, it follows that the elements composite material (s) are subjected to this critical temperature for a time of nearly 23s. This time ideally not to exceed 15s to safeguard the integrity of the composite material (s), it is necessary to reduce the detection time, for example less than 7s if latency period is 8s. This problem is particularly present for the fluid distribution system which comprises the pressurized air supply line and at high temperature of both the aircraft and the starter of the turbomachine and the air supply line of the NAI circuit. . Indeed, these pipes have pipes that are typically housed in the fan compartment of the turbomachine, this in particular for the pressurized air supply of the starter and the defrosting circuit of the input shaft. However, as already indicated, the blower compartment is particularly sensitive because of the elements of composite material (s) it contains. It is therefore particularly important that such a high temperature pressurized air distribution system permits the detection of high temperature air leakage in the blower compartment.
    [0004] DISCLOSURE OF THE INVENTION The object of the invention is to overcome this drawback and is therefore intended to provide a method for detecting leakage of fluid at high temperature in a turbomachine that makes it possible to detect a high-temperature leakage of fluid. in a compartment of the turbomachine regardless of the origin of the leak, this with a reduced detection time vis-à-vis the prior art. For this purpose, the invention relates to a method for detecting leakage of fluid in a turbomachine, said turbomachine comprising: a source of fluid at high temperature; at least one fluid distribution pipe adapted to distribute said fluid to different parts; of the turbomachine and / or the aircraft which is intended to be equipped with said turbomachine, - a turbomachine compartment in which the distribution pipe is at least partly housed, said compartment having in operation a low temperature relative to the high the temperature of the fluid supplied by the fluid source, the method comprising the following steps: measuring a variation of temperature in the compartment between two instants to obtain a temperature gradient; detecting a leakage of fluid if the gradient of temperature is greater than or equal to a threshold temperature gradient. With such a method it is possible to detect a leak of high temperature fluid in the compartment in a much lower time than that of a simple detection by temperature threshold. Indeed, the supply of fluid in the compartment during a leak usually generates, as illustrated in Figure 1, a temperature increase in the compartment that is almost instantaneous and has a direct impact on the measured temperature. The measured temperature variation, and thus also the gradient of the measured temperature, are important from the first moments of the leak.
    [0005] Thus, with this detection method, it is possible to detect the occurrence of a leak of high temperature fluid in the compartment with a detection time nearly ten times lower than that of a method of the prior art allowing to detect a fluid leak regardless of its origin.
    [0006] It is understood above and in the rest of this document by low temperature relative to the high temperature that the temperature difference between the high temperature fluid supplied by the fluid source and the temperature in the compartment is greater than 50 ° C. and preferably at 100 ° C. Similarly, the step of detecting a leak is preferably a step of detecting a fluid leak if the temperature gradient is strictly greater than a threshold temperature gradient. The method may further comprise the following steps: - measurement of a temperature in the compartment, - detection of a fluid leak if the temperature measured in the compartment is greater than or equal to a threshold temperature. Such complementary detection steps are particularly suitable for the detection of a high temperature low temperature fluid leak and which causes a temperature rise contained. The measurement of a temperature variation can be performed in at least two locations of the compartment so as to obtain at least two temperature gradients, the detection of a fluid leak thus occurring if at least one of the two gradients of temperature is greater than the threshold temperature gradient. Such detection provided by redundant sensors allows robust detection regardless of the location in the fluid leaking compartment. The method may comprise an additional step of: inhibiting the leak detection step when the turbomachine is in a predetermined state in which the temperature gradient is greater than or equal to a threshold temperature gradient.
    [0007] The method may comprise an additional step of: modifying the threshold temperature gradient as a function of the state of the turbomachine. Such steps of inhibition and modification of the threshold temperature gradient make it possible to avoid erroneous detections of fluid leaks which could be due to certain extreme operating configurations of the turbomachines such as starting up. The method may comprise an additional step of: closing the fluid line upstream of the compartment if a leak is detected. The compartment may be located radially between a fan casing and a nacelle of the turbomachine. The turbomachine may comprise a first and a second fluid duct, the first duct being a duct for distributing said fluid to the aircraft and to a starter of the turbomachine, the second duct being a pipe for distributing the fluid at a level of air inlet shaft of the turbomachine, the first and the second pipe being at least partly housed in the compartment The method according to the invention is particularly suitable for such compartments. The invention also relates to a high temperature fluid distribution system for a turbomachine comprising: a source of fluid at high temperature; at least one fluid distribution pipe adapted to deliver said fluid to different parts of the turbomachine and / or the aircraft which is intended to be equipped with said turbomachine, - a turbomachine compartment in which the distribution pipe is at least partly housed, said compartment having in operation of the turbomachine a low temperature relative to the high temperature of the fluid provided by the fluid source, - at least one temperature sensor of the turbomachine compartment, - a processing unit arranged to control the temperature measuring means and configured to detect a fluid leak in the compartment, the treatment unit being configured to provide from the measuring means a measure of variation of temperature in the compartment between two instants to deduce a temperature gradient, and to detect a leakage of fluid if the temperature gradient is greater and / or equal to a threshold temperature gradient.
    [0008] Such a system allows the implementation of a method according to the invention and thus allows to benefit from the advantages of the method according to the invention. Two temperature sensors can be installed in the turbomachine compartment on either side of the turbine engine fan. The invention further relates to a turbomachine comprising a fluid distribution system according to the invention. Such a turbomachine has the advantages of the process according to the invention. BRIEF DESCRIPTION OF THE DRAWINGS The present invention will be better understood on reading the description of exemplary embodiments, given purely by way of indication and in no way limiting, with reference to the appended drawings in which: FIG. 1 is a graph showing the variation of the temperature in the fan of a turbomachine during a leak of pressurized high temperature air paralleled with the temperature measured by a temperature sensor of the same fan, FIG. 2 schematically illustrates a fluid distribution circuit 3 illustrates respectively a graph representing the variation of the temperature gradient in the fan of a turbomachine during a leak of fluid at high temperature and a graph representing the variation of the temperature gradient measured by a turbine engine, FIG. temperature sensor of the same blower during the same leak. The different parts shown in the figures are not necessarily in a uniform scale, to make the figures more readable. The different possibilities (variants and embodiments) must be understood as not being exclusive of each other and can be combined with one another.
    [0009] DETAILED DESCRIPTION OF PARTICULAR EMBODIMENTS FIG. 2 schematically illustrates an exemplary fluid distribution system, more specifically a pressurized air system, according to the invention equipping a turbomachine 10. Such a fluid distribution system comprises: a high compressor pressure 11 forming a source of pressurized air at high temperature, - a fan 12 having a housing which delimits externally a stream of secondary flow and outside which are installed a first and a second temperature sensor 121 for measuring the temperature in the fan compartment, a nacelle 13 of the turbomachine comprising an inlet sleeve 131 of the turbomachine for the admission of air into the latter, a first high-pressure pipe 14 for drawing pressurized air at high temperature. from the high pressure compressor to the aircraft, said first pipe having a br secondary reed 14a for supplying pressurized air to a starter 122 of the turbomachine, - a second de-icing line 15 of the nacelle 13 and the input shaft 131 of the turbomachine 10, - a motor calculator, not shown.
    [0010] The fan 12 of the turbomachine, generally comprises elements of composite material (s) (s) sensitive (s) at high temperature. The fan 12 is therefore a sensitive compartment of the turbomachine in which it is important to detect a possible leakage of fluid at high temperature, such as the pressurized air supplied by the high pressure compressor 11. The high pressure compressor 11 can supply the first and second lines 14, 15 with pressurized air at high temperatures typically up to 500 ° C. The first pipe 14 is designed to draw pressurized air from the high-pressure compressor in order to supply the aircraft with pressurized air, in particular for the air-conditioning systems 21 of the aircraft and for the de-icing of the wings 22 of the aircraft. 'aircraft. Upstream of a heat exchanger 141 for cooling the pressurized air from air taken from the blower (from the pipe 123 referenced in Figure 2), the first pipe 14 comprises a secondary pipe 14a to the starter 122. Thus, the first pipe 14 makes it possible to feed the starter 122 located in the fan 12 with pressurized air whose temperature is typically of the order of 360 ° C. The first pipe 14 comprises first valves 142, typically so-called ECS valves (meaning English: Environmental Control System, that is to say environmental control system) to regulate the flow of air taken from the high-pressure compressor 11 The second duct 15 supplies the de-icing circuit of the air inlet duct 131 of the nacelle 13. The second duct 15 comprises second valves 151 for regulating the flow rate of the air taken from the high-pressure compressor 11 Typically, the second pipe 15 makes it possible to feed the de-icing circuit of the air inlet pipe 131 with a pressurized air of a temperature of the order of 500 ° C. Whether it is the first or the second duct 14, 15, these passing through the blower 12, part of their respective ducts are housed in the blower compartment. Thus, in case of leakage of one of these pipes in the blower compartment, it generates a supply of pressurized air at high temperature and therefore a rise in temperature in the compartment. Such a rise in temperature is detrimental to certain elements of composite material (s) that may be in the blower compartment. In order to allow detection of such leaks, the fan compartment comprises the first and second temperature sensors 121 which are arranged on either side of the compartment, for example diametrically opposite to the fan casing 12, for detect any rise in temperature that would result from a hot air leak in the blower compartment. The first and second temperature sensors 121 are in communication with the engine computer. These first and second temperature sensors 121 may be, for example, sensors of the variable resistance type (better known under the name "Variable Resistance Transducer" giving the initials VRT).
    [0011] Advantageously, the temperature measured by each sensor is derived and then filtered with a second-order low-pass filter, in order to eliminate any noise on the measurement of the temperature gradient due to the bypass operation without unduly attenuating this same measurement. gradient. To enable a leak of pressurized air to be detected in the blower 12, the engine computer is configured to implement a process comprising the following steps: measuring a first and second temperature in the blower compartment from the first and second the second temperature sensor 121, said measurements being compared with a measurement made at a previous instant to determine for each of them a temperature variation between two instants and to obtain for each of them a temperature gradient, - detection of a leakage of fluid if at least one of the two temperature gradients is greater than or equal to a threshold temperature gradient or if one of the two temperatures in the compartment is greater than or equal to a threshold temperature.
    [0012] With such a configuration, fluid leakage is detected according to two different principles. The first principle, illustrated in FIG. 1, is similar to the configuration of the engine computers of the prior art described above, and consists in directly detecting the rise in temperature and the exceeding of a threshold temperature, typically 120 ° C. . This first measurement principle is, in the context of the invention, mainly dedicated to low leakage of pressurized air which cause a slower rise in temperature. The second detection principle is illustrated in FIG. 3. It consists in detecting a sharp increase in a temperature gradient which would be related to a large supply of pressurized air at high temperature due to a leak of a pipe the first or the second pipe 14, 15, typically caused by a sudden rupture or unmolding of one of these two pipes. Thus, FIG. 3 illustrates in parallel the variation 911 of the real temperature gradient dT (1 ') dt in the fan compartment with the temperature gradient variation 912 measured by one of the temperature sensors 121. It can thus be seen that when a pipe begins to leak, the gradients in actual temperature and measured show an almost instantaneous increase, these being differentiated only by the intensity of this increase. This strong increase is followed, for the real temperature gradient, by a fallout just as abrupt as the previous increase, while the fallout is much slower for the gradient of the measured temperature. Thus, the second detection principle consists in verifying that the temperature gradient does not exceed a threshold gradient characteristic of the sudden increase in temperature which directly follows the breakage or untangling of a pressurized air line. This second principle therefore makes it possible, for a rapid increase in temperature in the blower, which is typically the case during a rupture or unscrewing of a pipe of one of the first and second pipe 14, 15, a time detection much less than the 15s required according to the first principle and the configuration according to the prior art.
    [0013] The engine computer is also configured to, when a pressurized air leak is detected, close the pipes likely to be the source. In addition to this closing of the first and second valves, the engine computer can also be configured to transmit an error code to the aircraft so as to indicate that a failure has just occurred. According to another possibility of the invention, the engine computer may be configured to inhibit the leak detection step when the turbomachine is in a predetermined state in which the temperature gradient is likely to be greater than or equal to the temperature gradient threshold. This predetermined state may be for example a motor start step. According to a variant of this possibility of the invention, the engine computer can be configured to modify the value of the threshold temperature gradient to adapt it as a function of the state of the turbomachine. Thus, for example, the engine computer can be configured to increase the value of the threshold temperature gradient during startup of the turbomachine. With such a configuration, the engine computer forms a processing unit configured to supply from the temperature sensors 121 a temperature variation measurement in the blower 12 between two instants to deduce a temperature gradient, and to detect a leak of fluid if the temperature gradient is greater than and / or equal to the threshold temperature gradient. According to a preferred variant of the invention, the engine computer may be configured to detect a leakage of fluid if the temperature gradient is strictly greater than the threshold temperature gradient. It should be noted that if, in the embodiment above, the computer is adapted to implement the two detection principles described, it can also be configured to perform a leak detection according to the second described principle, that is, by detecting whether a temperature gradient is greater than or equal to a threshold temperature gradient, without performing detection according to the first principle. According to this same possibility, the engine computer can also be, in addition, configured to detect a pressurized air leak according to a third principle not described, such as those described in these documents FR 2987398 A1 and FR 2972485 A1. It should be noted that if in the embodiment described above, the leak detection method allows a leak detection of pressurized air in the fan compartment of the turbomachine, it can be adapted for leak detection in another sensitive compartment of the turbomachine. It should also be noted that if in the embodiment described above, the distribution system is a pressurized air distribution system in the turbomachine, the invention can be adapted for the detection of high temperature fluid leakage. other than leakage of pressurized air without departing from the scope of the invention. Thus, the invention can thus be applied to an oil distribution circuit at high temperature without departing from the scope of the invention.
    权利要求:
    Claims (11)
    [0001]
    REVENDICATIONS1. A method for detecting fluid leakage in a turbomachine (10), said turbomachine (10) comprising: - a high temperature fluid source, - at least one fluid distribution pipe (14, 15) adapted to deliver said fluid to different parts of the turbomachine (10) and / or the aircraft (20) which is intended to be equipped with said turbomachine (10), - a turbomachine compartment (10) in which the distribution pipe (14, 15) is at least partially housed, said compartment having in operation a low temperature relative to the high temperature of the fluid supplied by the fluid source, the method comprising the following steps: - measurement of a temperature variation in the compartment between two instants to obtain a temperature gradient, - detection of a fluid leak in the compartment if the temperature gradient is greater than or equal to a threshold temperature gradient.
    [0002]
    2. A method of leak detection according to claim 1 further comprising the following steps: - measurement of a temperature in the compartment, - detection of a fluid leak if the temperature measured in the compartment is greater than or equal to a temperature threshold.
    [0003]
    A leak detection method according to claim 1 or 2 wherein the measurement of a temperature change is performed in at least two locations of the compartment so as to obtain at least two temperature gradients, the detection of a leak of fluid thus occurring if at least one of the two temperature gradients is greater than the threshold temperature gradient.
    [0004]
    4. Leak detection method according to any one of claims 1 to 3, comprising an additional step of: - inhibition of the leak detection step when the turbomachine is in a predetermined state in which the temperature gradient is greater than or equal to a threshold temperature gradient.
    [0005]
    5. Leak detection method according to any one of claims 1 to 3, comprising an additional step of: - modification of the threshold temperature gradient as a function of the state of the turbomachine.
    [0006]
    6. Leak detection method according to any one of claims 1 to 5, comprising an additional step of: - closing the fluid line upstream of the compartment if a leak is detected.
    [0007]
    7. Leak detection method according to any one of claims 1 to 6, wherein the compartment is located radially between a fan casing (12) and a nacelle (13) of the turbomachine (10).
    [0008]
    8. A method of leak detection according to any one of claims 1 to 7, wherein the turbomachine comprises a first and a second pipe (14, 15) fluid, the first pipe (14) being a pipe for distributing said fluid to the aircraft and a starter (122) of the turbomachine (10), the second pipe (15) being a pipe for distributing the fluid at an air inlet shaft (131) of the turbomachine ( 10), the first and the second pipe being at least partly housed in the compartment.
    [0009]
    9. High temperature fluid distribution system for a turbomachine comprising: a source of fluid at high temperature; at least one fluid distribution pipe (14, 15) adapted to deliver said fluid to different parts of the turbomachine; and or the aircraft that is intended to be equipped with said turbomachine, - a turbomachine compartment in which the distribution pipe is at least partially housed, said compartment having in operation of the turbomachine a low temperature relative to the high temperature of the fluid supplied by the fluid source, - at least one temperature sensor (121) of the turbomachine compartment, - a processing unit arranged to control the temperature measuring means and configured to detect fluid leakage in the compartment, the fluid distribution system being characterized in that the processing unit is configured to provide from the measuring means a temperature variation measurement in the compartment between two instants to deduce a temperature gradient, and to detect a leakage of fluid if the temperature gradient is greater than and / or equal to a threshold temperature gradient .
    [0010]
    10. Fluid distribution system according to claim 9, wherein two temperature sensors (121) are installed in the turbomachine compartment on either side of the fan (12) of the turbomachine. 25
    [0011]
    11. A turbomachine comprising a fluid distribution system according to one of claims 9 and 10.
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    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US20100147399A1|2006-05-18|2010-06-17|Airbus Deutschland Gmbh|Wiring Arrangement For Protecting A Bleed Air Supply System Of An Aircraft Against Overheating And Bleed Air Supply System Incorporating Such A Wiring Arrangement|
    US20100158068A1|2008-12-22|2010-06-24|Embraer - Empresa Brasileira De Aeronautica S.A.|Bleed leakage detection system and method|
    EP2369318A2|2010-03-05|2011-09-28|General Electric Company|Thermal Measurement System and Method for Leak Detection|
    FR2972485A1|2011-03-08|2012-09-14|Snecma|METHOD FOR MONITORING THE CHANGE OF STATE OF A VALVE BY MEASURING PRESSURE|FR3054595A1|2016-07-27|2018-02-02|Ge Energy Products France Snc|GAS TURBINE COMPARTMENT COMPRISING A HOT AIR LEAK DETECTION DEVICE AND METHOD OF DETECTING HOT AIR LEAK DETECTION|
    FR3081924A1|2018-05-30|2019-12-06|Safran Aircraft Engines|TURBOMACHINE FOR AN AIRCRAFT COMPRISING A PRESSURIZED FLUID CONDUIT SURROUNDED BY A BRAIDED OR WOVEN METAL SHEATH|US3059660A|1958-10-08|1962-10-23|Gen Electric|Turbine control system|
    GB889305A|1959-11-26|1962-02-14|Rolls Royce|Gas turbine engine|
    US3769998A|1971-10-07|1973-11-06|Garrett Corp|Regulator and shutoff valve|
    US3771350A|1971-12-30|1973-11-13|Aviat Inc|Pipeline leak detector|
    US3981466A|1974-12-23|1976-09-21|The Boeing Company|Integrated thermal anti-icing and environmental control system|
    US4006634A|1975-09-17|1977-02-08|National Semiconductor Corporation|Flow meter|
    US4351150A|1980-02-25|1982-09-28|General Electric Company|Auxiliary air system for gas turbine engine|
    US4710095A|1982-08-04|1987-12-01|General Electric Company|Turbomachine airflow temperature sensor|
    US4655607A|1983-12-19|1987-04-07|Santa Barbara Research Center|High speed hot air leak sensor|
    IL78786D0|1985-06-03|1986-08-31|Short Brothers Plc|Duct for hot air|
    US4702273A|1986-03-07|1987-10-27|Parker Hannifin Corporation|Electrically controlled starter air valve|
    US4852343A|1987-07-02|1989-08-01|Avco Corporation|Method of operating anti-icing valve|
    US5063963A|1990-08-09|1991-11-12|General Electric Company|Engine bleed air supply system|
    GB9120113D0|1991-09-20|1992-09-23|Short Brothers Plc|Thermal antiicing of aircraft structures|
    US5463865A|1993-09-30|1995-11-07|General Electric Company|Starter air valve position pressure transducer|
    US5581995A|1995-03-14|1996-12-10|United Technologies Corporation|Method and apparatus for detecting burner blowout|
    FR2772341B1|1997-12-12|2000-03-24|Aerospatiale|HOT AIR DIFFUSER FOR AIR INTAKE COVER OF REACTION ENGINE WITH DEFROSTING CIRCUIT|
    US6098011A|1998-05-18|2000-08-01|Alliedsignal, Inc.|Efficient fuzzy logic fault accommodation algorithm|
    DE10111640A1|2001-03-10|2002-10-02|Airbus Gmbh|Procedure for the detection and reporting of overheating and fires in an aircraft|
    FR2887294B1|2005-06-21|2007-08-10|Airbus France Sas|SYSTEM FOR DEFROSTING THE EDGE OF AN AIR INLET HOOD FOR A TURBOMOTEUR|
    US7725272B2|2006-03-30|2010-05-25|Codman Neuro Sciences, Sarl|Methods and devices for monitoring fluid of an implantable infusion pump|
    US7784263B2|2006-12-05|2010-08-31|General Electric Company|Method for determining sensor locations|
    US7588368B2|2006-12-20|2009-09-15|Cummins Inc.|System for diagnosing temperature sensor operation in an exhaust gas aftertreatment system|
    GB0703336D0|2007-02-20|2007-03-28|Thermocable Flexible Elements|Temperature detector|
    US20100003123A1|2008-07-01|2010-01-07|Smith Craig F|Inlet air heating system for a gas turbine engine|
    GB2462826B|2008-08-20|2014-03-12|Rolls Royce Plc|A method for detecting overpressure inside a compartment associated with a gas turbine nacelle|
    US8100632B2|2008-12-03|2012-01-24|General Electric Company|Cooling system for a turbomachine|
    US8061657B2|2008-12-31|2011-11-22|General Electric Company|Method and apparatus for aircraft anti-icing|
    FR2944871B1|2009-04-22|2011-07-01|Snecma|SEALING HEAD FOR INSTALLATION OF FLUID TESTS ON A PIECE OF AIRCRAFT TURBOMACHINE|
    FR2945270B1|2009-05-05|2011-04-22|Airbus France|DEFROSTING DEVICE FOR PROPFAN PROPELLER BLADES|
    IT1396514B1|2009-11-27|2012-12-14|Nuovo Pignone Spa|METHOD OF CONTROL OF TURBINE BASED ON RELATIONSHIP BETWEEN DISCHARGE TEMPERATURE AND TURBINE PRESSURE|
    JP2011183922A|2010-03-08|2011-09-22|Mitsubishi Heavy Ind Ltd|Anti-icing and deicing device at wing leading edge part in aircraft and main wing of aircraft|
    FR2957586B1|2010-03-18|2012-04-27|Airbus Operations Sas|DEFROSTING DEVICE COMPRISING MEANS FOR DETECTING A LEAK AT A HOT AIR SUPPLY|
    US8702372B2|2010-05-03|2014-04-22|Bha Altair, Llc|System and method for adjusting compressor inlet fluid temperature|
    US9097182B2|2010-08-05|2015-08-04|General Electric Company|Thermal control system for fault detection and mitigation within a power generation system|
    US9019108B2|2010-08-05|2015-04-28|General Electric Company|Thermal measurement system for fault detection within a power generation system|
    US20120048000A1|2010-08-31|2012-03-01|Joseph Kirzhner|Method and system to detect and measure piping fuel leak|
    CN102162765B|2011-01-26|2012-06-06|南京航空航天大学|System and method for detecting leakage of high-temperature gas in high-temperature high-pressure guide pipe of airplane|
    US8997558B2|2011-03-29|2015-04-07|General Electric Company|Combustor probe for gas turbine|
    DE102011102458A1|2011-05-24|2012-11-29|Rolls-Royce Deutschland Ltd & Co Kg|Deicing device of an aircraft gas turbine engine|
    FR2987398B1|2012-02-24|2017-07-21|Snecma|SYSTEM FOR DETECTING FAILURE PREMISES OF A VALVE OF AN AIRCRAFT ENGINE|
    US9261054B2|2012-03-23|2016-02-16|Ford Global Technologies, Llc|Fuel system diagnostics|
    US9140189B2|2012-04-11|2015-09-22|General Electric Company|Systems and methods for detecting fuel leaks in gas turbine engines|
    US9239008B2|2012-10-16|2016-01-19|General Electric Company|Turbine leak detection system|
    US20140119881A1|2012-10-31|2014-05-01|General Electric Company|Apparatus for recirculating a fluid within a turbomachine and method for operating the same|
    US9528880B2|2013-08-16|2016-12-27|General Electric Company|Method and system for gas temperature measurement|
    US9933313B2|2013-09-06|2018-04-03|United Technologies Corporation|Method for determining circumferential sensor positioning|
    US9764847B2|2013-10-18|2017-09-19|The Boeing Company|Anti-icing system for aircraft|
    KR101490947B1|2013-11-22|2015-02-06|현대자동차 주식회사|Leak detection method of reducing agent pumping system|
    GB201404462D0|2014-03-13|2014-04-30|Rolls Royce Plc|Ice thickness measurement sensor|
    ITUB20151085A1|2015-05-28|2016-11-28|Alenia Aermacchi Spa|Nacelle for aircraft engine with de-icing system using a two-phase fluid.|
    US9914543B2|2015-12-09|2018-03-13|The Boeing Company|System and method for aircraft ice detection within a zone of non-detection|WO2015124361A1|2014-02-19|2015-08-27|Siemens Aktiengesellschaft|Turbo-machine having a thermal transfer line|
    GB2533936B|2015-01-07|2017-10-25|Homeserve Plc|Flow detection device|
    GB201501935D0|2015-02-05|2015-03-25|Tooms Moore Consulting Ltd And Trow Consulting Ltd|Water flow analysis|
    US20170267360A1|2016-03-18|2017-09-21|Rohr, Inc.|Thermal management system for deicing aircraft with temperature based flow restrictor|
    USD800591S1|2016-03-31|2017-10-24|Homeserve Plc|Flowmeter|
    US10066630B2|2016-06-15|2018-09-04|General Electric Company|Method and system for metallic low pressure fan case heating|
    DE102020102332A1|2020-01-30|2021-08-05|Rolls-Royce Deutschland Ltd & Co Kg|Sensor device and measurement method|
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    优先权:
    申请号 | 申请日 | 专利标题
    FR1454516A|FR3021350B1|2014-05-20|2014-05-20|METHOD FOR DETECTING FLUID LEAKAGE IN TURBOMACHINE AND FLUID DISPENSING SYSTEM|FR1454516A| FR3021350B1|2014-05-20|2014-05-20|METHOD FOR DETECTING FLUID LEAKAGE IN TURBOMACHINE AND FLUID DISPENSING SYSTEM|
    US14/714,551| US10400623B2|2014-05-20|2015-05-18|Method for detecting a fluid leak in a turbomachine and system for distributing a fluid|
    GB1508575.6A| GB2528549B|2014-05-20|2015-05-19|Method for detecting a fluid leak in a turbomachine and system for distributing a fluid|
    CN201510257835.XA| CN105092158B|2014-05-20|2015-05-20|Method for detecting fluid leakage in a turbomachine and system for distributing fluid|
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