• 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 (10), comprising: - a device (62) for discharging a compressor (56), in particular a high-pressure compressor, comprising at least one valve (66) for discharging said compressor (56), one of which outlet is connected to a discharge circuit (68) capable of evacuating a flow of discharge air, and - a device (50) for cooling at least one member (18), comprising a heat exchanger (32) of which an air outlet is connected to an ejector (46) of the jet jet type, which comprises a duct (48) for the passage of a secondary air stream coming from said air outlet and a nozzle (52). ) spraying a primary air flow inside said passage duct (48), characterized in that the nozzle (52) is connected to said discharge circuit (68).
    公开号:FR3028888A1
    申请号:FR1461416
    申请日:2014-11-25
    公开日:2016-05-27
    发明作者:Benissa Boujida；Daniel Bernava；Dominik Igel；Maxime Rotenberg
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] The invention relates to the field of turbomachines and, in particular, to turboprop engines, but also to high-power turbofan engines, such as those used in civil aviation and equipped with a turbomachine. a member in which circulates a lubricating oil to be cooled according to certain operating phases. This member is for example a speed reducer.
    [0002] To increase their performance, while reducing noise and fuel consumption, turbomachines, such as turboprops, must have large-diameter, low-speed "multi-blade" type propellers. However, the power transmitted to the propeller rotating at low speed, by the gas generator rotating at high speed, by means of a mechanical speed reducer, generates a large amount of heat due to mechanical losses, that is to say say rubbing. It will be understood that this heat must be evacuated or dissipated in an efficient manner, in order to avoid rapidly degrading the mechanical parts of the gearbox, such as the gears and the bearings, or to degrade the qualities of the lubricant of the gearbox, on pain of noting the fall of the efficiency of the turbomachine. However, even with a yield close to or slightly higher than 99%, the speed reducer of a turbine engine with a mechanical power of 10,000 kW releases, despite everything, a thermal power close to 100 kW due to mechanical losses. It is well known, in the field of the prior art, to evacuate this type of heat, that is to say to dissipate such a thermal power, by circulating the lubricant of the speed reducer, in a closed circuit, by means of a pump or a thermosiphon, in a radiator, such as an oil radiator or an air / oil heat exchanger, for example an exchanger known as ACOC, "air cooled / oil cooler ".
    [0003] It is known to propose a turboprop comprising a scoop in which is disposed an exchanger in which the lubricant circulates. In such a turboprop, the moving air passing through the exchanger discharges heat to the outside of the scoop and the cooled lubricant returns to the speed reducer through the cooling circuit. A flap may optionally be located at the inlet or outlet of the scoop for regulating the air flow through the exchanger, in order to regulate the temperature of the lubricant, for example for turboprop operation phases according to which the radiator is oversized with respect to the thermal power it must evacuate. For low aircraft speeds, however, and for which the turboprop is in operation, the flow of air through the exchanger may be insufficient. To remedy this drawback, it is known to propose a turboprop engine comprising a cooling device comprising an exchanger, an air outlet of which is connected to a jet jet ejector. Such ejector comprises a duct for passage of a secondary air stream coming from the exchanger comprising at least one spray nozzle of a primary air stream coming from a turboprop compressor, intended to accelerate the flow of air. secondary air by a venturi effect. Downstream of the nozzle, a first section of reduced section forms a mixer and a second section, of larger section, forms a diffuser. More particularly, it has been proposed, in the published document FR-2.788.308-A1, a turboprop engine of the type described above, comprising a flap mounted downstream of the duct of the ejector, which notably allows the regulation of the air flow. . The spraying nozzle is generally supplied by a tapping, or sampling line, carried out on a turboprop compressor, selectively, by a valve which makes it possible to circulate the flow of air thus taken as a function of the supply requirements. of the nozzle.
    [0004] Typically, the jet pump is used to overcome an insufficient secondary air flow through the heat exchanger, which configuration generally occurs for reduced air flow velocities through the exchanger, for example when the aircraft that is equipped with the turbomachine rolls at low speed or is stopped waiting for take-off. Moreover, most turbomachines comprise discharge devices which are intended to prevent pumping phenomena in the compressors of these turbomachines and in particular in high pressure compressors.
    [0005] Indeed, in a turbomachine, air is directed through several compressor stages to a combustion chamber. As the air passes through the successive compressor stages, the air pressure increases. Under certain conditions, for example when the engine is operating at reduced speeds, a pumping phenomenon may occur. Pumping is a fundamental cyclical phenomenon specific to dynamic compressors. Indeed, in a compressor, the compression is obtained by energy exchange in the gas set in motion in rows of fins. Like an aircraft wing which, under high incidence and at reduced speed loses its lift and "picks up", a compressor can stall. At a reduced flow rate, the compressor no longer makes it possible to push the flow of air. Since the compressor forms the interface of two networks at different pressures, namely respectively a suction network and a discharge network, in the event of a stall, the capacity of the delivery network, which has the highest pressure, is capable of emptying into the capacity of the suction network by a flow against the current in the compressor. When the discharge network has sufficiently emptied in the suction, the compressor finds new operating conditions enabling it to restore the flow in the right direction, until a new cycle of instability recommences.
    [0006] 3028888 4 These large cyclical flow fluctuations, called pumping, are like a series of shocks whose mechanical consequences can be disastrous, and cause, for example, breaks in fins, or radial vibrations of very large size. level, with destruction of the internal sealing devices on the centrifugal compressors. Current turbomachines therefore comprise devices for discharging their compressors. A discharge device essentially comprises a tapping or sampling duct, carried out at the outlet of the compressor, which makes it possible, for reduced flow rates, to reduce the pressure downstream of the compressor in order to avoid back-ups and consequently avoid pumping phenomena. The air taken from the compressor can be discharged into different devices inside or outside the internal flow of a gas stream of the turbomachine.
    [0007] A turbomachine having a discharge device and a cooling device of the type described above may therefore comprise two taps or sampling ducts made on the same compressor, and both intended to feed the cooling and discharge devices under similar conditions. that is, when the turbomachine is operating at a reduced rotational speed. This design has the disadvantage of multiplying the nozzles or sampling ducts on the compressor, or the corresponding valves. The invention overcomes this drawback by proposing a turbomachine equipped with an at least partially common feed of these devices. For this purpose, the invention proposes a turbomachine comprising a device for discharging a compressor, in particular a high-pressure compressor, comprising at least one discharge valve of said compressor, an outlet of which is connected to a discharge circuit capable of evacuating a discharge air stream, and a cooling device of at least one member, comprising a heat exchanger, an air outlet of which is connected to a jet-type ejector, which comprises a passage duct, a secondary air stream coming from said air outlet and a spray nozzle of a primary air flow inside said passage duct, the spraying of which is likely to be selectively authorized or interrupted by means of an ejector valve, and which is advantageously characterized in that the nozzle is connected to said discharge circuit. According to other features of the invention: the discharge circuit of the compressor comprises at least one outlet intended to evacuate the flow of discharge air inside an internal flow vein of the gases of the turbomachine the discharge circuit of the compressor comprises at least one outlet intended to evacuate the flow of discharge air to the outside of an internal flow passage of the gases of the turbomachine, the discharge circuit comprises at least an outlet for discharging the discharge air flow outside the turbomachine, - the compressor discharge circuit comprises a single output consisting of the spray nozzle, - the spraying of the primary air flow in the nozzle is allowed or interrupted only by the discharge valve, - the exchanger is an air / oil exchanger for cooling the lubricating oil of the body of the turbomachine. The invention also relates to a method for controlling a cooling device of at least one member of a turbomachine, comprising a heat exchanger, an air outlet of which is connected to a jet jet ejector which comprises a duct for passage of a secondary air flow from said air outlet and a spray nozzle of a primary air flow inside said passage duct. This method is characterized in that it comprises at least one stage 30 for supplying the spray nozzle during which the spray nozzle is supplied with a discharge air stream coming from a discharge circuit 3028888 6 a compressor of the turbomachine, and at least one step of cutting off the supply of the spray nozzle. According to another characteristic of the method, the supply step corresponds to a low-power operation of the turbomachine, in particular operation at an idle speed, during which a discharge valve, an output of which is connected to the circuit of discharge, is open, and the step of supplying power to the spray nozzle corresponds to operation at nominal or maximum power, during which the discharge valve is closed.
    [0008] The invention will be better understood and other details, features and advantages of the present invention will emerge more clearly on reading the following description given by way of nonlimiting example and with reference to the appended drawings, in which: Figure 1 is a sectional view of a turboprop engine according to a prior art; FIG. 2 is a schematic view of a turbomachine according to a prior state of the art; FIG. 3 is a schematic view of a preferred embodiment of a turbomachine made according to the invention; FIG. 4 is a sectional view of a turboprop engine according to a first embodiment of the invention; - Figure 5 is a sectional view of a turboprop engine according to a second embodiment of the invention; and FIG. 6 is a sectional view of a turboprop according to a third embodiment of the invention. In the following description, like reference numerals designate like parts or having similar functions. FIG. 1 shows the main elements of a turbomachine 10 installed in a nacelle 11 under the wing 12 of an aircraft.
    [0009] In this case, the turbomachine 10 is a turboprop, but this configuration is in no way limitative of the invention. In the upstream part thereof there is a propeller 14 driven in rotation by a turbine 16, via a speed reducer 18.
    [0010] The turbine 16 receives the combustion gases from a combustion chamber which is supplied with air by an internal air circulation 20 whose input is via an inlet sleeve 22, which is placed immediately downstream of the combustion chamber. the propeller 14 at the beginning of an upstream cover 24 of the nacelle 11 of the turboprop 10. The flow of the gases passing through the turboprop 10 has been represented by arrows "G". The gearbox 18 is fed with lubricant by a lubrication circuit 26 which essentially comprises pipes 28, a pump 30, and a heat exchanger 32 intended to allow the cooling of the lubricant circulating in the speed reducer 18.
    [0011] The exchanger 32 is part of a cooling device 50, which extends over the entire longitudinal dimension of the turboprop. The cooling air of the exchanger 32 is taken downstream of the inlet sleeve 22. For this purpose, an air intake slot 34 is used, placed on the internal air circulation 20 of the turbomachine. downstream of the inlet sleeve 22, to supply an air supply line 36 which supplies fresh air to the exchanger 32, housed in a central portion 38 of the cooling device 50, enlarged for the purpose of receiving the Exchanger 32. The cooling device 50 is completed by a discharge pipe 40 placed downstream of the central portion 38 to prolong the flow of air in the exchanger 32 and to evacuate the air into the environment. 60. The flow rate through the cooling device 50 can moreover be regulated by a flap 44 placed in the exhaust pipe 40. In such a turboprop 10, the operation of the cooling device is linked to the operating conditions of the turboprop. 10.
    [0012] Thus, in high-speed flight at cruising speed, during a long flight, for example, or in very cold weather, the air entering the air intake slot 34, driving through the duct By means of the feedthrough 36 through the exchanger 32 and discharged through the discharge line 40, the exchanger 32 and the lubricant passing therethrough are generally sufficiently cooled. Under certain conditions, it may be necessary to modulate the flow of air in the cooling device 50 by means of the flap 44 to prevent too much cooling of the lubricant, which would then penalize the operation of the gearbox 18. The flap 44 can be 10 advantageously controlled by the device for automatically regulating the operation of the turboprop 10 which is preferably of the type: "full redundant authority", that is to say of the "FADEC" type (Full Authority Digital Engine Control) and which is actuated by electric, electromechanical, hydraulic or electrohydraulic known means such as a cylinder 15 (not shown). On the other hand, at low speed, or under conditions in which the flow of air naturally arriving at the air supply duct 36 is insufficient, for example when waiting in the car park, for an idling circulation at As a result of the ground or hot running, it is useful to accelerate the flow of air through the cooling device 50. For this purpose, the cooling circuit 50 comprises, downstream of the exchanger 32 and upstream of the discharge pipe 40, an ejector 46 jet jet type.
    [0013] As illustrated in FIG. 1, such an ejector 46 essentially comprises a duct 48 for passing a secondary air stream coming from the radiator 32 and at least one spray nozzle 52 for an air flow. primary inside said conduit 48, for accelerating the flow of air by a venturi effect.
    [0014] As illustrated in FIG. 1, the nozzle 52 is supplied with primary air via a sampling duct 54 connected to the compressor 56 of the turboprop 10, and the circulation of air within this sampling duct 54 can be authorized. or interrupted by an ejector valve 58. The primary air injection allows, by venturi effect, to accelerate the secondary air flow and therefore when it is required to increase the flow rate through the exchanger 32, resulting in better cooling. The schematic configuration of such a cooling device 50 has also been partly and schematically represented in FIG. 2 in a more general manner, said cooling device 50 being applicable to any turbomachine comprising an exchanger 32 dedicated to the cooling of an organ, and not specifically to a turbine engine comprising an exchanger 32 dedicated to the cooling of a gearbox 18.
    [0015] With reference to FIG. 1, the turboprop engine 10 also comprises, in a conventional manner, a discharge device 62 intended to prevent the pumping phenomena within the compressor 56. The device 62 successively comprises a tapping 64 or sampling duct connected to the compressor 56 , and a discharge valve 20 of said compressor, an output of which is connected to a discharge circuit 68 able to evacuate a flow of discharge air. The discharge valve 66 is better known as the HBV valve or "Handling Bleed Valve". In FIG. 1, there is shown a discharge circuit 68 consisting of a scoop 74 which makes it possible to evacuate the air discharged from the compressor 56 directly into the ambient medium, but it will be understood that the discharge circuit 68 can take other configurations, as will be seen later with reference to different variants of the invention. In this configuration, it can be clearly seen in FIG. 1 as in FIG. 2, that a turbomachine, such as the turboprop engine 10, equipped with a cooling device 50 and a discharge device comprises two sampling lines. 54 and 64 and two valves, namely an ejector valve 58 and a discharge valve 66. However, these valves 58, 66 are controlled in opening under the same operating conditions of the turbomachine, that is to say for reduced speeds of rotation of the turbomachine and at low speed, firstly in the context of the discharge device 62 to prevent pumping phenomena within the compressor 56, and secondly within the scope of the device cooling to increase the flow in the exchanger. The redundancy of at least the sampling ducts 54 and 64 10 penalizes the onboard weight of the turbomachine and increases its complexity. The invention overcomes this disadvantage by proposing a turbomachine 10 of the type described above, characterized in that, as shown schematically in FIG. 3, the nozzle 52 of the cooling device 50 is connected to the discharge circuit 68 of the 62 This configuration has been shown for the turboprop 10 of FIGS. 4 to 6. This configuration advantageously makes it possible to supply the nozzle 52 of the cooling device 50 with the aid of the discharge circuit 68 without using a conduit of FIG. Specific sampling of the type of sampling duct 54 which had been shown with reference to Figure 2, and therefore without requiring additional tapping on the compressor housing 56. This configuration therefore reduces the number of ducts used in the turbomachine 10.
    [0016] Another particularly novel feature of the invention is that, as shown in FIG. 3, the spraying of the primary air stream into the nozzle 52 is allowed or interrupted only by the discharge valve 66. The discharge valve 66 acts as ejector valve.
    [0017] Indeed, the discharge valve 66 being controlled in opening precisely according to the operating conditions of the turbomachine which are also required for the supply of the cooling device 50, said cooling device 50 can therefore be fed directly by the discharge valve 66 via the discharge circuit 68. This configuration thus makes it possible to reduce the number of valves used in the turbomachine 10, that is to say for reduced speeds of rotation of the turbomachine and at low speed . As previously mentioned, the discharge circuit 68 may take different configurations, and the nozzle 52 may be connected to this discharge circuit 68 in any configuration.
    [0018] For example, as illustrated in FIG. 4, which represents a first embodiment of the invention, the discharge circuit 68 may comprise at least one outlet 70 intended to evacuate the flow of discharge air inside the outlet. the internal flow of the turbo-propeller gases 10, for example in a nozzle 72. The cooling device 50 comprises a bypass 55 connected to the discharge circuit 68 to enable the nozzle 52 to be powered. The compressor discharge circuit 68 may also comprise at least one outlet intended to evacuate the air taken outside the internal flow of the turbo-propeller gas 10. Again, the cooling device 50 comprises a bypass 55 connected to the discharge circuit 68 to allow For example, as shown in FIG. 5, which represents a second embodiment of the invention, the discharge circuit 68 may include an outlet intended to evacuate the nozzle. discharge air flow directly to the outside of the turboprop 10, that is to say in the ambient medium 60 via a scoop 74 similar to that which has been previously shown in FIG. reference to the state of the art. In this case, the cooling device 50 also includes a bypass 55 connected to the discharge circuit 68 so as to supply the nozzle 52, 30 and this branch is for example located in the scoop 74.
    [0019] Finally, according to a third embodiment of the invention which has been shown in FIG. 6, the compressor discharge circuit could comprise a single output consisting of the spray nozzle 52. In this case, the cooling device 50 does not have a bypass, because the discharge circuit 68 previously mentioned is purely and simply replaced by the spray nozzle 52. This solution considerably simplifies the discharge circuit 68 but nevertheless requires a calculation. rigorous design of the nozzle 52 and the flow rate through the discharge valve 66, so that the flow is not too high and may not cause too much cooling of the exchanger 32. Indeed, d ' generally, in the preferred embodiment of the invention, the exchanger 32 is an air / oil exchanger for cooling the lubricating oil of an organ of the turbomachine.
    [0020] For example, in the case of a turboprop 10 of the type shown in FIGS. 4 to 6, the member is a reducer similar to the gear reducer 18 of FIG. 1. Excessive cooling of the circulating oil in the exchanger 32 could penalize the efficiency of this reducer 18.
    [0021] Thus, the invention proposes a method of controlling a cooling device 50 of at least one member 18 of a turbomachine, comprising a heat exchanger 32, an air outlet of which is connected to an ejector 46 of the type jet tube which comprises a duct 48 for passage of a secondary air flow coming from said air outlet and a nozzle 52 for spraying a primary air flow inside said passage duct 48, which comprises at least one step of supplying the spray nozzle 52 during which the spray nozzle 52 is fed with a discharge air stream coming from the discharge circuit 68 of a compressor of the turbomachine. This supply step corresponds to a low power operation of the turbomachine 10, including idle speed operation, during which the discharge valve 66, whose output is connected to the discharge circuit 68, is opened. It will be understood that since the use of the jet pump is no longer required to improve the cooling of the exchanger, the method 5 determines a step of cutting off the supply of the spray nozzle 52. This step of supplying power to the spray nozzle 52 corresponds to operation at nominal or maximum power, during which the discharge valve 66 is closed. The invention therefore makes it possible to share the same compressed air supply 10 in favor of the discharge circuit 68 and the cooling device 50, and also to share the control of this supply by the use of a common discharge valve 66. which makes it possible to usefully reduce the weight of the turbomachine 10. 15
    权利要求:
    Claims (9)
    [0001]
    REVENDICATIONS1. Turbomachine (10), comprising: - a device (62) for discharging a compressor (56), in particular at high pressure, comprising at least one valve (66) for discharging said compressor (56), an output of which is connected to a discharge circuit (68) capable of evacuating a flow of discharge air, and - a device (50) for cooling at least one member (18), comprising a heat exchanger (32) whose output of air is connected to a jet jet ejector (46) which includes a duct (48) for passing a secondary air stream from said air outlet and a spray nozzle (52). a primary air flow inside said passage duct (48), characterized in that the nozzle (52) is connected to said discharge circuit (68).
    [0002]
    2. Turbine engine (10) according to claim 1, characterized in that the discharge circuit (68) of the compressor (56) comprises at least one outlet intended to evacuate the flow of discharge air inside a vein internal flow (G) of the turbomachine gases. 20
    [0003]
    3. The turbomachine (10) according to claim 1, characterized in that the discharge circuit (68) of the compressor (56) comprises at least one outlet intended to evacuate the flow of discharge air outside a vein. internal flow (G) of the turbomachine gases.
    [0004]
    4. A turbomachine (10) according to claim 3, characterized in that the discharge circuit (68) comprises at least one outlet for discharging the discharge air stream outside the turbomachine (10).
    [0005]
    5. The turbomachine (10) according to claim 1, characterized in that the discharge circuit (68) of the compressor (56) comprises a single output consisting of the nozzle (52) spray. 3028888 15
    [0006]
    6. Turbomachine (10) according to one of the preceding claims, characterized in that the spraying of the primary air flow in the nozzle is allowed or interrupted only by the discharge valve (66).
    [0007]
    7. Turbomachine (10) according to one of the preceding claims, characterized in that the exchanger (32) is an air / oil exchanger for cooling the lubricating oil of the member (18) of the turbomachine.
    [0008]
    8. A method for controlling a device (50) for cooling at least one member (18) of a turbomachine (10), comprising a heat exchanger (32) of which an air outlet is connected to an ejector Jet jet type (46) comprising a conduit (48) for passing a secondary air stream coming from said air outlet and a nozzle (52) for spraying a primary air flow inside said passage duct (48), characterized in that it comprises at least one step of supplying the spray nozzle (52) during which the spray nozzle (52) is fed with a flow discharge air from a discharge circuit (68) of a compressor (56) of the turbomachine (10), and at least one step of supplying the spray nozzle (52).
    [0009]
    9. Control method according to the preceding claim, characterized in that the supply step corresponds to a low power operation of the turbomachine (10), including operation at an idle speed, during which a valve (66) ), of which an output is connected to the discharge circuit (68), is open, and in that the step of disconnecting the supply of the spray nozzle (52) corresponds to operation at nominal or maximum power, during which the discharge valve (66) is closed.
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    同族专利:
    公开号 | 公开日
    RU2017119667A|2018-12-26|
    RU2017119667A3|2019-06-20|
    US10883422B2|2021-01-05|
    FR3028888B1|2016-12-09|
    RU2753738C2|2021-08-23|
    EP3224462B1|2020-08-26|
    CA2968481A1|2016-06-02|
    BR112017010675A2|2018-02-14|
    CN107002560A|2017-08-01|
    US20170335769A1|2017-11-23|
    EP3224462A1|2017-10-04|
    WO2016083732A1|2016-06-02|
    CN107002560B|2020-03-17|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP0511770A1|1991-04-22|1992-11-04|General Electric Company|Heat exchanger system|
    EP1018468A1|1999-01-07|2000-07-12|Snecma Moteurs|Cooling device for a turbomachine reduction gear|
    US8261527B1|2012-01-31|2012-09-11|United Technologies Corporation|Gas turbine engine with geared turbofan and oil thermal management system with unique heat exchanger structure|WO2020049262A1|2018-09-06|2020-03-12|Liebherr-Aerospace Toulouse Sas|Device for cooling heat-sensitive control members of a pneumatic or electropneumatic valve, and valve equipped with such a cooling device|
    RU2753385C1|2018-06-18|2021-08-13|НУОВО ПИНЬОНЕ ТЕКНОЛОДЖИ - С.р.л.|Ventilation system for bearing oil cavity|SU1804042A1|1991-03-28|1994-01-15|Киевский механический завод им.О.К.Антонова|Engine heat exchanger cooling system|
    US8966875B2|2011-10-21|2015-03-03|United Technologies Corporation|Constant speed transmission for gas turbine engine|
    EP2981697B1|2013-01-21|2019-10-02|United Technologies Corporation|Air oil cooler airflow augmentation system and corresponding method|
    FR2986275B1|2012-02-01|2016-07-01|Turbomeca|GAS TURBINE EXHAUST GAS EJECTION METHOD AND OPTIMIZED CONFIGURATION EXHAUST ASSEMBLY|US9879591B2|2015-02-20|2018-01-30|Pratt & Whitney Canada Corp.|Engine intake assembly with selector valve|
    US10087777B2|2016-04-29|2018-10-02|Hamilton Sundstrand Corporation|Lubricant cooling systems for high speed turbomachines|
    US20180372210A1|2017-06-26|2018-12-27|Bell Helicopter Textron Inc.|Safety Bypass Valve|
    US10774874B2|2018-08-06|2020-09-15|General Electric Company|Fluid bearing assembly|
    US11028775B2|2018-08-23|2021-06-08|The Boeing Company|Bleed air boosted engine oil cooler|
    US11078837B2|2019-02-06|2021-08-03|Raytheon Technologies Corporation|Engine bleed air ducting into heat exchanger|
    CA3132276A1|2019-03-01|2020-09-10|Pratt & Whitney Canada Corp.|Cooling system configurations for an aircraft having hybrid-electric propulsion system|
    法律状态:
    2015-11-16| PLFP| Fee payment|Year of fee payment: 2 |
    2016-05-27| PLSC| Publication of the preliminary search report|Effective date: 20160527 |
    2016-11-09| PLFP| Fee payment|Year of fee payment: 3 |
    2017-10-20| PLFP| Fee payment|Year of fee payment: 4 |
    2017-11-10| CD| Change of name or company name|Owner name: SNECMA, FR Effective date: 20170713 |
    2018-10-24| PLFP| Fee payment|Year of fee payment: 5 |
    2019-10-22| PLFP| Fee payment|Year of fee payment: 6 |
    2020-10-21| PLFP| Fee payment|Year of fee payment: 7 |
    2021-10-20| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1461416A|FR3028888B1|2014-11-25|2014-11-25|COOLING DEVICE FOR A TURBOMACHINE SUPPLIED BY A DISCHARGE CIRCUIT|FR1461416A| FR3028888B1|2014-11-25|2014-11-25|COOLING DEVICE FOR A TURBOMACHINE SUPPLIED BY A DISCHARGE CIRCUIT|
    RU2017119667A| RU2753738C2|2014-11-25|2015-11-24|Cooling device for turbomachine provided with unloading circuit|
    US15/528,474| US10883422B2|2014-11-25|2015-11-24|Cooling device for a turbomachine supplied by a discharge circuit|
    CA2968481A| CA2968481A1|2014-11-25|2015-11-24|Cooling device for a turbomachine supplied by a discharge circuit|
    BR112017010675-2A| BR112017010675A2|2014-11-25|2015-11-24|cooling device for a turbocharger powered by a discharge circuit|
    PCT/FR2015/053200| WO2016083732A1|2014-11-25|2015-11-24|Cooling device for a turbomachine supplied by a discharge circuit|
    EP15812881.9A| EP3224462B1|2014-11-25|2015-11-24|Cooling device for a turbomachine supplied by a discharge circuit|
    CN201580066646.2A| CN107002560B|2014-11-25|2015-11-24|Cooling device for a turbomachine, supplied by a discharge circuit|
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