• 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 turbomachine (30) with a double flow comprising a nacelle (11) forming an air inlet lip, a set of compressors (14), a set of turbines (18), a supply pipe ( 55), a transfer line (56) for circulating oil from the compressor assembly (14) to the turbine assembly (18), a deicing circuit (310) for the inlet lip of air, and a thermal management system (300) comprising: - a first heat exchanger (51) ensuring a heat exchange between the fuel of the supply line (55) and the oil of the transfer line (56); a loop (302) comprising a main pipe (306) and a pump (304) circulating a heat transfer fluid in the main pipe (306), where the main pipe (306) is connected to the outlet of the pump (304) and enters an inlet of a third heat exchanger (308), where on exit of the third heat exchanger (308), the main pipe (306) joins an inlet of the de-icing circuit (310), where at the outlet of the de-icing circuit (310), the main pipe (306) joins the inlet of the pump ( 304), and wherein the third heat exchanger (308) provides a heat exchange between the heat transfer fluid of the main pipe (306) and the oil of the transfer pipe (56) exiting the first heat exchanger (51).
    公开号:FR3054856A1
    申请号:FR1657541
    申请日:2016-08-03
    公开日:2018-02-09
    发明作者:Jean Michel Rogero；Olivier Verseux
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    TECHNICAL AREA
    The present invention relates to an aircraft turbomachine comprising a thermal management system and an aircraft comprising at least one such turbomachine.
    STATE OF THE PRIOR ART
    Fig. 1 shows a turbomachine 10 of an aircraft. The turbomachine 10 is equipped with a thermal management system 50 of the prior art. The thermal management system 50 makes it possible to manage the thermal energy of the propulsion unit comprising the turbomachine 10, the nacelle 11 and the other systems of the propulsion unit, by removing the excess heat to redistribute it to the systems requiring heat to perform a function through the circulation of a heat transfer fluid.
    In particular, part of the thermal energy is used to regulate the temperature of fluids (engine oil, electric generator, hydraulic fluid, air conditioning), structures (engine turbine, air intake lip and edge of 'wing attack for an anti-icing function) and systems (valve, electronics, actuator, pump, etc.).
    Most of this part of the thermal energy is then lost to the engine thrust.
    The turbomachine 10 comprises:
    - a blower 12 intended to generate an air flow in the turbomachine 10 in a direction of movement 13 of the air in the turbomachine 10, where in known manner, the air flow then moves downstream of the blower 12 ,
    a set of compressors 14 downstream of the fan 12,
    a combustion chamber 16 downstream from the set of compressors 14, and
    - a set of turbines 18 downstream of the combustion chamber 16.
    The thermal management system 50 generally comprises:
    a first heat exchanger 51,
    a second heat exchanger 52, and
    - a third heat exchanger 53.
    The thermal management system 50 also includes a hot air pipe 54 which takes hot air from the primary flow of the compressor assembly 14 and transports it, for example, to the nacelle 11 to defrost it. This air is released to the outside and is therefore lost.
    The turbomachine 10 also comprises a supply pipe 55 which supplies the combustion chamber 16 with fuel.
    The turbomachine 10 also comprises a transfer pipe 56 which allows the circulation of hot oil from the engine, in particular from the set of compressors 14, to the first 51 and third 53 heat exchangers and then its reintegration in the engine, in particular in the turbine set 18.
    The first heat exchanger 51 provides heat exchange between the fuel in the supply line 55 and the oil in the transfer line 56 in order to heat the fuel by the heat given off by the oil and thus cool it.
    The third heat exchanger 53 provides heat exchange between the oil in the transfer line 56 and the air in a first air line 57 which takes air from the secondary flow of the turbomachine 10 and rejects it. outside or in the secondary flow. This third heat exchanger 53 makes it possible to complete the cooling of the oil.
    The thermal management system 50 also includes an air conditioning system 58 which draws air from the primary flow in general at the intermediate stage and the final stage of the set of compressors 14. A To this end, the air conditioning system 58 comprises a first duct 59 which takes the air from the intermediate stage and a second duct 60 which takes the air from the final stage. The first 59 and the second pipe 60 join upstream of the second heat exchanger 52 and exit from the second heat exchanger 52 to supply the air conditioning system for the air in the cabin of the aircraft.
    The second heat exchanger 52 ensures a heat exchange between, on the one hand, the air from the first 59 and from the second pipe 60 and, on the other hand, the air from a second air pipe 61 which takes off air in the secondary flow of the turbomachine 10 and discharges it outside or into the secondary flow. This second heat exchanger 52 makes it possible to cool the air coming from the first 59 and the second pipe 60.
    Although such an installation is entirely satisfactory, it results in increased drag and therefore greater fuel consumption.
    STATEMENT OF THE INVENTION
    The object of the present invention is to provide a turbomachine comprising a thermal management system which allows a reduction in drag and a better management of the flow of fluids in the turbomachine.
    To this end, there is provided a turbomachine with a double flow of an aircraft comprising a nacelle forming an air intake lip, a set of compressors, a combustion chamber, a set of turbines, a supply line supplying fuel the combustion chamber, a transfer line ensuring the circulation of oil from the compressor assembly to the turbine assembly, a de-icing circuit for the air intake lip, and a thermal management system comprising:
    - a first heat exchanger ensuring a heat exchange between the fuel in the supply line and the oil in the transfer line,
    - a loop comprising a main pipe and a pump intended to circulate a heat transfer fluid in the main pipe, where the main pipe is connected to the outlet of the pump and enters an inlet of a third heat exchanger, where at the outlet of the third heat exchanger, the main pipe joins an inlet to the defrosting circuit, where at the outlet of the defrosting circuit, the main pipe joins the inlet of the pump, and where the third heat exchanger provides heat exchange between the heat transfer fluid the main line and the oil in the transfer line coming out of the first heat exchanger.
    This particular arrangement allows better anti-icing management at the level of the air intake lip.
    Advantageously, the thermal management system comprises:
    - a first three-way valve arranged upstream of the inlet of the third heat exchanger and a first bypass pipe arranged between the first valve and the main pipe, downstream of the outlet of the third heat exchanger, and / or
    - a second three-way valve arranged upstream from the inlet of the defrosting circuit and a second bypass line arranged between the second valve and the main line, downstream from the outlet of the defrosting circuit.
    Advantageously, the thermal management system comprises a fourth heat exchanger disposed on the main pipe between the outlet of the defrosting circuit and the inlet of the pump, and the fourth heat exchanger provides heat exchange between the heat transfer fluid of the main pipe and the air from a first air duct which takes air from the secondary flow of the turbomachine and discharges it outside or into the secondary flow.
    Advantageously, the thermal management system comprises a third three-way valve arranged upstream of the inlet of the fourth heat exchanger and a third bypass pipe arranged between the third valve and the main pipe, downstream of the outlet of the fourth heat exchanger .
    Advantageously, the thermal management system includes an air conditioning system which draws air from the primary flow of the compressor assembly through a first and a second pipe which supply an air conditioning system of the air from the aircraft, a second heat exchanger ensuring a heat exchange, on the one hand, between the air of the first and of the second pipe and, on the other hand, the heat transfer fluid of the main pipe, and the second heat exchanger is arranged on the main pipe between the outlet of the third heat exchanger and the inlet of the defrosting circuit.
    Advantageously, the thermal management system includes a fourth three-way valve arranged upstream of the inlet of the second heat exchanger and a fourth bypass pipe arranged between the fourth valve and the main pipe, downstream of the outlet of the second heat exchanger .
    The invention also provides an aircraft comprising at least one turbomachine according to one of the preceding variants.
    BRIEF DESCRIPTION OF THE DRAWINGS
    The characteristics of the invention mentioned above, as well as others, will appear more clearly on reading the following description of an exemplary embodiment, said description being made in relation to the accompanying drawings, among which:
    Fig. 1 is a schematic representation of an aircraft turbomachine equipped with a thermal management system according to the state of the art, FIG. 2 is a side view of an aircraft comprising a turbomachine according to the invention, FIG. 3 is a schematic representation of an aircraft turbomachine equipped with a thermal management system according to a first embodiment of the invention, FIG. 4 is a schematic representation of an aircraft turbomachine equipped with a thermal management system according to a second embodiment of the invention, and FIG. 5 is a schematic representation of a controller managing a thermal management system according to the invention.
    DETAILED DESCRIPTION OF EMBODIMENTS
    Fig. 2 shows an aircraft 200 fitted with a double-flow turbomachine 202 according to the invention.
    Fig. 3 shows a turbomachine 30 equipped with a thermal management system 300 according to a first embodiment of the invention, and FIG. 4 shows a turbomachine 40 equipped with a thermal management system 400 according to a second embodiment of the invention. Each thermal management system 300, 400 is intended to manage the thermal distribution between the different fluids in the turbomachine 30, 40.
    The turbomachine 30, 40 comprises a nacelle 11 which forms at the front an air intake lip through which the air enters the turbomachine 30, 40. At the level of the air intake lip, the nacelle 11 is equipped with a defrost circuit 310, 410 of the air intake lip.
    The turbomachine 30, 40 comprises elements common with the turbomachine 1 of FIG. 1, in particular a blower 12, a set of compressors 14, a combustion chamber 16, a set of turbines 18, a supply line 55 for bringing the fuel to the combustion chamber 16, a transfer line 56 to ensure the circulation of hot oil from the compressor assembly 14 to the turbine assembly 18. These elements have the same references. The fan 12 generates an air flow in the turbomachine 30, 40 in a direction of movement 13 of the air in the turbomachine 30, 40.
    Among the elements common with the thermal management system 50 of the prior art, the thermal management system 300, 400 according to the invention comprises a first heat exchanger 51 which ensures a heat exchange between the fuel of the pipeline. supply 55 and the oil of the transfer line 56 in order to heat the fuel by the heat given off by the oil and to cool it.
    The thermal management system 300, 400 according to the invention comprises a loop 302, 402 in which a heat transfer fluid circulates.
    The loop 302, 402 comprises a main pipe 306, 406 and a pump 304, 404 intended to circulate the heat transfer fluid in the main pipe 306, 406.
    The main pipe 306, 406 is connected to the outlet of the pump 304, 404 and enters an inlet of a third heat exchanger 308, 408. At the outlet of the third heat exchanger 308, 408, the main pipe 306, 406 joins a inlet of the defrost circuit 310, 410. At the outlet of the defrost circuit 310, 410, the main pipe 306, 406 joins the inlet of the pump 304, 404.
    The third heat exchanger 308, 408 provides heat exchange between the heat transfer fluid of the main pipe 306, 406 and the oil of the transfer pipe 56 which leaves the first heat exchanger 51.
    Thus, the heat of the engine oil transported in the transfer line 56 which has not been dissipated in the fuel of the supply line 55 is transferred to the heat transfer fluid of the loop 302, 402 via the third heat exchanger 308, 408. The heat transfer fluid thus heated then joins the defrost circuit 310, 410 of the air intake lip, thus ensuring the defrost function and allowing the heat transfer fluid to cool.
    Such a thermal management system 300, 400 ensures the distribution of heat to the systems which need it and the heat is not transformed into another energy which makes it possible to get rid of the losses linked to the transformation as well as the masses of associated systems. The thermal management system 300, 400 minimizes the waste of outside air captured by the engine but not used for propulsive purposes by limiting the number of air / air or air / fluid exchangers whose sole objective is to remove calories which will be little or not valued and minimizes the levies on the engine and the anti-icing system used which very occasionally serves as a heat exchanger to regulate the temperature of the heat transfer fluid.
    To compensate for the loss of efficiency of the heat exchanger constituted by the defrost circuit 310, 410 of the air intake lip when the aircraft 200 is stationary or at very low speed, the thermal management system 300, 400 includes a fourth heat exchanger 312, 412 which is disposed on the main pipe 306, 406 between the outlet of the defrosting circuit 310, 410 and the inlet of the pump 304, 404.
    The fourth heat exchanger 312, 412 provides a heat exchange between the heat transfer fluid of the main pipe 306, 406 and the air of a first air pipe 314, 414 which takes air in the secondary flow of the turbomachine 30, 40 and rejects it outside or in the secondary flow.
    The thermal management system 300, 400 includes an air conditioning system 58 which draws air from the primary flow of the set of compressors 14 and to this end it comprises a first duct 59 which draws air at the level of the intermediate stage of the compressor assembly 14 and a second pipe 60 which draws air at the final stage of the compressor assembly 14. The first 59 and the second pipe 60 meet upstream d 'a second heat exchanger 52 and comes out of the second heat exchanger 52 to supply the air conditioning system with air from the cabin of the aircraft.
    In the first embodiment of the invention presented in FIG. 3, the second heat exchanger 52 provides heat exchange between, on the one hand, the air from the first 59 and from the second pipe 60 and, on the other hand, the air from a second air pipe 61 which takes air from the secondary flow of the turbomachine 20 and rejects it outside or in the secondary flow.
    In the second embodiment of the invention presented in FIG. 4, the second heat exchanger 52 provides a heat exchange between, on the one hand, the air from the first 59 and from the second pipe 60 and, on the other hand, the heat transfer fluid from the main pipe 406. The second exchanger thermal 52 is arranged on the main pipe 406 between the outlet of the third heat exchanger 408 and the inlet of the defrost circuit 410. The second heat exchanger 52 constitutes the pre-cooler of the air conditioning system system.
    In order to best manage the thermal management of the thermal management system
    300, 400, that is to say whether or not to use such an element present along the main pipe 306, 406, the thermal management system 300, 400 comprises bypass pipes which are hydraulically connected to the main pipe 306, 406 in parallel with said elements.
    At the intersection between a bypass line and the main line 306, 406, upstream of said element, is arranged a three-way valve controlled remotely.
    To this end, the thermal management system 300, 400 includes a controller 350, 450 which individually controls each three-way valve in opening or closing according to parameters of different sensors. The sensors are for example temperature sensors measuring the temperatures of the various fluids of the turbomachine 30, 40, or pressure sensors.
    Thus, the thermal management system 300, 400 allows dynamic and integrated heat management by avoiding heavy storage systems.
    Fig. 5 shows a controller 500 which comprises, connected by a communication bus 510: a processor 501 or CPU (“Central Processing Unit” in English), a random access memory RAM 502 (“Random Access Memory” in English), a ROM read only memory 503 (“Read Only Memory” in English), a storage unit such as a hard disk or a storage medium reader, such as an SD card reader 504 (“Secure Digital” in English), and at least a communication interface 505, allowing for example the controller 500 to communicate with the various three-way valves and the sensors.
    The processor is capable of executing instructions loaded in RAM from the ROM, an external memory (not shown), a storage medium (such as an SD card), or a network of communication. When the equipment is powered on, the processor is able to read and execute instructions from RAM.
    The thermal management system 300, 400 comprises at least one three-way valve and the following associated bypass line:
    for the first and the second embodiment of the invention:
    a first three-way valve 352, 452 arranged upstream from the inlet of the third heat exchanger 308, 408 and a first bypass line 353, 453 arranged between the first valve 352, 452 and the main line 306, 406, downstream of the outlet of the third heat exchanger 308, 408, and / or
    - a second three-way valve 354, 454 arranged upstream of the inlet of the defrosting circuit 310, 410 and a second bypass line 355, 455 arranged between the second valve 354, 454 and the main line 306, 406, downstream from the defrost circuit outlet 310, 410, and / or when the fourth heat exchanger 312, 412 is present:
    - a third three-way valve 356, 456 arranged upstream of the inlet of the fourth heat exchanger 312, 412 and a third bypass line 357, 457 arranged between the third valve 356, 456 and the main line 306, 406, downstream of the outlet of the fourth heat exchanger 312, 412, and / or for the second embodiment of the invention:
    - A fourth three-way valve 458 arranged upstream of the inlet of the second heat exchanger 52 and a fourth bypass line 459 arranged between the fourth valve 458 and the main line 406, downstream of the outlet of the second heat exchanger 52.
    An example of operation is described below.
    The heat source here is provided by engine oil which is used to lubricate the engine bearings and the gearbox.
    The engine oil temperature should be regulated around 100 ° C at the engine inlet. The heat is extracted from the engine oil by the first heat exchanger 51 between the oil and the fuel. This first heat exchanger 51 is operated as long as the output fuel does not exceed a certain temperature, around 150 ° C. The excess residual heat is extracted from the engine oil by the third heat exchanger 308, 408 between the oil and the heat transfer fluid.
    The heat transfer fluid thus heated returns all or part of its heat to the air intake lip to ensure anti-icing.
    The heat exchangers are, for example, of the compact plate / fin or surface exchanger type.
    In the second embodiment of the invention, the pre-cooler 52 of the air conditioning system 58 has been integrated into the loop 402, but it is possible to integrate heat exchangers from other systems of the aircraft. 200, such as, for example, electric generators.
    It is also possible to control by the loop 302, 402, the temperature of the hydraulic fluid leaving the pump by adding a hydraulic fluid / heat transfer fluid exchanger of the loop 302, 402.
    The turbine casings can also be regulated by this loop 302,
    402 by circulating it around the casings.
    ίο
    The temperature regulation of systems such as air sampling valves can also be done by the loop 302, 402.
    The interest is maximized when all the heat and cold sources of the propulsion unit are connected by the loop 302, 402.
    It is also possible to integrate into the loop 302, 402, the cooling of the oil of electric generators which is currently cooled by a compact exchanger or a surface exchanger whose cold source is the air from the flow of the combined blower or not with compact exchangers placed on the engine oil and / or fuel circuits.
    It is also possible to control by this same loop, the temperature of the hydraulic fluid by adding a hydraulic fluid / heat transfer fluid exchanger of the fluid loop.
    The temperature regulation of the casings (low pressure and high pressure) of the turbine assembly can also be ensured by the loop by circulating the main pipe 306, 406 around the casings.
    The temperature regulation of systems such as air sampling valves can also be done by the loop.
    The interest is maximized when all the heat and cold sources of the propulsion unit are connected by the fluid loop.
    权利要求:
    Claims (7)
    [1" id="c-fr-0001]
    1) Double-flow turbomachine (30, 40) of an aircraft (200) comprising a nacelle (11) forming an air intake lip, a set of compressors (14), a
    5 combustion chamber (16), a set of turbines (18), a supply line (55) supplying fuel to the combustion chamber (16), a transfer line (56) ensuring the circulation of oil from the compressor assembly (14) to the turbine assembly (18), a defrosting circuit (310, 410) of the air intake lip, and a thermal management system (300, 400) comprising:
    10 - a first heat exchanger (51) ensuring a heat exchange between the fuel of the supply line (55) and the oil of the transfer line (56),
    - A loop (302, 402) comprising a main pipe (306, 406) and a pump (304, 404) intended to circulate a heat transfer fluid in the
    15 main line (306, 406), where the main line (306, 406) is connected to the outlet of the pump (304, 404) and enters an inlet of a third heat exchanger (308, 408), where in outlet of the third heat exchanger (308, 408), the main pipe (306, 406) joins an inlet of the defrosting circuit (310, 410), where at the outlet of the defrosting circuit (310, 410), the main pipe
    20 (306, 406) joins the inlet of the pump (304, 404), and where the third heat exchanger (308, 408) provides a heat exchange between the heat transfer fluid of the main pipe (306, 406) and the oil from the transfer line (56) coming out of the first heat exchanger (51).
    [2" id="c-fr-0002]
    2) Turbomachine (30, 40) according to claim 1, characterized in that the
    25 thermal management system (300, 400) includes:
    a first three-way valve (352, 452) arranged upstream of the inlet of the third heat exchanger (308, 408) and a first bypass pipe (353, 453) arranged between the first valve (352, 452) and the main pipe (306, 406), downstream of the outlet of the third heat exchanger (308, 408), and / or
    30 - a second three-way valve (354, 454) arranged upstream of the inlet of the defrosting circuit (310, 410) and a second bypass pipe (355, 455) arranged between the second valve (354, 454) and the main pipe (306, 406), downstream from the outlet of the defrosting circuit (310, 410).
    [3" id="c-fr-0003]
    3) Turbomachine (30, 40) according to one of claims 1 or 2, characterized in that the thermal management system (300, 400) comprises a fourth heat exchanger (312, 412) disposed on the main pipe (306, 406) between the outlet of the defrosting circuit (310, 410) and the inlet of the pump (304, 404), and in that the
    5 fourth heat exchanger (312, 412) provides a heat exchange between the heat transfer fluid of the main pipe (306, 406) and the air of a first air pipe (314, 414) which takes air in the secondary flow of the turbomachine (30, 40) and rejects it outside or in the secondary flow.
    [4" id="c-fr-0004]
    4) Turbomachine (30, 40) according to claim 3, characterized in that the
    10 thermal management system (300, 400) comprises a third three-way valve (356, 456) arranged upstream of the inlet of the fourth heat exchanger (312, 412) and a third bypass pipe (357, 457) arranged between the third valve (356, 456) and the main pipe (306, 406), downstream of the outlet of the fourth heat exchanger (312, 412).
    15
    [5" id="c-fr-0005]
    5) Turbomachine (40) according to one of claims 1 to 4, characterized in that the thermal management system (400) comprises an air conditioning system (58) which takes air from the primary flow of l '' set of compressors (14) through a first (59) and a second pipe (60) which supply an air conditioning system of the aircraft air, a second heat exchanger (52) ensuring a
    20 heat exchange, on the one hand, between the air of the first (59) and the second pipe (60) and, on the other hand, the heat transfer fluid of the main pipe (406), and in that the second heat exchanger (52) is disposed on the main pipe (406) between the outlet of the third heat exchanger (408) and the inlet of the defrosting circuit (410).
    25
    [6" id="c-fr-0006]
    6) A turbomachine (40) according to claim 5, characterized in that the thermal management system (400) comprises a fourth three-way valve (458) arranged upstream of the inlet of the second heat exchanger (52) and a fourth bypass line (459) arranged between the fourth valve (458) and the main line (406), downstream of the outlet of the second heat exchanger
    30 (52).
    [7" id="c-fr-0007]
    7) Aircraft (200) comprising at least one turbomachine (202) according to one of the preceding claims.
    PL. 1/2
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    同族专利:
    公开号 | 公开日
    US20180038280A1|2018-02-08|
    FR3054856B1|2018-09-07|
    引用文献:
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    US20160114898A1|2014-10-27|2016-04-28|Snecma|Circuit for de-icing an air inlet lip of an aircraft propulsion assembly|EP3657001A1|2018-11-22|2020-05-27|Airbus Operations |Turbine engine provided with a system for de-icing of the air intake|
    WO2020201032A1|2019-04-03|2020-10-08|Safran Nacelles|System for cooling an aircraft turbojet engine|
    WO2020201034A1|2019-04-03|2020-10-08|Safran Nacelles|System for cooling an aircraft turbojet engine|FR2987602B1|2012-03-02|2014-02-28|Aircelle Sa|TURBOMOTEUR NACELLE EQUIPPED WITH A HEAT EXCHANGER|
    FR3002978B1|2013-03-07|2016-12-30|Aircelle Sa|NACELLE EQUIPPED WITH AN INTERMEDIATE EXCHANGER OIL COOLING CIRCUIT|
    JP6162827B2|2013-04-04|2017-07-12|エル・ピー・ケー・エフ・レーザー・ウント・エレクトロニクス・アクチエンゲゼルシヤフト|Method and apparatus for separating substrates|
    GB201415078D0|2014-08-26|2014-10-08|Rolls Royce Plc|Gas turbine engine anti-icing system|
    EP3018304B1|2014-11-06|2020-10-14|United Technologies Corporation|Thermal management system for a gas turbine engine|
    US9759094B2|2015-06-24|2017-09-12|General Electric Company|Pump for a turbine engine|
    US10260419B2|2015-07-31|2019-04-16|General Electric Company|Cooling system|
    US20170159564A1|2015-12-08|2017-06-08|General Electric Company|Thermal management system|FR3007738B1|2013-06-28|2015-07-31|Aircelle Sa|DEFROSTING AND PACKAGING DEVICE FOR AIRCRAFT|
    US10364750B2|2017-10-30|2019-07-30|General Electric Company|Thermal management system|
    US11156162B2|2018-05-23|2021-10-26|General Electric Company|Fluid manifold damper for gas turbine engine|
    US11255264B2|2020-02-25|2022-02-22|General Electric Company|Frame for a heat engine|
    法律状态:
    2017-08-22| PLFP| Fee payment|Year of fee payment: 2 |
    2018-02-09| PLSC| Publication of the preliminary search report|Effective date: 20180209 |
    2018-08-27| PLFP| Fee payment|Year of fee payment: 3 |
    2019-08-22| PLFP| Fee payment|Year of fee payment: 4 |
    2020-08-21| PLFP| Fee payment|Year of fee payment: 5 |
    2021-08-19| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1657541A|FR3054856B1|2016-08-03|2016-08-03|TURBOMACHINE COMPRISING A THERMAL MANAGEMENT SYSTEM|FR1657541A| FR3054856B1|2016-08-03|2016-08-03|TURBOMACHINE COMPRISING A THERMAL MANAGEMENT SYSTEM|
    US15/667,873| US20180038280A1|2016-08-03|2017-08-03|Turbomachine comprising a heat management system|
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