• 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 lubrication device for a turbomachine, comprising an oil supply line (23) equipped with an oil supply pump (24) and regulation means (25) located downstream of the engine. a supply pump (24), a supply line (26) for supplying oil to a member to be lubricated and a recycle line (27), the control means (25) for directing all or part of the flow rate of oil from the supply line (23) to the supply line (26) and / or the recycle line (27), the pump (24) being driven by at least one rotating member of a relay accessories of the turbomachine.
    公开号:FR3022300A1
    申请号:FR1455292
    申请日:2014-06-11
    公开日:2015-12-18
    发明作者:Jeremy Vielcanet；Caroline Frantz；David Simon
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to a lubricating device for a turbomachine, such as for example an aircraft turbomachine.
    [0002] The invention applies in particular to a "open rotor" type turbine engine, that is to say having an unsheathed fan. Such a turbomachine, known in particular from the patent application FR 2 940 247, conventionally comprises a high pressure body comprising a high pressure compressor and a high pressure turbine coupled in rotation by a first shaft, and an additional body comprising a low pressure compressor. and an intermediate pressure turbine, rotatably coupled by a second shaft. The turbomachine further comprises a power-free turbine forming a low-pressure turbine and comprising a first rotor (or inner rotor) and a second rotor (or outer rotor). The turbomachine also comprises a counter-rotating propeller system, namely respectively a first propeller and a second propeller driven by the low-pressure turbine via an epicyclic reduction gearbox. The propeller system also has a stator.
    [0003] More particularly, the epicyclic gear comprises a sun gear rotating about an axis, meshing with satellites around axes belonging to a planet carrier, the satellites meshing with a radially outer ring gear, itself carried by a crown shaft . The crown shaft is rotatably coupled to the second rotor. In addition, the sun gear shaft is rotatably coupled to the first rotor. In addition, the planet carrier shaft is rotatably coupled to the first propeller and the crown shaft is rotatably coupled to the second propeller. The turbomachine comprises an oil circuit ensuring, in particular, the lubrication, cooling of the epicyclic gearbox and bearings supporting the rotating parts. This circuit comprises an oil inlet pipe equipped with an oil supply pump and, if appropriate, regulating means located downstream of the supply pump, a supply pipe intended to supply oil with the oil. gearbox and a recycle line 5 opening upstream of the feed pump, the control means for directing all or part of the flow of oil from the supply line to the supply line and / or towards the recycling line. The pump, with fixed displacement, is rotated by a movable member of an accessory relay, located nearby, via a power shaft. Given the constraints of space, it is indeed relatively complicated to connect a power shaft (that is to say a shaft for transmitting a relatively large torque, for example between 90 and 900 Nm) to an organ mobile of the epicyclic gear 15 speed reducer. However, the rotational drive of such an oil supply pump can be performed only through a power shaft. It is recalled that an accessory relay or A.G.B. ("Accessory Gear Box" in English) comprises a housing containing a number of gears connected to equipment or accessories, such as for example an electric generator, a starter, an alternator, hydraulic pumps, fuel pumps, oil pumps , etc. In order to drive these different gears, part of the power of the turbomachine is taken from the high pressure body via a power take-off shaft. The rotational speeds of the various moving parts of the accessory relay are therefore directly dependent on the speed of rotation of the high pressure body of the turbomachine. On the other hand, the rotational speeds of the various moving parts of the epicyclic gear train are not directly dependent on the rotational speed of the high pressure body, but are directly dependent on the rotational speeds of the rotors of the low pressure turbine. The oil requirements of the epicyclic gear train are thus decoupled from the rotational speed of the high pressure body. The oil circuit, and in particular the pump, is sized to cover the maximum need for oil flow and thus supercharges the epicyclic gear train outside the operating point for which the pump has been dimensioned. This supercharging is combined with a limited capacity of oil evacuation due to the structure of the gearbox, especially at low rotational speeds (centrifugal oil discharge). There is therefore a risk of drowning the gearbox, which affects its operation, degrades its performance and its life, generates overheating and creates unbalance. The invention aims in particular to provide a simple, effective and economical solution to this problem. For this purpose, it proposes a lubrication device for a turbomachine, comprising an oil inlet pipe equipped with an oil supply pump and regulation means located downstream of the feed pump, a pipe supply unit for supplying oil to a member to be lubricated and an oil recycling line, the regulating means making it possible to direct all or part of the flow of oil from the inlet line to the supply line and / or to the recycling line, the pump being driven by at least one rotary member of an accessory relay of the turbomachine, characterized in that the regulating means comprise a controlled metering valve comprising an input connected to the pipe and an outlet connected to the supply line, the regulating means further comprising a regulating valve comprising an inlet connected to the inlet pipe and an outlet connected to the recycling line, the position of the control valve being controlled according to the oil pressures at the inlet and the outlet of the metering valve.
    [0004] Thus, according to the invention, the feed pump is driven by at least one rotary member of the accessory relay or A.G.B., for example via a power shaft. It will be noted that, in the case of A.G.B., the space constraints are less important than in the case of the gearbox. Also, it is possible to draw a large torque at A.G.B, via a power shaft, to drive the feed pump. Furthermore, it is possible to control the metering valve by means of a law taking into account, in particular, the speed of rotation of a particular element, such as, for example, the speed of rotation of a gear reducer element. or the low pressure turbine. This avoids under-feeding or over-supply of oil to the body to be lubricated, for example gear reducer. The control law of the metering valve can also take into account other parameters of the turbomachine (temperature, engine speed, power, torque, other engine parameters, ...).
    [0005] The regulating valve makes it possible to recycle the flow of oil, generated by the main pump, which is not necessary for the lubrication of the aforementioned member. According to one embodiment of the invention, the regulating valve may comprise a variable position piston whose position influences the flow of oil at the outlet of the regulating valve, said piston being capable of being subjected to a first pressure force generated by applying a first pressure in a first pressure chamber of the regulating valve and a second pressing force, opposite to the first pressing force, generated by applying a second pressure in a second pressure chamber of the regulating valve. In this case, the device may comprise a first tapping pipe connecting the inlet pipe or the inlet of the metering valve and the first pressure chamber, and a second tapping pipe connecting the supply pipe or the outlet. of the metering valve and the second pressure chamber.
    [0006] The control valve is thus controlled by the pressure difference between the outlet and the inlet of the metering valve. Furthermore, the regulating valve may comprise a return spring adapted to generate a return force on the piston, so as to maintain a constant pressure difference between the outlet and the inlet of the metering valve. In addition, the metering valve may comprise at least one metering slot and a movable member whose position is controlled, for example by means of a servovalve, and influences the oil flow at the outlet of the valve of dosage. In this way, the oil flow at the outlet of the metering valve is only dependent on the position in said metering valve. The latter is relatively easy to control. The driving law can then be established simply and reliably. This metering law then gives the flow rate at the outlet of the metering valve as a function of the position of said metering valve. In operation, the position of the regulating valve then adapts automatically to redirect part of the oil flow to the recycling line. The recycle line may open into the inlet line upstream of the feed pump. In a variant, the device comprises an oil recovery line capable of recovering oil from, for example, the member to be lubricated, said recovery line being equipped with a recovery pump, the recycling line opening into the recovery line, downstream of the recovery pump. The invention also relates to a turbomachine comprising a lubricating device of the aforementioned type, a first and a second counter-rotating propeller driven in rotation by means of a low pressure turbine, via a gear reducer, for example to train epicyclic, the supply line being intended to supply oil to the gear reducer.
    [0007] In this case, the turbomachine may comprise a high pressure body comprising a high pressure compressor and a high pressure turbine rotatably coupled by a first shaft, and an additional body comprising a low pressure compressor and an intermediate pressure turbine, rotatably coupled. by a second shaft, the rotational speed of the rotary member of the accessory relay being dependent (for example a multiple) of the rotational speed of the shaft of the high-pressure body. The invention will be better understood and other details, features and advantages of the invention will appear on reading the following description given by way of non-limiting example with reference to the accompanying drawings in which: - Figure 1 is a half longitudinal sectional view of a non-ducted fan turbomachine according to the invention, FIG. 2 is a detailed view of a part of FIG. 1, FIG. 3 is a schematic view of a lubrication device. according to the invention, - Figure 4 is a schematic view of a portion of a lubrication device according to the invention, - Figure 5 is a schematic view of a lubrication device according to an alternative embodiment of the invention. FIGS. 1 and 2 show a turbomachine 1 with a non-ducted fan, called an "open rotor". This comprises a high-pressure body comprising a high-pressure compressor 2 and a high-pressure turbine 3 rotatably coupled by a first shaft 4, and an additional body comprising a low-pressure compressor 5 and an intermediate pressure turbine 6, which are coupled together. rotation by a second shaft 7. A combustion chamber 8 is located between the high-pressure compressor 2 and the high-pressure turbine 3.
    [0008] The turbomachine 1 further comprises a free power turbine 9, forming a low-pressure turbine and comprising a first rotor 10 (or inner rotor) and a second rotor 11 (or outer rotor), visible in FIG. 2. The turbomachine 1 comprises also a counter-rotating propeller system, namely respectively a first propeller 12 and a second propeller 13 driven by the low-pressure turbine 9 via an epicyclic gear reduction gear 14. The propeller system also comprises a stator 15. More in particular, the epicyclic gear train 14 comprises a sun gear 16 rotating about the axis A of the turbomachine, meshing with satellites 17 around axes B belonging to a planet carrier 18, the satellites 17 meshing with a radially outer ring gear 19 , itself carried by a crown shaft 20. The shaft 20 of the ring gear 19 is coupled in rotation to the second rotor 11. Furthermore, the shaft 21 of the sun gear 16 is In addition, the shaft 22 of the planet carrier 18 is rotatably coupled to the first propeller 12 and the shaft 20 of the crown is rotatably coupled to the second propeller 13. The turbomachine 1 comprises an oil circuit ensuring in particular the lubrication and cooling of the speed reducer 14 to planetary gear. This circuit conventionally comprises an oil inlet pipe 23 connected upstream to a reservoir and equipped with an oil supply pump 24 and control means 25 located downstream of the feed pump 24, a pipe supply 26 for supplying the gear reducer 14 with oil and a recycling line 27 opening upstream of the feed pump 24, the regulation means 25 making it possible to direct all or part of the flow of oil from the incoming pipe 23 to the feed pipe 26 and / or to the recycling pipe 27. The pump 24, with fixed displacement, is rotated by a movable member of an accessory relay (not shown), located nearby, via a power shaft 28. As seen above, the rotational speeds of the various moving parts of the accessory relay are directly dependent (ie, multiples) on the rotational speed of the body. high pressure of the turbomachine. As can be seen more clearly in FIG. 3, the regulation means 25 comprise a controlled metering valve 29, for example using a servovalve, said metering valve comprising an inlet 31 connected to the inlet pipe 23 and an outlet 32 connected to the supply line 26. The inlet oil pressure 31 of the metering valve 29 is denoted P1 and the outlet pressure 32 of the metering valve 29 is denoted P2. The regulating valve 34 is designed to maintain a pressure difference P1-P2 substantially constant across the metering valve 29 (with the possible exception of transient conditions). In this way, the output oil flow 32 of the metering valve 29 is only dependent on the position in said metering valve 29. The control means of the metering valve 29 may comprise a control loop taking into account a measurement of the position of the valve 29 and / or a measurement of the oil flow at the outlet 32 of the metering valve 29.
    [0009] The metering valve 29 has slits or dosing ports as well as a movable member 33 whose position influences the flow rate of the fluid at the outlet 32 of said metering valve 29. It is therefore possible to obtain a law that can be easily determined. , for example exponential, linear or discrete, between the output oil flow 32 of the metering valve 29 and the position of the movable member 33. This position can be detected using a sensor 30 of the type LvDT for example. It should be noted that the oil is a fluid having a relatively high viscosity as well as a large variation in viscosity as a function of temperature. Consequently, the characteristic giving the output flow 32 of the metering valve 29 as a function of the position of the movable member 33 is modified substantially by the temperature of the oil, which impacts the accuracy with which the flow rate The oil is dosed through the metering valve 29. It will be noted, for example, that the viscosity varies by a factor of 17 for type II oil, between 20 ° C. and 120 ° C. It is therefore preferable to take into account the temperature of the oil in the control law of the metering valve 29. Furthermore, it turns out that the oil requirement of the gearbox 14 depends on its rotational speed, for the low speeds of the turbomachine, and its thermal rejections for the high speeds of the turbomachine. It is therefore also useful to take into account the engine speed, the oil temperature and / or the rotational speed of an element of the gearbox 14 in the control law of the metering valve. regulation further comprise a regulating valve 34 comprising an inlet 35 connected to the inlet pipe 23 and an outlet 36 connected to the recycling pipe 27. More particularly, the regulating valve 34 comprises a piston 37 whose position influences the flow rate oil outlet 36 of the regulating valve 34, said piston 37 being adapted to be subjected to a first pressure force generated by applying a first pressure in a first pressure chamber 38 of the regulating valve 34 and a second effort presser, opposed to the first pressing force, generated by applying a second pressure in a second pressure chamber 39 of the regulating valve 34. A first sewing pipe 40 connects the pressure the inlet 23 or the inlet 31 of the metering valve 29 and the first pressure chamber 38, a second branch pipe 41 connecting the supply line 26 or the outlet 32 of the metering valve 29 and the second Pressure chamber 39. Thus, the first pressure chamber 38 is subjected to the pressure P1 and the second pressure chamber 39 is subjected to the pressure P2. The first pressing force is a function of the pressure P1 and the application surface Si of the pressure P1. The second pressing force is a function of the pressure P2 and the application surface S2 of the pressure P2. The regulating valve 34 further comprises a return spring 42 mounted in the second pressure chamber 39 and capable of generating a return force on the piston 37, opposing the first pressing force. The regulating valve 34 is dimensioned so as to have a piston stroke 37 and a stiffness of the return spring 42 which are small, so as to regulate a pressure difference P1-P2 which is substantially constant. The regulation of the oil flow rate for supplying the speed reducer 14 makes it possible to avoid any damage to said speed reducer 14, for example due to a flooding thereof during operation, and makes it possible to optimize the performances and the constraints These heat exchangers of said speed reducer 14. FIG. 5 illustrates an embodiment variant of the invention which differs from that previously described in that the lubrication device comprises an oil recovery line 43 able to recover oil The recovery line 43 is equipped with a recovery pump 44. In this variant, the recycling line 27 opens into the recovery line 43, downstream of the recovery pump 44, relative to in the direction of circulation of the oil. Of course, the lubricating device according to the invention can also serve to supply oil to other members to be lubricated, such as, for example, bearings of the turbomachine.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Lubrication device for a turbomachine, comprising an oil supply line (23) equipped with an oil supply pump (24) and regulation means (25) located downstream of the feed pump ( 24), a supply line (26) for supplying oil to a lubricating member (14) and an oil recycling line (27), the regulating means (25) for directing all or part of the flow rate of oil from the supply line (23) to the supply line (26) and / or to the recycle line (27), the pump (24) being driven by at least one rotary member of a accessory relay of the turbomachine, characterized in that the regulating means (25) comprise a controlled metering valve (29) comprising an inlet (31) connected to the inlet pipe (23) and an outlet (32) connected to the supply line (26), the regulating means (25) further comprising a regulating valve (34) comprising an inlet (35) connected to the inlet pipe (23) and an outlet (36) connected to the recycling pipe (27), the position of the regulating valve (34) being controlled by the oil pressures (P1 , P2) at the inlet (31) and at the outlet (32) of the metering valve (29).
    [0002]
    2. Device according to claim 1, characterized in that the regulating valve (34) comprises a piston (37) with a variable position whose position influences the output oil flow (36) of the regulating valve (34), said piston (37) being adapted to be subjected to a first pressing force generated by applying a first pressure (P1) in a first pressure chamber (38) of the regulating valve (34) and a second pressing force, opposite at the first pressing force, generated by applying a second pressure (P2) in a second pressure chamber (39) of the regulating valve (34).
    [0003]
    3. Device according to claim 2, characterized in that it comprises a first branch pipe (40) connecting the inlet pipe (23) or the inlet (31) of the metering valve (29) and the first chamber pressure valve (38), and a second piping line (41) connecting the supply line (26) or the outlet (32) of the metering valve (29) and the second pressure chamber (39).
    [0004]
    4. Device according to claim 2 or 3, characterized in that the regulating valve (34) comprises a return spring (42) adapted to generate a return force on the piston (37).
    [0005]
    5. Device according to one of claims 1 to 4, characterized in that the metering valve (29) comprises at least one metering slot and a movable member (33) whose position is controlled and influences the flow rate. oil outlet (32) of the metering valve (29).
    [0006]
    6. Device according to one of claims 1 to 5, characterized in that the regulating valve (34) is dimensioned and controlled so as to maintain a constant pressure difference between the outlet (32) and the inlet (31) of the metering valve (29).
    [0007]
    7. Device according to one of claims 1 to 6, characterized in that the recycle line (27) opens into the inlet pipe (23), upstream of the feed pump (24).
    [0008]
    8. Device according to one of claims 1 to 6, characterized in that it comprises an oil recovery line (43) adapted to recover oil from eg the member to be lubricated (14), said recovery line (43) being equipped with a recovery pump (44), the recycling line (27) opening into the recovery line (43), downstream of the recovery pump (44).
    [0009]
    9. Turbomachine (1), characterized in that it comprises a lubricating device according to one of claims 1 to 8, a first and a second contra-rotating propellers (12, 13) driven in rotation by means of a low turbine pressure (9), via a gear reducer (14), for example planetary gear, the supply line (26) being intended to supply oil to the gear reducer (14).
    [0010]
    10. A turbomachine (1) according to claim 9, characterized in that it comprises a high pressure body comprising a high pressure compressor (2) and a high pressure turbine (3) rotatably coupled by a first shaft (4), and an additional body comprising a low-pressure compressor (5) and an intermediate pressure turbine (6) rotatably coupled by a second shaft (7), the rotational speed of the rotary member of the accessory relay being dependent on the speed of rotation of the shaft of the high-pressure body.
    类似技术:
    公开号 | 公开日 | 专利标题
    WO2015189524A1|2015-12-17|Lubrication device for a turbine engine
    EP2801707B1|2017-07-05|Turbomachine lubrication circuit with anti-siphon valve for windmilling
    FR2907495A1|2008-04-25|TURBOMACHINE
    EP3277938B1|2019-03-06|Cooling of a turbine engine oil circuit
    FR2987416A1|2013-08-30|DEVICE FOR LUBRICATING AN EPICYCLOIDAL REDUCER.
    FR2977636A1|2013-01-11|Device for lubricating rolling bearing of double helix turbopropeller of airplane, has flow channel opening to downstream level of downstream roller bearing, and lubricating oil jet opening longitudinally at upstream end of channel
    FR3022301A1|2015-12-18|TURBOMACHINE COMPRISING A DRIVE SYSTEM OF AN EQUIPMENT SUCH AS AN ACCESSORY HOUSING
    CA2801680C|2018-12-11|Architecture for a non-lubricated turboshaft engine
    EP2576995B1|2014-08-06|Gearbox in a turbomachine
    CA2923212C|2021-07-27|Device for supplying hydraulic fluid to a ram and mechanism for controlling the pitch of the blades of a turbine engine propeller comprising the ram
    FR3050761B1|2019-07-05|CONTROL OF OIL FLOW IN A COOLING CIRCUIT OF A TURBOMACHINE
    FR3034140A1|2016-09-30|AIRCRAFT TURBOMACHINE WITH PLANETARY OR EPICYCLOIDAL REDUCER
    FR3027367A1|2016-04-22|EQUIPMENT SUPPORT FOR A TURBOMACHINE COMPRISING A MAGNETIC REDUCER
    EP3682141A1|2020-07-22|Pivot for a plain bearing and gearset with reduced thermal stress
    CA2621711A1|2008-08-19|Process for drawing back-up power from a jet turbine engine and turbine engine equipped to implement such a process
    WO2015075348A1|2015-05-28|Lubrication device for a turbine engine
    FR3041052A1|2017-03-17|BOX FOR DRIVING EQUIPMENT IN A TURBOMACHINE
    FR2680829A1|1993-03-05|DRIVING DEVICE FOR AT LEAST ONE AUXILIARY MOTOR ORGAN.
    WO2015107308A1|2015-07-23|Accessory gearbox assembly for an aircraft turbine engine
    FR3035153A1|2016-10-21|TURBOPROPULSEUR WITH DOUBLET OF CONTRAROTATIVE PROPELLERS HAS BEFORE THE GAS GENERATOR
    WO2021229167A1|2021-11-18|Aircraft turbomachine comprising a device for lubricating a bearing
    FR3002007A1|2014-08-15|Oil pump for use in thermal engine of car, has control ring moved around pivot to move axis of external rotor closer to axis of internal rotor, and passage zones formed in ring to maximize sections of oil in aspiration and repression areas
    FR3108951A1|2021-10-08|SPRINKLING REDUCER LUBRICATION
    WO2021198602A1|2021-10-07|Assembly for aircraft turbine engine comprising an improved system for lubricating a fan drive reduction gear
    FR3005486A1|2014-11-14|LUBRICATION IN A TURBOMACHINE
    同族专利:
    公开号 | 公开日
    FR3022300B1|2016-06-10|
    US20170198605A1|2017-07-13|
    GB2541605A|2017-02-22|
    WO2015189524A1|2015-12-17|
    GB2541605B|2020-04-29|
    GB201620919D0|2017-01-25|
    US10677095B2|2020-06-09|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US2964132A|1957-05-28|1960-12-13|Gen Motors Corp|Lubrication system for a turbine engine|
    US5067454A|1989-06-14|1991-11-26|Avco Corporation|Self compensating flow control lubrication system|
    US6058694A|1997-11-11|2000-05-09|Alliedsignal Inc.|Gas turbine engine commanded oil flow valve with failsafe|
    EP1048842A2|1999-04-30|2000-11-02|Lucas Industries Limited|Fuel control system and valve therefor|
    EP1531271A2|2003-11-11|2005-05-18|Goodrich Pump & Engine Control Systems, Inc.|Fuel pump capacity control system for a gas turbine engine|
    US20080178833A1|2007-01-31|2008-07-31|Honeywell International, Inc.|Systems and methods for preventing oil migration|
    US2317745A|1939-03-03|1943-04-27|Duckstein Martin|Lubricating device for aircraft engines|
    US2991845A|1959-04-10|1961-07-11|Westinghouse Electric Corp|Lubrication system for a gas turbine engine|
    US3477545A|1967-03-09|1969-11-11|Auto Research Corp|Lubricant distribution system|
    US3477546A|1967-06-16|1969-11-11|Eaton Yale & Towne|Lubricating oil pumping station and master control center for positive displacement type metering valves|
    US3486582A|1967-10-30|1969-12-30|Caterpillar Tractor Co|Lubrication system for a gas turbine engine|
    US3861139A|1973-02-12|1975-01-21|Gen Electric|Turbofan engine having counterrotating compressor and turbine elements and unique fan disposition|
    US4245465A|1979-08-30|1981-01-20|Avco Corporation|Gas turbine engine lubrication system including three stage flow control valve|
    US5023789A|1990-06-04|1991-06-11|Sundstrand Corporation|Temperature compensated closed loop control of a hydraulically controlled clutch and APU starting system|
    US5217085A|1992-05-04|1993-06-08|Ford Motor Company|Lubrication and cooling system for a powertrain including an electric motor|
    US5896737A|1997-06-16|1999-04-27|United Technologies Corporation|Combined pressure regulating and fuel flow system|
    EP2295768B1|1998-01-08|2012-10-31|United Technologies Corporation|Bi-level hydraulic pressurizing system|
    DE10161131B4|2000-12-12|2013-11-07|Slw Automotive Inc.|Vane pump variable displacement|
    US7805947B2|2005-05-19|2010-10-05|Djamal Moulebhar|Aircraft with disengageable engine and auxiliary power unit components|
    US20090071754A1|2007-09-17|2009-03-19|Mcarthur Malcolm J|Metering Lubrication oil at low flow rates|
    FR2940247B1|2008-12-19|2011-01-21|Snecma|SYSTEM OF CONTRAROTATIVE PROPELLERS DRAWN BY AN EPICYCLOIDAL TRAIN PROVIDING A BALANCED TORQUE DISTRIBUTION BETWEEN THE TWO PROPELLERS|
    US8578967B2|2009-01-29|2013-11-12|Pratt & Whitney Canada Corp.|Pressure regulating valve for aircraft engine|
    GB201000103D0|2010-01-06|2010-02-17|Rolls Royce Plc|Back-Up Feathers|
    DE102010014637B4|2010-04-12|2016-05-04|MTU Aero Engines AG|Method of preserving a fuel system and an oil system|
    US8959920B2|2012-04-13|2015-02-24|Eaton Corporation|Aircraft engine fuel pump bearing flow and associated system and method|FR3044044B1|2015-11-19|2021-01-29|Snecma|FLUID SUPPLY SYSTEM OF AT LEAST ONE ORGAN OF AN AIRCRAFT PROPELLER ASSEMBLY|
    US11255221B2|2017-09-20|2022-02-22|General Electric Company|Lube system for geared turbine section|
    FR3087223B1|2018-10-10|2020-10-23|Safran Aircraft Engines|TURBOMACHINE WITH CONTRAROTARY TURBINE FOR AN AIRCRAFT|
    US11118535B2|2019-03-05|2021-09-14|General Electric Company|Reversing gear assembly for a turbo machine|
    CN111678023B|2020-06-12|2021-12-17|杨松梅|Bearing oiling device of mechanical equipment|
    法律状态:
    2015-06-12| PLFP| Fee payment|Year of fee payment: 2 |
    2015-12-18| PLSC| Search report ready|Effective date: 20151218 |
    2016-06-08| PLFP| Fee payment|Year of fee payment: 3 |
    2017-04-26| PLFP| Fee payment|Year of fee payment: 4 |
    2018-02-09| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170717 |
    2018-06-05| PLFP| Fee payment|Year of fee payment: 5 |
    2019-05-22| PLFP| Fee payment|Year of fee payment: 6 |
    2020-05-20| PLFP| Fee payment|Year of fee payment: 7 |
    2021-05-19| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1455292A|FR3022300B1|2014-06-11|2014-06-11|LUBRICATION DEVICE FOR A TURBOMACHINE|FR1455292A| FR3022300B1|2014-06-11|2014-06-11|LUBRICATION DEVICE FOR A TURBOMACHINE|
    PCT/FR2015/051552| WO2015189524A1|2014-06-11|2015-06-11|Lubrication device for a turbine engine|
    GB1620919.9A| GB2541605B|2014-06-11|2015-06-11|Lubrication device for a turbine engine|
    US15/316,751| US10677095B2|2014-06-11|2015-06-11|Lubrication device for a turbine engine|
    [返回顶部]