• 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 device (1) for lubricating an aircraft, comprising a pinion (2) having a pinion shaft (22) which is hollow and which has an axis of rotation (R-R '), said device ( 1) being characterized in that it further comprises a shaft (23) disposed within the pinion shaft (22); a space (E) between the shaft (23) and the pinion shaft (22), allowing the displacement of the oil; an oil reservoir (31) disposed opposite said gap (E) at a first end (22a) of the pinion shaft (22); an oil outlet line (42,421) disposed opposite the gap (E) at a second end (22b) of the pinion shaft (22), wherein the pinion shaft (22) ) and the shaft (23) are arranged together to form a pump adapted to push oil from the reservoir (31) to the oil outlet (42, 421) as the barrel rotates. pinion (22) around the shaft (23).
    公开号:FR3031786A1
    申请号:FR1550406
    申请日:2015-01-19
    公开日:2016-07-22
    发明作者:Boris Morelli；Stephane Prunera-Usach
    申请人:Hispano Suiza SA；
    IPC主号:
    专利说明:

    [0001] GENERAL TECHNICAL FIELD The invention relates to the field of the lubrication of aircraft elements, in particular elements positioned on the kinematic chain of a power transmission, for example a gearbox of the accessories (AGB for "Accessory GearBox" in English terminology). The mechanical power required to drive the accessories (also called "equipment") is usually taken mechanically at a propulsion unit of the aircraft. Subsequently, gears cascades allow to feed the various equipment necessary for the operation of the aircraft: generator, starter, alternator, hydraulic pumps, lubrication group, etc.
    [0002] Gear cascades as well as bearings and bearings allowing the rotation of the elements of the kinematic chain require a quasi-permanent lubrication. STATE OF THE ART In the state of the art, these gears and bearings are lubricated by a pump or a lubrication group supplied by the AGB. Sprinklers sprinkle the oil elements which are then recovered in collectors or pockets on a crankcase or cover.
    [0003] But such lubrication depends directly on the operation of the pump or lubricating group. Thus, when the propellant is stopped, lubrication is no longer, except residual oil still present or beading oil from the housing on the gears. However, when stopped by "windmilling" effects, that is to say rotation of the propulsion unit by the effect of the wind without the propulsion unit being in operation, the pinions can be rotated and have need, therefore, to be lubricated. Otherwise, there is a risk that the gears will become damaged (seizure, etc.).
    [0004] The effects of "windmilling" are also observed in flight, where air enters the engine and the influence of the wind modifies the speed of rotation of the blades or blades, which can lead to a lack of lubrication.
    [0005] PRESENTATION OF THE INVENTION To overcome the limitations mentioned above, the invention proposes a device for lubricating elements of an accessory drive system of an aircraft, comprising a pinion having a pinion shaft which is hollow. and which has an axis of rotation, said device being characterized in that it further comprises: - A shaft, disposed inside the pinion shaft and extending along the axis of rotation, - A space between the shaft and pinion shaft, allowing the displacement of the oil, - an oil reservoir, arranged opposite said space, at a first end of the pinion shaft, - an oil outlet pipe, disposed opposite the gap, at a second end of the pinion shaft, wherein the pinion shaft and the shaft are arranged to together form a pump adapted to push oil from the reservoir to the oil outlet pipe, during the rotation of the t pinion around the shaft.
    [0006] Such a device constitutes a pump complementary to conventional systems powered by the propulsion unit of the aircraft. It takes full advantage of the inertia in rotation of certain elements, when the propulsion unit is cut, as well as their ability to be set in motion by fluid mechanics effects, when stopped or in flight, to pump oil and thus provide lubrication of the elements. The invention constitutes a complementary source for lubricating the elements (in particular the sprockets) of a kinematic chain when the oil supply of the aircraft is cut off, preventing the deterioration of the elements of the aircraft (seizure, etc.). This complementary mode of lubrication to the traditional lubrication groups and / or pump, has a number of advantages.
    [0007] This additional source of lubrication can thus come as a supplement, thus adding to the lubrication group and / or traditional pump. Finally, in case of failure or malfunction of the traditional lubrication system (leakage, stoppage of the pump or lubrication unit, etc.), this additional source of lubrication can come as a substitute, replacing at least in part the lubrication that is no longer provided by the lubrication group and / or traditional pump.
    [0008] The invention furthermore comprises the following features, taken alone or in combination: A first embodiment, in which: the pinion shaft has a helical recess, and the shaft forms an eccentric screw of complementary shape to the recess helical, the pump being Sparrow type, - a second embodiment, in which: - the pinion was in the form of a hollow cylindrical tube, and - the shaft comprises spirals in the form of thread extending radially towards the pinion shaft and winding around the shaft in a direction parallel to the axis of rotation, the pump being a screw-type pump to Archimedes, A third embodiment, in which: pinion has the shape of a cylindrical tube inside which are arranged spirals extending radially towards the shaft and winding around the shaft in a direction parallel to the axis of rotation, and - the shaft is cylindrical, - the radia extension the spiral is less than the distance between the shaft and the shaft, - the pitch of the spirals is constant, - the pitch of the spirals decreases between the first end and the second end, so as to increase the pressure of the oil pumped, - the oil outlet line releases the oil on a station to be lubricated, for example in the upper part of the pinion, - the outlet pipe is connected to a nozzle which squirts oil under pressure or operates by drip gravity.
    [0009] The invention also relates to an assembly comprising a device as described above, and further comprising a housing and / or a cover, the cover being at the axis of rotation of the device. The invention further comprises the following features, taken alone or in combination: - the oil tank is a manifold or a pocket integrated in the housing or the lid, - The tank is fed by flow of oil into the housing. The invention relates to a unit comprising an assembly as described above, further comprising a propellant group in the form of a turbomachine supplying the drive system of the equipment and allowing the drive in rotation of the pinion. Finally, the invention relates to an aircraft comprising a device, an assembly or a unit as previously described. PRESENTATION OF THE FIGURES Other characteristics, objects and advantages of the invention will emerge from the description which follows, which is purely illustrative and nonlimiting, and which should be read with reference to the appended drawings, in which: FIGS. 3, 5 show various embodiments of the invention for three types of given pumps; FIGS. 2, 4, 6 show respective details of the various embodiments relating to the operation of said pumps. DETAILED DESCRIPTION In Figures 1 to 6, various embodiments of the device 1 have been shown. The device 1 comprises a pinion 2, having a pinion gear 21 21 for driving the pinion 2 in rotation about an axis of rotation R-R '. Pinion means any gear on an axis of rotation. The pinion gear 21 is integral, by fixation or material, with a hollow pinion shaft 22 (hereinafter referred to as a "shaft") which extends along the axis of rotation R-R '. A pinion shaft is the central part of a pinion, in the center of which passes the axis of rotation, and which supports a disk comprising the pinion gear.
    [0010] The pinion 2 is typically positioned on the force transmission chain of an AGB, that is to say that said pinion 2 for example drives an accessory (or equipment) or constitutes an intermediate element during a step of reduction of ratio or transmission. The AGB is itself driven by a propulsion unit of the aircraft. Said propellant group is preferably a turbomachine. Inside the hollow pinion shaft 22, a shaft 23 is disposed and extends along the axis of rotation R-R '. The shaft 22 and the shaft 23 are arranged so that there is a space E between them. Thanks to the rotation of the shaft 22, the shaft 23 and the shaft 22 form pumping means, in particular by pushing the oil. Space E, as will be seen later, allows the displacement of oil during pumping.
    [0011] At a first end 23a of the shaft 23 and a first end 22a of the shaft 22, facing the space E, an oil reservoir 31 is disposed. The oil reservoir 31 supplies the space E with oil. The oil tank 31 will be detailed later.
    [0012] At a second end 23b of the shaft 23 and a second end 22b of the shaft 22, opposite the space E always, an oil outlet line 42 is positioned to recover the oil pumped and possibly pressurized. The oil outlet pipe 42 is preferably located in the lower part of the shaft, so that the gravity favors the flow. The oil outlet pipe 42 may open at various locations. In one embodiment, the oil line 42 opens on the pinion 2 and allows its lubrication. In other embodiments, the oil line 42 opens to other stations to be lubricated, such as bearings 6 or other bearings. The pipe 42 will be detailed later and various embodiments will be explained.
    [0013] Thanks to the rotation of the shaft 22, the shaft 23 and the shaft 22, which form pumping means, move the oil from the oil reservoir 31 to the oil outlet pipe 32. As mentioned above, displacement can be accompanied by pressurization.
    [0014] The device 1 is integrated without limitation in a housing 5 which protects the other elements of the aircraft oil projections in particular. At the end of the device 1 may be a cover 51 secured to the housing 5, by screwing for example. Alternatively, the cover 51 may be part of the same part as the housing 5. The pinion 2 (more precisely the shaft 22) and the shaft 23 are held in position preferably through the housing 5 and / or the cover 51. For this purpose , bearings 6 are provided at the ends of the device 1, and allow, while supporting the pinion 2, the rotation of the device 1.
    [0015] In particular, the first end 22a of the shaft 22, located on the oil reservoir side 31, and the second end 22b of the shaft 22, located on the oil outlet line side 42 are carried by said bearings 6. Alternatively in one embodiment cantilevered, only one end 22a, 22b of the barrel 22 can be carried by the bearings 6.
    [0016] Now, different embodiments of the pump system of the device 1 will be described. Sparrow type pump In this first embodiment, the hollow sprocket drum 22 and the shaft 23 form a Sparrow type pump (see FIG. 1). The hollow pinion shaft 22 has a helical shape and the shaft is a helical eccentric shaft, having a shape complementary to the helical recess of the shaft 22. When the shaft is inserted into the pinion shaft, the space E is comprised of a double chain of sealed cavities El, E2 (sometimes called cells). When the shaft 22 rotates outside the shaft 23, the shape of the helical eccentric shaft 23 cooperates with the helical shape of the pinion shaft 22 and the cells progress along the shaft 23 and the shaft 22 of the pump without changing shape or volume, which transfers the oil from the oil reservoir 31 to the oil outlet conduit 42. In this embodiment, due to the tight cavities El and E2 which move , the oil reservoir 31 typically comprises the spout 311 which pours into the upper part of the space E. The architecture of the shaft 22 and the shaft 21 is made so that the cells move from the tank 31 towards the outlet duct 42 when the pinion 2 drives the pump.
    [0017] In this embodiment, because of the helical eccentricity of the shaft 23 and the rotational drive by the shaft 22, the two ends 23a, 23b of the shaft 23 have a rectilinear translational movement in a plane parallel to the axis of rotation RR '(see Figure 2).
    [0018] To allow this movement, the casing 5 and / or the cover 51 can provide notches 52. In order to ensure the seal at these translations in the notches 52, seals are positioned (not shown in the figures ). At the second end 23b of the shaft 23, the oil must be directed to the oil outlet conduit 42. The housing 5 is preferably adapted for this purpose. The operation of the pump is called volumetric. There is no pressurization, or only under low pressure.
    [0019] The pump delivers discontinuous fluid volumes. Archimedean Screw Pump In this second embodiment, the hollow pinion shaft 22 and the shaft 23 form an Archimedean screw pump (see FIG. 3). The hollow pinion shaft 22 forms a cylindrical tube and the shaft 23 is a cylindrical tube centered on the axis of rotation R-R '. The shaft 23 comprises on its outer surface spirals 24 extending radially towards the shaft 22 and winding around the shaft 23 along the axis of rotation R-R ', for example in the form of threading. The shaft 23 is fixed in the device 1 while it was turning. For this, the shaft 23 is integral with the housing 5 or cover 51, either on the side of the first end 23a, or on the side of the second end 23b (as shown in Figure 3), and the shaft 22 is driven by the gear teeth 21. Compared to a traditional screw pump in which the shaft (the stator) is fixed, and the shaft (the rotor) is rotating, the pump here is reversed. Nevertheless, the relative movement of the shaft 22 relative to the shaft 23 remains the same and the pump operates in a similar manner. The shaft 23 can be fixed to the housing 5 or be integral with it. In this embodiment, there is typically the barrel which extends axially along the axis RR 'more than the first end 23a of the shaft 23, so that the reservoir can pour directly into the space E. The meaning Spiral winding 24 is selected so that for a given pinion 22 rotation, the device acts well as a pump from tank 31 to the oil outlet line 32. The radial extension is denoted by "e" spirals 24, "d" the distance between the shaft 23 and the shaft 22, "L" the pitch between two spirals 24 along an axis 25 parallel to the axis of rotation RR '(see Figure 4). According to a first type of preferred variant, the radial extension e is smaller than the distance d, so that there remains a free play at the inner surface of the drum 22. In a plane normal to the axis of rotation R - 30 R ', the space E is not divided into several parts. By the rotation of the shaft 22 and the centrifugal force, the oil is pressed against the inner surface of the shaft 22. Therefore, all the oil is not directly driven by the spirals 24. The latter help to promote the displacement of the oil, the viscosity of the oil then allowing the displacement by training. According to a second type of variant, several step values L can be chosen. In a first case, the pitch L between two spirals 24 is constant. In a second case, the pitch L between two spirals 24 decreases when approaching the oil outlet duct 42. The decrease is preferably progressive all along the shaft 23 (Figure 4) This decrease allows for increase the pressure of the oil. The adapted screw pump In this third embodiment, the hollow pinion shaft 22 and the shaft 23 again form a screw pump (see FIG. 5). The hollow pinion shaft 22 forms a cylindrical tube and the shaft 23 is a cylindrical tube centered on the axis of rotation R-R '. The hollow sprocket drum 22 comprises on its inner surface spirals 25 extending radially towards the shaft 23 and wound on the inner surface of the barrel 22 along the axis of rotation R-R ', for example under thread shape. The shaft 23 is fixed in the device 1 while it was turning. For this, the shaft 23 is integral with the housing 5 or cover 51, and the shaft 22 is driven by the gear teeth. In this embodiment, there is typically the shaft which extends axially along the axis R-R 'more than the first end 23a of the shaft 23, so that the reservoir can pour directly into the space E.
    [0020] The winding direction of the spirals 24 is chosen so that for a given pinion 22 rotation, the device acts well as a pump from the tank 31 towards the oil outlet pipe 32.
    [0021] We note "e" the radial extension of the spirals 24, "d" the distance between the shaft 22 and the shaft 23, the "L" the pitch between two spirals 25 along an axis parallel to the axis of rotation RR '(see Figure 6).
    [0022] According to the same first type of preferred variant, the radial extension e 'is less than the distance of, so that there remains a free play at the shaft 23. In a plane normal to the axis of rotation R-R ', the space E is therefore not divided into several parts.
    [0023] By the rotation of the shaft 22 and the centrifugal force, the oil is pressed against the inner surface of the shaft 22. Consequently, the majority of the oil is directly driven by the spirals 25. The remaining oil, closer to the shaft 23 is essentially driven by viscosity.
    [0024] According to the same second type of variant, several pitch values L 'can be chosen. In a first case, the pitch L 'between two spirals 25 is constant. In a second case, the pitch L 'between two spirals 25 decreases when approaching the oil outlet duct 42. The decrease is preferably progressive all along the shaft 22 (Figure 6). This decrease increases the pressure of the oil. In both embodiments of screw (Archimedes and adapted), the profile of the spirals 24, 25 of the thread shown in Figures 4, 6 is not limiting. This may take the form of a slot, or a non-isosceles triangle, that is to say that the spiral 24, 25 of the thread may have a shape favoring a direction of drive of the oil, especially in being inclined towards the oil outlet pipe 42.
    [0025] In addition, by the viscosity of the oil, the spirals 24, 25 have essentially a global driving role.
    [0026] Now some elements of the device will be described in more detail. These elements apply to all embodiments. So that the reservoir 31 can pour into said space E, the first end 22a of the shaft 22 extends axially along the axis RR 'and towards the oil reservoir 31, further than the first end 23a of the shaft 23 so that part of the reservoir 31 enters the volume defined by the barrel cylinder 22 to define a Z pay zone. In addition, when the device 1 is installed on an aircraft, the oil reservoir 31 is located at least partly higher than the space E defined between the shaft 23 and the shaft 22, so as to be able to pour by gravity into said space E. Alternatively, the shaft 23 and the shaft 22 may have lengths similar to level of the pour zone Z, that is to say that the first ends 22a, 23a of the shaft 22 and the shaft 23 end substantially at the same level. In this case, the oil reservoir 31 may comprise a spout 311 which enters the space E between the shaft 22 and the shaft 23. Preferably the spout 311 pours into the upper part of the space E.
    [0027] The oil reservoir 31 is typically in the form of a pocket or a manifold. The oil reservoir 31 is advantageously integrated in the housing 5 or the cover 51. The supply of the oil reservoir 31 can be carried out by streaming oil inside the housing 5. In effect, the lubrication of the pinion 2 causes centrifugal force projections of oil on the walls of the casing 5. The projected oil drops drift along the wall and are recovered at the collector forming the oil reservoir 31.
    [0028] Alternatively, it is possible to provide a specific supply of the oil reservoir 31, for example by means of a dedicated nozzle. The oil reservoir 31 is preferably sized to contain a sufficient amount of oil to allow continued lubrication when the propellant is shut down. More generally, the tank 31 can be replaced by an oil supply. Nevertheless, it is better to have a stock of oil. The oil outlet duct 42 may be part of the casing 5. Two main modes of use of the oil outlet duct 42 can be distinguished. Generally speaking, the oil duct 42 may comprise part of recovery 421, a transmission portion 422 and a pouring portion 423. The recovery portion 421 is preferably located vis-à-vis the second end 22b of the barrel 22, substantially at the same level, and lower part of the barrel 22 to take advantage of the gravity flow.
    [0029] A seal system (not shown) is provided in the junction to limit leakage. In a first embodiment, the transmission portion 422 raises the oil to the upper part of the pinion and pours oil therein, in order to lubricate the pinion 2 by gravity flow. It is thus not necessary to mount the oil under pressure very significantly: it suffices to overcome the hydrostatic pressure of the transmission portion 422. The first embodiment is preferably used for the embodiment with a pump of Sparrow type.
    [0030] In a second embodiment, when the oil is under pressure, the pouring portion 423 may comprise a nozzle 7 which sprinkles the pinion 2 with oil. The spraying is typically done in the lower part of pinion 2. The second embodiment can be used when the oil is pressurized by the pump as in certain variants of screw pumps.
    [0031] The oil outlet duct 42 may also contribute to lubricating the bearings 6 or any other bearing present in the AGB, more generally any station requiring lubrication. Alternatively, the oil outlet duct 42 can pass through the casing 5 to lubricate other elements of the AGB. By the architecture of the system and the pressure levels involved, the invention is particularly relevant for local lubrication, that is to say in the vicinity of pinion 2. By proximity means a distance such that the device 1 can carry oil over this distance. According to an advantageous embodiment of the invention, it is even self-lubrication, since the pinion 2 feeds the device 1 which lubricates it. Whatever the lubricated element, lubrication can be done either by a drip or by a projection of oil under pressure (using a nozzle for example). The invention applies to any pinion dimensioning 2. In fact, the pump principle integrated into the shaft of a hollow pinion 22 can be generalized over any size of shaft diameter 22 and shaft 23.
    [0032] Similarly, the sizing of the components of the pump (shaft diameter, number of spirals, etc.) can be adapted as needed. In an accessory drive system, several devices 1 are provided and intermesh each other. In particular, the device 1 makes it possible to transmit forces and / or to reduce a ratio in order to supply an accessory.
    权利要求:
    Claims (14)
    [0001]
    REVENDICATIONS1. Device (1) for lubricating elements of an aircraft accessory drive system, comprising a pinion (2) having a pinion shaft (22) which is hollow and which has an axis of rotation (R- R '), said device (1) being characterized in that it further comprises: - A shaft (23) disposed inside the pinion shaft (22) and extending along the axis of rotation ( R-R '), - a space (E) between the shaft (23) and the pinion shaft (22), allowing the displacement of the oil, - an oil tank (31) disposed opposite said space (E), at a first end (22a) of the pinion shaft (22), - an oil outlet pipe (42, 421) disposed opposite the space (E), at the a second end (22b) of the pinion shaft (22), wherein the pinion shaft (22) and the shaft (23) are arranged to together form a pump adapted to push oil from the tank (31) to the oil outlet line (42, 421), when the rotation of the pinion shaft (22) around the shaft (23).
    [0002]
    2. Device according to claim 1, wherein: - the pinion shaft (22) has a helical recess, and - the shaft (23) forms an eccentric screw of complementary shape to the helical recess, the pump being Sparrow type.
    [0003]
    3. Device according to claim 1, wherein: - the pinion (22) has the shape of a hollow cylindrical tube, and- the shaft (23) comprises spirals (24) in the form of thread extending radially towards the pinion shaft (22) and winding around the shaft (23) in a direction parallel to the axis of rotation (R-R '), the pump being an Archimedean screw type pump.
    [0004]
    4. Device according to claim 1, wherein: - the pinion shaft (22) has the shape of a cylindrical tube inside which are arranged spirals (25) extending radially towards the shaft (23) and winding around the shaft (23) in a direction parallel to the axis of rotation (R-R '), and - the shaft (23) is cylindrical.
    [0005]
    5. Device according to any one of claims 3 to 4, wherein the radial extension (e, e ') of the spirals (24, 25) is less than the distance (d, d') between the barrel (22). and the shaft (23).
    [0006]
    6. Device according to any one of claims 4 to 5, wherein the pitch (L, L ') of the spirals (24, 25) is constant.
    [0007]
    7. Device according to any one of claims 3 to 6, wherein the pitch (L, L ') of the spirals (24, 25) decreases between the first end (22a, 23b) and the second end (22b, 23b) , so as to increase the pressure of the oil pumped.
    [0008]
    8. Device according to any one of claims 1 to 7, wherein the oil outlet pipe (42, 423) releases the oil on a station to be lubricated, for example in the upper part of the pinion (2). 30
    [0009]
    9. Device according to any one of claims 1 to 8, wherein the outlet pipe (42, 421) is connected to a nozzle (7) which squirts oil under pressure or works by gravity drip .
    [0010]
    10. An assembly comprising a device (1) according to any one of claims 1 to 9, and further comprising a housing (5) and / or a cover (51), the cover being at the axis of rotation of the device (R-R ').
    [0011]
    11. The assembly of claim 10, wherein the oil reservoir (31) is a collector or a pocket integrated in the housing (5) or the cover (51).
    [0012]
    12. An assembly according to claim 10 or 11, wherein the reservoir (31) is fed by flow of the oil into the housing (5).
    [0013]
    13. Unit comprising an assembly according to one of claims 10 to 12, further comprising a propellant group in the form of a turbomachine supplying the drive system of the equipment and allowing the rotational drive of the pinion (2).
    [0014]
    Aircraft comprising a device, an assembly or a unit according to any one of claims 1 to 13.
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    同族专利:
    公开号 | 公开日
    CN107110027B|2019-06-14|
    JP2018504563A|2018-02-15|
    CN107110027A|2017-08-29|
    EP3247924B1|2020-07-29|
    EP3247924A1|2017-11-29|
    FR3031786B1|2018-11-02|
    RU2705484C2|2019-11-07|
    CA2973313A1|2016-07-28|
    WO2016116694A1|2016-07-28|
    US20180266540A1|2018-09-20|
    RU2017129258A3|2019-07-17|
    US10415691B2|2019-09-17|
    JP6709224B2|2020-06-10|
    RU2017129258A|2019-02-21|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    GB1250040A|1968-11-19|1971-10-20|United Aircraft Corp|Accesory drive system and pump system|
    DE4330226C1|1993-09-07|1994-09-08|Bornemann J H Gmbh & Co|Eccentric worm screw pump|
    WO1997040273A1|1996-04-24|1997-10-30|Wood Steven M|Progressive cavity pumps using composite materials|
    EP2063125A1|2007-11-02|2009-05-27|Grundfos Management A/S|Moineau pump|
    EP2690318A1|2012-07-25|2014-01-29|Bell Helicopter Textron Inc.|Direct drive rotation device for passively moving fluid|
    WO1992012357A1|1991-01-14|1992-07-23|Advanced Power Technology, Inc.|Hydraulic machine|
    US20120283060A1|2011-05-02|2012-11-08|American Axle & Manufacturing, Inc.|Lubrication distribution within rear drive module|FR3007462B1|2013-06-21|2017-11-24|Hispano-Suiza|TURBOMACHINE ACCESSORY BOX EQUIPPED WITH CENTRIFUGAL PUMP|
    FR3018860B1|2014-03-21|2021-10-15|Hispano Suiza Sa|ACCESSORY RELAYS FOR GAS TURBINE ENGINES|
    RU2669453C1|2017-11-10|2018-10-11|Публичное акционерное общество "ОДК - Уфимское моторостроительное производственное объединение" |Thrust bearing block for discharge pump of gas turbine engineoil pump unit , thrust bearing of driving wheel for discharge pump of oil pump unit, thrust bearing of driven wheel for discharge pump of oil pump unit|
    RU2669662C1|2017-11-10|2018-10-12|Публичное акционерное общество "ОДК - Уфимское моторостроительное производственное объединение" |Method of operating gas-turbine engineoil unit and gte oil unit operating therewith |
    RU2669531C1|2017-11-10|2018-10-11|Публичное акционерное общество "ОДК - Уфимское моторостроительное производственное объединение" |Method of gas-turbine engineoil unit discharge pump operation and gte oil unit discharge pump working therewith , gte oil unit discharge pump driving wheel, gte oil unit discharge pump driven wheel|
    CN109555602B|2018-12-10|2020-02-04|中国航发南方工业有限公司|Oil return system of transmission box|
    法律状态:
    2016-01-22| PLFP| Fee payment|Year of fee payment: 2 |
    2016-07-22| PLSC| Publication of the preliminary search report|Effective date: 20160722 |
    2017-01-05| PLFP| Fee payment|Year of fee payment: 3 |
    2017-08-25| CD| Change of name or company name|Owner name: HISPANO - SUIZA, FR Effective date: 20170725 |
    2017-12-21| PLFP| Fee payment|Year of fee payment: 4 |
    2019-12-19| PLFP| Fee payment|Year of fee payment: 6 |
    2020-12-17| PLFP| Fee payment|Year of fee payment: 7 |
    2021-12-15| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1550406|2015-01-19|
    FR1550406A|FR3031786B1|2015-01-19|2015-01-19|INTEGRATION OF A PUMP IN FUT OF PINION|FR1550406A| FR3031786B1|2015-01-19|2015-01-19|INTEGRATION OF A PUMP IN FUT OF PINION|
    US15/544,424| US10415691B2|2015-01-19|2016-01-19|Integration of a pump on a pinion shank|
    CA2973313A| CA2973313A1|2015-01-19|2016-01-19|Integration of a pump on a pinion shank|
    EP16703346.3A| EP3247924B1|2015-01-19|2016-01-19|Integration of a pump on a pinion shank|
    PCT/FR2016/050098| WO2016116694A1|2015-01-19|2016-01-19|Integration of a pump on a pinion shank|
    JP2017537940A| JP6709224B2|2015-01-19|2016-01-19|Integrated pump with pinion shank|
    RU2017129258A| RU2705484C2|2015-01-19|2016-01-19|Pump integration into shank end of gear|
    CN201680006143.0A| CN107110027B|2015-01-19|2016-01-19|Pump the conglomerate on pinion shaft|
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