HYDRAULIC DEVICE FOR AIRCRAFT TURBOMACHINE LUBRICANT CIRCUIT

Abstract

The invention relates to a hydraulic distributor (2), intended to be arranged within a lubricant circulation circuit for an aircraft turbomachine, comprising: - a first lubricant inlet (210) intended to be supplied with lubricant leaving a device to be lubricated (19); - a first lubricant outlet (211) intended to supply an inlet of an exchanger (9); - a second lubricant inlet (212) intended to be supplied with lubricant leaving the exchanger (9); - a second lubricant outlet (213) intended to supply an inlet of the device to be lubricated (19);- a passive control member (23), intended to be pressure-controlled by lubricant leaving the exchanger (9), between a circulation position allowing a first communication between the first lubricant inlet (210) and the first lubricant outlet (211) as well as a second communication between the second lubricant inlet (212) and the second lubricant outlet (213), and a bypass position breaking the first communication. Figure 4.;

Description

Title of the invention: HYDRAULIC DEVICE FOR AN AIRCRAFT TURBOMACHINE LUBRICANT CIRCUIT Field of invention

[0001] The present invention relates to the field of dual-flow aircraft turbomachines.

[0002] More particularly, the invention relates to a hydraulic distributor intended to be arranged within a lubricant circulation circuit for an aircraft turbomachine, between a device to be lubricated and a heat exchanger through which the lubricant passes.

[0003] The invention preferably relates to turbomachines comprising a rectifier provided with rectifier vanes, also called OGV (from the English "Outlet Guide Vane"), provided for rectifier a flow of air leaving a fan of the turbomachine. State of the prior art

[0004] On certain turbomachines, and mainly dual-flow turbomachines, it is known to install a rectifier provided with rectifier blades downstream of the fan in order in particular to straighten the air flow which escapes from the latter. The rectifier blades can also now have an additional heat exchanger function, and more particularly between the air passing through the rectifier, and the lubricant circulating inside the rectifier blades. This heat exchanger function is for example known from document US 8,616,834 or from document FR 2,989,110.

[0005] The lubricant intended to be cooled by the stator vanes can come from different areas of the turbomachine. In particular, this lubricant can be used for the lubrication and cooling of a fan drive reducer implemented to reduce the rotational speed of the fan. Indeed, such a reducer comprising numerous bearings and gears, it proves necessary to lubricate and cool them by the circulation of lubricant which must in turn be cooled at the stator vanes so that the lubricant circulation circuit can operate continuously.

[0006] However, a disadvantage for the user of the rectifier and the rectifier blades as heat exchangers comes from the risk of fire if a rectifier blade breaks, for example following an impact with a foreign body ingested by the turbomachine. Indeed, if a rectifier blade carries a lubricant circulation circuit, then in the event that this rectifier blade breaks, the circuit of Lubricant circulation opens to the open air in the turbomachine, thereby igniting the lubricant which continues to flow without interruption, thus self-feeding the fire. In addition, a break in the lubrication circuit would cause a significant or even total drop in pressure in the lubrication circuit, thus preventing lubrication of the reducer and therefore potentially causing damage or even breakage of the reducer.

[0007] There is therefore a need to provide a solution that makes it possible to preserve the integrity of the turbomachine as well as the lubrication and cooling functions of the lubrication circuit in the event of mechanical problems at the rectifier level. Statement of the invention

[0008] The invention aims to remedy at least in part the drawbacks mentioned above relating to the techniques of the prior art.

[0009] To this end, the invention relates to a hydraulic distributor intended to be arranged within a lubricant circulation circuit for an aircraft turbomachine, between a device to be lubricated and a heat exchanger through which the lubricant passes, the hydraulic distributor comprising:

[0010] - a first lubricant inlet intended to be supplied with lubricant leaving the lubricating device;

[0011] - a first lubricant outlet intended to supply an inlet of the exchanger;

[0012] - a second lubricant inlet intended to be supplied with lubricant coming out of the exchanger;

[0013] - a second lubricant outlet intended to supply an inlet of the device to lubricate;

[0014] the distributor comprising a passive control member, intended to be pressure-controlled by lubricant leaving the exchanger, between a circulation position allowing a first communication between the first lubricant inlet and the first lubricant outlet as well as a second communication between the second lubricant inlet and the second lubricant outlet, and a bypass position breaking the first communication, this bypass position being reached when the lubricant pressure applied to the control member falls below a predetermined value.

[0015] Thus, the invention proposes a new and inventive approach making it possible to resolve at least in part certain of the drawbacks of the prior art.

[0016] Indeed, this makes it possible to prevent the lubricant from continuing to circulate in the event of breakage at the exchanger and thereby presenting a risk of self-fueling fire due to the fact that in the bypass position corresponding to a position indicating a drop in pressure below a predetermined value, the first communication between the first lubricant inlet and the first lubricant outlet is broken. In other words, the lubricant no longer reaches the exchanger in this bypass position. In addition, such a solution makes it possible to limit the rupture of the lubrication circuit and therefore to limit the pressure drop in the lubrication circuit because the lubricant does not continue to flow and therefore remains in the lubrication circuit.

[0017] According to a particular aspect of at least one embodiment of the invention, the hydraulic device comprises a hollow cylindrical body carrying said first lubricant inlet, said first lubricant outlet, said second lubricant inlet, and said second lubricant outlet.

[0018] According to a particular aspect of at least one embodiment of the invention, the hydraulic device comprises a piston arranged in said hollow cylindrical body, and comprising a plurality of partitions, said partitions and said hollow cylindrical body forming at least two sealed compartments, said piston being mounted movably in said hollow cylindrical body so that in said circulation position, said first communication between the first inlet and the first outlet passes through a first sealed compartment of said sealed compartments, and said second communication between the second inlet and the second outlet passes through a second sealed compartment of said sealed compartments.

[0019] This makes it possible to implement mechanically simple and reliable means in order to optimize the operation of the solution and reduce possible maintenance.

[0020] According to a particular aspect of at least one embodiment of the invention, in the bypass position, the first communication and the second communication are broken, and a third communication is established between the first lubricant inlet and the second lubricant outlet.

[0021] Redirecting the lubricant arriving via the first inlet to the second outlet makes it possible to short-circuit part, or even all, of the faulty lubrication circuit and to limit lubricant losses, and therefore also pressure losses in the lubrication circuit.

[0022] According to a particular aspect of at least one embodiment of the invention, the device further comprises a return spring controlled by said passive control member, said passive control member being configured to compress said return spring so as to slide said piston in said hollow cylindrical body from said bypass position to said circulation position, when the lubricant pressure applied to the control member is above said predetermined value.

[0023] According to a particular aspect of at least one embodiment of the invention, the hydraulic device further comprises cooling means.

[0024] This makes it possible to increase the cooling capacity of the lubricant and therefore consequently the cooling capacity of the device to be lubricated.

[0025] According to a particular aspect of at least one embodiment of the invention, said predetermined value is between 0 bar and a minimum operating pressure of the lubricant circulation circuit.

[0026] This minimum pressure, as well as a maximum pressure, constitute two limits, respectively lower and upper, of a working pressure of the lubricant circulation circuit depending on the type of turbomachine.

[0027] This predetermined value may, according to a particular aspect, be equal to a quarter of the minimum pressure so as to protect against a total breakage of the circuit on a given blade, due to the fact that a leak of all the lubricant passing through this blade is observable by a total drop in pressure.

[0028] It would also be possible to provide a predetermined value relatively close to the minimum pressure so as to detect the slightest drop, even a slight one, in pressure in the lubricant circulation circuit.

[0029] The invention also relates to an assembly for an aircraft turbomachine, comprising a lubricant circulation circuit for an aircraft turbomachine connecting at least one device to be lubricated and a heat exchanger through which the lubricant passes, the assembly comprising at least one hydraulic distributor according to one of the aforementioned embodiments, said hydraulic device being intended to be arranged within said lubricant circulation circuit, between said device to be lubricated and said heat exchanger.

[0030] According to a particular aspect of at least one embodiment of the invention, said device to be lubricated is a reducer and said heat exchanger is an air flow straightener comprising at least one straightener blade.

[0031] According to a particular aspect of at least one embodiment of the invention, said air flow straightener comprises several straightener vanes, each of said straightener vanes being connected to said reducer by an independent hydraulic device.

[0032] This allows that in the event of breakage of one of the rectifier vanes, only the portion of the lubricant circuit passing through this rectifier vane is isolated while the other portions of the lubricant circuit passing through the other rectifier vanes can continue to operate normally, so as to ensure lubrication of the reducer and cooling of the lubricant.

[0033] The invention also relates to an aircraft turbomachine, comprising an assembly according to one of the aforementioned embodiments. Presentation of figures

[0034] The invention, as well as the various advantages that it presents, will be more easily understood in the light of the following description of an illustrative and non-limiting embodiment thereof, and of the appended drawings among which: [Fig.l] is a schematic sectional view of an aircraft turbomachine; [Fig.2] is a diagram illustrating an assembly according to one embodiment of the invention, the hydraulic device being in the circulation position; [Fig.3] is a diagram illustrating an assembly according to the embodiment of [Fig.2], the hydraulic device being in the bypass position; [Fig.4] is a diagram illustrating an assembly according to the embodiment of [Fig.2], the hydraulic device being in the circulation position, and [Fig.5] is a diagram illustrating an assembly according to the embodiment of [Fig.2], the hydraulic device being in the bypass position.

[0035] Detailed description of an embodiment of the invention

[0036] With reference to [Fig.l], a twin-spool turbojet engine 1 is shown, having a high bypass ratio. The turbojet engine 1 conventionally comprises a gas generator 5 on either side of which are arranged a low-pressure compressor 4 and a low-pressure turbine 12, this gas generator 5 comprising a high-pressure compressor 6, a combustion chamber 8 and a high-pressure turbine 10. Subsequently, the terms "front" and "rear" are considered along a direction 14 opposite to the main flow direction of the gases within the turbojet engine, this direction 14 being parallel to the longitudinal axis 3 thereof. On the other hand, the terms "upstream" and "downstream" are considered along the main flow direction of the gases within the turbojet engine.

[0037] The low-pressure compressor 4 and the low-pressure turbine 12 form a low-pressure body, and are connected to each other by a low-pressure shaft 11 centered on the axis 3. Similarly, the high-pressure compressor 6 and the high-pressure turbine 10 form a high-pressure body, and are connected to each other by a high-pressure shaft 13 centered on the axis 3 and arranged around the low-pressure shaft 11. The shafts are supported by rolling bearings 59, which are lubricated by being arranged in oil chambers. The same applies to the fan hub 17, also supported by rolling bearings 59.

[0038] The turbojet 1 also comprises, in front of the gas generator 5 and the low-pressure compressor 4, a single fan 15 which is here arranged directly at the rear of an air inlet cone of the engine. The fan 15 is rotatable along the axis 3, and surrounded by a fan casing. In [Fig.l], it is not driven directly by the low-pressure shaft 11, but only driven indirectly by this shaft via a reducer 19, which allows it to rotate at a slower speed. Nevertheless, a solution with direct drive of the fan 15, by the low pressure shaft 11, falls within the scope of the invention.

[0039] Furthermore, the turbojet 1 defines a primary vein 16 intended to be crossed by a primary flow, as well as a secondary vein 18 intended to be crossed by a secondary flow located radially outwardly relative to the primary flow, the fan flow therefore being divided. As is known to those skilled in the art, the secondary vein 18 is delimited radially outwardly in part by an outer shroud 53, preferably metallic, extending the fan casing rearwardly.

[0040] Although this has not been shown, the turbojet 1 is equipped with a set of equipment, for example of the fuel pump, hydraulic pump, alternator, starter, variable-speed stator actuator (VSV), wastegate actuator, or even electric power generator type. This includes equipment for lubricating the reducer 19. This equipment is driven by an accessory gearbox or AGB (not shown), which is also lubricated.

[0041] Downstream of the fan 15, in the secondary vein 18, there is provided a ring of guide vanes which are here outlet guide vanes 90 (or OGV, from the English “Outlet Guide Vane”). These stator vanes 90 connect the outer shell 53 to a casing 56 surrounding the low-pressure compressor 4. They are circumferentially spaced from each other, and make it possible to straighten the secondary flow after it has passed through the fan 15. In addition, these vanes 90 can also fulfill a structural function, as is the case in the exemplary embodiments which are presently described. They ensure the transfer of forces coming from the reducer and the rolling bearings 19 of the engine shafts and the fan hub, towards the outer shroud 53. Then, these forces can pass through an engine attachment 30 fixed on the shroud 53 and connecting the turbojet to a mounting pylon (not shown) of the aircraft.

[0042] Finally, the outlet guide vanes 90 provide a third heat exchanger function between the secondary air flow passing through the crown of vanes, and the lubricant circulating inside these vanes 90. The lubricant intended to be cooled by the outlet guide vanes 90 is that used in particular for the lubrication of the reducer 19.

[0043] The turbomachine therefore comprises a lubricant circulation circuit connecting at least one device to be lubricated, here the reducer, and a heat exchanger 9, here the rectifier 9 comprising at least one rectifier blade 90 through which the lubricant passes.

[0044] According to the general principle of the invention, in order to prevent the lubricant from continuing to circulate in the event of breakage at the exchanger and thereby presenting a risk of self-sustaining fire, the solution consists of implementing at least one hydraulic distributor intended to be provided within said lubricant circulation circuit, between said device to be lubricated and said heat exchanger.

[0045] An embodiment of the invention is now presented in relation to Figures 2 to 5.

[0046] As illustrated, the invention applies to an assembly for an aircraft turbomachine, comprising a lubricant circulation circuit for an aircraft turbomachine connecting at least one device to be lubricated 19 and a heat exchanger 9 through which the lubricant passes.

[0047] This assembly comprises at least one hydraulic distributor 2 arranged within the lubricant circulation circuit, between the device to be lubricated 19 and the heat exchanger 9.

[0048] Here, the device to be lubricated is a reducer 19 and the heat exchanger is an air flow straightener 9 comprising a plurality of straightener vanes 90.

[0049] The air flow straightener here takes the form of a wheel carrying the plurality of straightener vanes. Depending on the embodiments, this straightener wheel may comprise either straightener vanes provided with an integrated heat exchanger alternating with straightener vanes not provided with a heat exchanger, or only straightener vanes provided with a heat exchanger.

[0050] More generally, it could be provided that the air flow straightener comprises at least one straightener blade 90.

[0051] The lubricant circulation circuit allows the lubricant to circulate between the reducer and the stator vanes in a closed loop so as to lubricate the reducer and cool the lubricant at the stator vanes.

[0052] According to the invention, a hydraulic device 2 is provided in order to control the circulation of the lubricant between the reducer 19 and the rectifier vanes 90.

[0053] It should be noted that, in this embodiment, each of the rectifier vanes 90 is connected to the reducer 19 by an independent hydraulic device 2 within the lubricant circulation circuit.

[0054] More precisely, in this embodiment, only the lubricant pump (not shown) is common to the lubrication circuit, each of the rectifier vanes 90 being connected to the reducer 19 by a hydraulic device 2 and therefore by different branches of the lubrication circuit.

[0055] The advantage of implementing a hydraulic device per rectifier blade is that in the event of breakage of the rectifier blade, only the branch of the circuit leading to this rectifier blade will be impacted, the branches relating to the integral rectifier blades not suffering any inconvenience.

[0056] As illustrated, this hydraulic distributor comprises:

[0057] a first lubricant inlet intended to be supplied with lubricant leaving the device to be lubricated;

[0058] - a first lubricant outlet intended to supply an inlet of the exchanger;

[0059] - a second lubricant inlet intended to be supplied with lubricant coming out of the exchanger;

[0060] - a second lubricant outlet intended to supply an inlet of the device to lubricate.

[0061] Therefore, in this embodiment, the hydraulic distributor 2 comprises:

[0062] a first lubricant inlet 210 intended to be supplied with lubricant leaving the reducer 19;

[0063] - a first lubricant outlet 211 intended to supply an inlet of the blade of rectifier 90;

[0064] - a second lubricant inlet 212 intended to be supplied with lubricant leaving the rectifier blade 90;

[0065] - a second lubricant outlet 213 intended to supply an inlet of the reducer 19.

[0066] More particularly and as visible, the hydraulic distributor 2 comprises a hollow cylindrical body 21 carrying the first lubricant inlet 210, the first lubricant outlet 211, the second lubricant inlet 212, and the second lubricant outlet 213.

[0067] The circulation circuit can also be equipped with non-return valves so as to guide the direction of circulation of the lubricant between these inlets and these outlets.

[0068] According to the invention, the distributor 2 comprises a passive control member, intended to be pressure-controlled by lubricant leaving the exchanger, between a circulation position allowing a first communication between the first lubricant inlet and the first lubricant outlet as well as a second communication between the second lubricant inlet and the second lubricant outlet, and a bypass position breaking the first communication, this bypass position being reached when the lubricant pressure applied to the control member falls below a predetermined value.

[0069] Figures 2 and 4 illustrate the hydraulic distributor in the circulation position while Figures 3 and 5 illustrate the hydraulic distributor in the bypass position.

[0070] Therefore, in the embodiment presented, the distributor 2 comprises a passive control member 23, intended to be pressure-driven by lubricant exiting the rectifier vane 90, between a circulation position allowing a first communication between the first lubricant inlet 210 and the first lubricant outlet 211 as well as a second communication between the second lubricant inlet 212 and the second lubricant outlet 213, and a bypass position breaking the first communication, this bypass position being reached when the lubricant pressure applied to the passive control member 23 falls below a predetermined value.

[0071] This predetermined value is here between 0 bar and a minimum operating pressure of the lubricant circulation circuit.

[0072] This minimum pressure, as well as a maximum pressure, constitute two limits, respectively lower and upper, of a working pressure of the lubricant circulation circuit depending on the type of turbomachine.

[0073] This predetermined value may for example be equal to a quarter of the minimum pressure so as to protect against a total breakage of the circuit on a given blade, due to the fact that a leak of all the lubricant passing through this blade is observable by a total drop in pressure.

[0074] It would also be possible to provide a predetermined value relatively close to the minimum pressure so as to detect the slightest drop, even slight, in pressure in the lubricant circulation circuit.

[0075] Such a value thus makes it possible to detect the integrity or, on the contrary, the failure of the rectifier vane so that the hydraulic distributor switches from the circulation position to the bypass position.

[0076] The passive control member may, depending on the embodiments, be a hydraulic or electro-hydraulic control member so that it can also be manually operated remotely by an operator or a user.

[0077] In order to allow these authorizations or breaks in communication within the hydraulic device, the hydraulic device according to the embodiment presented comprises a piston 22 arranged in the hollow cylindrical body 21, and comprising a plurality of partitions 220, 221, 222.

[0078] These partitions 220, 221, 222 and the hollow cylindrical body 21 here form two watertight compartments 24E, 24s.

[0079] In order to make the compartments watertight, O-rings may be provided on the outside of the partitions in contact with an interior surface of the hollow cylindrical body.

[0080] As can be seen, the piston 22 is mounted movably in the hollow cylindrical body 21 so that in the circulation position, illustrated in FIGS. 2 and 4, the first communication between the first inlet 210 and the first outlet 211 passes through a first sealed compartment 24E of the sealed compartments 24E, 24s, and the second communication between the second inlet 212 and the second outlet 213 passes through a second sealed compartment 24s of the sealed compartments 24E, 24s. On the contrary, in the bypass position, the first communication is broken and the first inlet 210 and first outlet 211 are not connected by a compartment formed by the piston partitions and the hollow cylindrical body.

[0081] In this embodiment, in the bypass position, the first communication and the second communication are broken, and a third communication is established between the first lubricant inlet 210 and the second lubricant outlet 213.

[0082] In this way, this makes it possible to redirect the lubricant arriving via the first inlet to the second outlet and therefore to short-circuit a part of the faulty lubrication circuit by limiting lubricant losses, and therefore also pressure losses in the lubrication circuit.

[0083] According to embodiments, it could also be provided to implement an additional safety means in the form of one or more valves making it possible to modify the lubricant circulation circuit in response to an anomaly detected at the level of a hydraulic distributor and therefore of a rectifier blade.

[0084] For example, it could be planned to implement a valve at the first lubricant outlet.

[0085] It could also be provided to implement an automatically closing valve at the second lubricant inlet so as to limit the injection of air into the lubricant circulation circuit.

[0086] Such valves can in particular be controlled automatically, electronically, using a sensor to detect a fault and a programmable component to trigger a valve closing sequence.

[0087] In order to move from the bypass position to the circulation position, the hydraulic device further comprises a return spring 25 controlled by the passive control member 23.

[0088] More precisely, here, the passive control member 23 is configured to compress the return spring 25 so as to slide the piston 22 in the hollow cylindrical body 21 from the bypass position to the circulation position, when the lubricant pressure applied to the control member is above said predetermined value.

[0089] Thus, in other words, the default position of this hydraulic device is the bypass position. This makes it possible to add safety because if the passive control member fails and is no longer supplied, the return spring is decompressed and the hydraulic device is in the bypass position.

[0090] Furthermore, the time that the passive control member is not sufficiently supplied, that is to say the time that the lubricant pressure applied to the control member is not above, or even at least equal to, said predetermined value, the return spring is not compressed enough and the hydraulic device is still in the bypass position.

[0091] The switching between the bypass position and the circulation position therefore takes place, in this embodiment, when the predetermined value of the lubricant pressure applied to the control member is reached.

[0092] It should be noted that the hydraulic device can also be equipped with sensors making it possible to measure the lubricant pressure applied to the control member so as to provide, in parallel, information which can be numerical or visual to an operator or a user.

[0093] According to an embodiment not illustrated, the hydraulic device may also comprise cooling means.

[0094] Such cooling means can make it possible to increase the cooling capacity of the lubricant. This cooling can be done passively (for example with radiator fins on an outer surface of the hollow cylinder body), or actively (for example by means of a fan, one or more Peletier effect plates).

[0095] Such additional cooling can also be achieved through heat exchange with other nearby fluid circulation circuits.

Claims

Claims

1. Hydraulic distributor (2) intended to be arranged within a lubricant circulation circuit for an aircraft turbomachine, between a device to be lubricated (19) and a heat exchanger (9) through which the lubricant passes, the hydraulic distributor (2) comprising: - a first lubricant inlet (210) intended to be supplied with lubricant leaving the device to be lubricated (19); - a first lubricant outlet (211) intended to supply an inlet of the exchanger (9); - a second lubricant inlet (212) intended to be supplied with lubricant leaving the exchanger (9); - a second lubricant outlet (213) intended to supply an inlet of the device to be lubricated (19);the distributor (2) comprising a passive control member (23), intended to be pressure-controlled by lubricant leaving the exchanger (9), between a circulation position allowing a first communication between the first lubricant inlet (210) and the first lubricant outlet (211) as well as a second communication between the second lubricant inlet (212) and the second lubricant outlet (213), and a bypass position breaking the first communication, this bypass position being reached when the lubricant pressure applied to the control member falls below a predetermined value.;

2. Hydraulic distributor (2) according to claim 1, characterized in that it comprises a hollow cylindrical body (21) carrying said first lubricant inlet (210), said first lubricant outlet (211), said second lubricant inlet (212), and said second lubricant outlet (213).

3. Hydraulic distributor (2) according to claim 2, characterized in that it comprises a piston (22) arranged in said hollow cylindrical body (21), and comprising a plurality of partitions (220, 221, 222), said partitions (220, 221, 222) and said hollow cylindrical body (21) forming at least two sealed compartments (24E, 24s), said piston (22) being mounted movably in said hollow cylindrical body (21) so that in said circulation position, said first communication between the first inlet (210) and the first outlet (211) passes through a first sealed compartment (24E) of said sealed compartments (24E, 24s), and said second communication between the second inlet (212) and the second outlet (213) passes through a second sealed compartment (24s) of said sealed compartments (24E, 24s).

4. Hydraulic distributor (2) according to claim 3, characterized in that, in the bypass position, the first communication and the second communication are broken, and a third communication is established between the first lubricant inlet (210) and the second lubricant outlet (213).

5. Hydraulic distributor (2) according to one of claims 3 or 4, characterized in that it further comprises a return spring (25) controlled by said passive control member (23), said passive control member (23) being configured to compress said return spring (25) so as to slide said piston (22) in said hollow cylindrical body (21) from said bypass position to said circulation position, when the lubricant pressure applied to the control member is above said predetermined value.

6. Hydraulic distributor (2) according to one of the preceding claims, characterized in that it further comprises cooling means.

7. Assembly for an aircraft turbomachine, comprising a lubricant circulation circuit for an aircraft turbomachine connecting at least one device to be lubricated (19) and a heat exchanger (9) through which the lubricant passes, the assembly comprising at least one hydraulic distributor (2) according to one of claims 1 to 6, said hydraulic device (2) being intended to be arranged within said lubricant circulation circuit, between said device to be lubricated (19) and said heat exchanger (9).

8. Aircraft turbomachine assembly according to the preceding claim, said device to be lubricated being a reducer (19) and said heat exchanger being an air flow straightener (9) comprising at least one straightener blade (90).

9. Aircraft turbomachine assembly according to the preceding claim, characterized in that said air flow straightener (9)

10. comprises several rectifier vanes (90), and in that each of said rectifier vanes (90) is connected to said reducer (19) by an independent hydraulic device (2). Aircraft turbomachine, characterized in that it comprises an assembly according to one of claims 7 to 9.

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