Aircraft turbine engine comprising an assembly having an accessory gearbox and a device

Abstract

The invention relates to an aircraft turbine engine comprising an assembly (14) having: - an accessory gearbox (16) comprising a casing (17) that has first and second walls (18, 19), and a gear (20a, 20b); - a device (21, 22) externally attached to a receiving wall, wherein the device (21, 22) comprises a rotor (21a, 22a) driven by the gear (20a, 20b) via a first transmission shaft (23); wherein the accessory gearbox (16) internally comprises a first pump (24, 28) arranged axially between the gear (20a, 20b) and the device (21, 22), wherein the first pump (24, 28) is housed in a first cavity in the casing (17), wherein the first pump (24, 28) comprises a first rotor rotatably connected to the first transmission shaft (23), and wherein the first cavity is formed in a first support of the casing (17) which projects axially inward from the receiving wall, the first support being integral with the receiving wall.

Description

[0001] DESCRIPTION

[0002] TITLE: TU RBOMACHI NE D'AERONEF COMPRISING A SET CONTAINING AN ACCESSORY CASE AND EQUIPMENT

[0003] Technical field of the invention

[0004] The present invention relates to an aircraft turbomachine comprising an assembly including an accessory housing and equipment.

[0005] Technical background

[0006] An aircraft turbomachine includes various transmission (e.g., gears) and guidance (e.g., roller bearings or hydrodynamic bearings) components that are lubricated with lubricant (usually oil) via a lubrication system, ensuring proper operation and minimizing wear. The lubrication system comprises a lubrication circuit through which the lubricant circulates via a lubrication unit. The lubrication unit is mounted on and rotated by an accessory gearbox. The accessory gearbox is known by the acronym AGB, for "Accessory Gearbox." The lubrication unit includes a supply pump and a scavenging pump. Specifically, the supply pump delivers the lubricant from the reservoir to the various components requiring lubrication.The recovery pump, meanwhile, allows the oil to be conveyed from the enclosures in which the parts to be lubricated are placed to the lubricant reservoir.

[0007] Engine manufacturers are now finding that the lubrication system is a reliable device that requires little maintenance.

[0008] In addition, engine manufacturers seek to reduce the size and mass of the various equipment (especially the lubrication unit) attached to the accessory box, in order to generally optimize the overall performance of the turbomachine, and possibly incorporate new or larger equipment, to cope with new constraints (for example, higher electrical consumption of the aircraft).

[0009] The objective of the present invention is therefore to provide a simple, effective, and economical solution to the aforementioned problem. Prior art includes documents JP2001317375A, US2024 / 093773A1, US7040082B2, and US10415691 B2.

[0010] Summary of the invention

[0011] The invention thus proposes an aircraft turbomachine comprising an assembly including:

[0012] - an accessory housing comprising a casing having first and second walls opposite each other, the accessory housing comprising internally a movable gear rotating around an axis A, B and arranged axially between the first and second walls;

[0013] - Equipment mounted externally on a receiving wall selected from the first and second walls of the housing, the equipment comprising a rotor driven in rotation by the gear via a first transmission shaft; characterized in that the accessory housing internally comprises a first pump arranged axially between the gear and the equipment, the first pump being housed in a first cavity of the housing, the first pump comprising a first rotor connected in rotation with the first transmission shaft, the first cavity being formed in a first support of the housing which projects axially inwards from the receiving wall, the first support being integral with the receiving wall. The integration of the pump into the accessory housing between the gear and the equipment allows for significant size and weight reductions, benefiting the overall performance of the turbomachine.In addition, such gains in size and mass make it possible to consider incorporating new or larger equipment to cope with new constraints (for example, higher electrical consumption of the aircraft).

[0014] Such integration also makes it possible to consider the integration of the various accessories (filters, strainers, valves, sensors, pipes, etc.) which are associated with the pump, in order to further maximize the gains in size and mass.

[0015] Such integration also allows the pump to be freely associated with one of the gears of the accessory housing, and in particular with a gear whose rotation speed is high, in order to reduce the displacement of the pump, and therefore to reduce the overall size of the function.

[0016] Such integration of the pump is not problematic from a maintenance point of view since the pump is a reliable device that requires little maintenance.

[0017] Finally, the pump draws in and expels lubricant which is also used to lubricate the various components of the accessory housing, facilitating the implementation of certain functions, including the integration of pipes and sealing.

[0018] The turbomachine according to the invention may comprise one or more of the following features, taken individually or in combination with each other:

[0019] - the first cavity is axially delimited by a bottom wall of the first support at a distal end of the first support and by a first cap attached to the receiving wall at a proximal end of the first support;

[0020] - the equipment is attached externally to an interface formed on the receiving wall, the interface surrounding the first cap;

[0021] - the gear wheel is guided in rotation relative to the housing via a first bearing and a second bearing arranged axially on either side of the gear wheel, the first bearing being housed at least partly in a housing which is formed externally in the first support and at a distal end of the first support;

[0022] - the first pump includes an inlet and an outlet formed at least partly in the first support;

[0023] - the inlet and outlet of the first pump are each connected to an internal pipe, the internal pipes being placed in the casing of the accessory box;

[0024] - the first pump comprises several first modules arranged axially next to each other, each first module comprising a rotating movable element which is arranged axially between two fixed flanges;

[0025] - the accessory housing includes internally a second pump which is arranged axially between the toothed wheel and a non-receiving wall which corresponds to the unselected wall among the first and second walls of the housing, the second pump being housed in a second cavity of the housing, the second pump comprising a second rotor which is driven in rotation by the toothed wheel;

[0026] - the second cavity is formed in a second support of the casing which protrudes axially inwards from the non-receiving wall, the second support being in one piece with the non-receiving wall;

[0027] - the second cavity is axially delimited by a bottom wall of the second support at a distal end of the second support and by a second cap attached to the non-receiving wall at a proximal end of the second support.

[0028] Brief description of the figures

[0029] The invention will be better understood and other details, features and advantages of the invention will become more apparent from the reading of the following description given by way of non-limiting example and with reference to the accompanying drawings in which: [Fig.1] Figure 1 is a schematic view in longitudinal half-section of a turbomachine comprising an assembly according to the invention;

[0030] [Fig.2] Figure 2 is a schematic view of the accessory box equipped with its equipment;

[0031] [Fig.3] Figure 3 is a front view of the accessory housing;

[0032] [Fig.4] Figure 4 is a cross-sectional view of the accessory housing according to the section plane IV-IV of Figure 2, which illustrates a first example of an embodiment of the invention;

[0033] [Fig.5] Figure 5 is a cross-sectional view of the accessory housing according to section plane IV-IV of Figure 2, which illustrates the first embodiment example;

[0034] [Fig.6] Figure 6 is a detailed exploded view illustrating the integration of the second pump in the first embodiment example;

[0035] [Fig.7] Figure 7 is a view similar to Figure 6 in which the first cover has been hidden;

[0036] [Fig.8] Figure 8 is a perspective view of the accessory case which illustrates the first embodiment and a second embodiment of the invention;

[0037] [Fig.9] Figure 9 is a side view of the accessory case which illustrates the first and second implementation examples;

[0038] [Fig.10] Figure 10 is a detailed exploded view illustrating the integration of the first pump in the second embodiment example;

[0039] [Fig.11] Figure 11 is a detail view illustrating the integration of a pump flange into a bottom wall of the crankcase.

[0040] Detailed description of the invention

[0041] Figure 1 schematically represents a turbomachine 1 with longitudinal axis X for an aircraft 2, such as an airplane.

[0042] The turbomachine 1 comprises a movable, unducted fan 3 and a fixed, unducted stator 4. Such a turbomachine 1 is more commonly known by the English acronym USF for "Unducted Single Fan". As illustrated in Figure 1, the fan 3 rotates about the X-axis. The fan 3 is driven in rotation by a power turbine 5 coupled to a gas generator 6, the power turbine 5 and the gas generator 6 both being located downstream of the fan 3. The fan 3 is driven in rotation by the power turbine 5 via a speed reducer 7. The speed reducer 7 reduces the rotational speed of the fan 3 relative to that of the power turbine 5, while simultaneously increasing its torque. The speed reducer 7 is, for example, an epicyclic gear reducer. The blower 3 has an annular row of blades 8 with fixed or variable pitch.

[0043] The straightener 4 is fixed in rotation about the X axis. The straightener 4 is configured to straighten at least part of the airflow F generated by the blower 3. The straightener 4 is arranged here directly downstream of the blower 3. The straightener 4 comprises an annular row of guide vanes 9 with fixed or variable pitch.

[0044] The gas generator 6 conventionally comprises, from upstream to downstream along the direction of airflow F, at least one compressor, one combustion chamber, and at least one expansion turbine (or high-pressure turbine). The rotors of a compressor and an expansion turbine of the same housing are rotationally linked to each other via a drive shaft. When the turbomachine 1 operates in "propulsion" mode, the fan 3 generates an airflow F which splits into a minor primary flow f1 and a major secondary flow f2. The minor primary flow f1 enters a closed primary channel 10 of the engine via an air inlet 11 located between the fan 3 and the rectifier 4, so as to supply the gas generator 6. The major secondary flow f2, on the other hand, flows around the fairings of the nacelle 12 in an open secondary channel 13, so as to propel the aircraft 2.

[0045] The turbomachine 1 further includes an assembly 14 which is arranged in an intervein compartment 15, the intervein compartment 15 being placed radially between the closed primary vein 10 and the open secondary vein 13.

[0046] The example illustrated in Figure 1 is in no way limiting; the assembly 14 according to the invention could be placed in another location and in other types of turbomachine 1, for example a turboprop, a turbojet, a turbomotor, or even a turbomachine generally comprising one or more shrouded or unshrouded fans.

[0047] Set 14 includes:

[0048] - an accessory housing 16 comprising a casing 17 having first and second walls 18, 19 opposite each other, the accessory housing 16 comprising internally a toothed wheel 20a, 20b movable in rotation around an axis A, B and arranged axially between the first and second walls 18, 19;

[0049] - Equipment 21, 22 (or accessory) externally mounted on a receiving wall selected from the first and second walls 18, 19 of the housing 17, equipment 21, 22 comprising a rotor 21a, 22a driven in rotation by the gear 20a, 20b via a first transmission shaft 23. According to the invention, the accessory housing 16 internally comprises a first pump 24, 28 arranged axially between the gear 20a, 20b and equipment 21, 22. The first pump 24, 28 is housed in a first cavity 32 of the housing 17. The first pump 24, 28 comprises a first rotor 24a, 28a rotationally connected to the first transmission shaft 23. The first cavity 32 is formed in a first support 34 (or first boss) of the The housing 17 projects axially inwards from the receiving wall (first wall 18 or second wall 19 depending on the equipment). The first support 34 is a single piece (or monobloc) with the receiving wall.

[0050] The integration of the pump 24, 28 into the accessory housing 16 between the gear 20a, 20b and the equipment 21, 22 allows for significant size and mass savings, to the benefit of the overall performance of the turbomachine 1. In addition, such size and mass savings make it possible to consider the incorporation of new or larger equipment, to cope with new constraints (for example, a higher electrical consumption of the aircraft).

[0051] Such integration also allows for the integration of the various accessories (filters, strainers, valves, sensors, pipes, etc.) which are associated with the pump 24, 28, in order to further maximize the gains in size and mass.

[0052] Such integration also allows the pump 24, 28 to be freely associated with one of the gears of the accessory housing 16, and in particular with a gear whose rotation speed is high, in order to reduce the displacement of the pump, and therefore to reduce the overall size of the function.

[0053] Such integration of pump 24, 28 is not problematic from a maintenance point of view since the pump is a reliable device which requires little maintenance operations.

[0054] Finally, the pump 24, 28 draws in and discharges lubricant which is also used to lubricate the various elements of the accessory housing 16, which facilitates the implementation of certain functions, including the integration of pipes and sealing.

[0055] By convention in this application, "axial" or "axially" means any direction parallel to the axis A, B of the gear 20a, 20b or to the axis X of the turbomachine 1, and "radial" or "radially" means any direction perpendicular to the axis A, B of the gear 20a, 20b or to the axis X of the turbomachine 1.

[0056] Advantageously, as illustrated in Figure 2, the gear 20a, 20b is part of a gear train 33 comprising a plurality (or cascade) of gears located inside the housing 17 and meshed with each other. The equipment (or accessory) is arbitrary and can thus correspond to any of the equipment mounted on the housing 17, for example, a pump (lubricant or fuel) or an electric generator / motor.

[0057] Advantageously, as illustrated in figures 4 and 5, the first cavity 32 is axially delimited by a bottom wall 35 of the first support 34 at a distal end of the first support 34 and by a first cap 36 attached to the receiving wall at a proximal end of the first support 34.

[0058] Alternatively, the first cavity 32 could be axially delimited by two caps.

[0059] Advantageously, as illustrated in figures 4, 5 and 8-10, the equipment 21, 22 is externally attached to an interface 37, 38 formed on the receiving wall, the interface 37, 38 surrounding the first cap 36. The interface 37, 38 is for example formed by an annular boss on which the equipment is placed and held in position.

[0060] The accessory housing 16 can internally include a second pump 26, 30 which is arranged axially between the gear wheel 20a, 20b and a non-receiving wall which corresponds to the unselected wall among the first and second walls 18, 19 of the housing 17. The second pump 26, 30 is housed in a second cavity 39 of the housing 17. The second pump 26, 30 includes a second rotor 26a which is driven in rotation by the gear wheel 20a, 20b.

[0061] Advantageously, as illustrated in figures 4 to 6, the second cavity 39 is formed in a second support 40 of the housing 17 which projects axially inwards from the non-receiving wall, the second support 40 being in one piece with the non-receiving wall.

[0062] Advantageously, as illustrated in figures 4 to 6, the second cavity 39 is axially delimited by a bottom wall 41 of the second support 40 at a distal end of the second support 40 and by a second cap 42 attached to the non-receiving wall at a proximal end of the second support 40. Alternatively, the second cavity 39 could be axially delimited by two caps.

[0063] Advantageously, as illustrated in figures 4 and 5, the gear 20a, 20b is guided in rotation relative to the housing 17 via a first bearing 43 and a second bearing 44 arranged axially on either side of the gear 20a, 20b.

[0064] The first bearing 43 can be housed at least in part in a first housing 45 which is formed externally in the first support 34 and at a distal end of the first support 34.

[0065] The second bearing 44 can be housed at least in part in a second housing 46 which is formed externally in the second support 40 and at a distal end of the second support 40.

[0066] The first pump 24, 28 can be a lubricant supply pump or a lubricant recovery pump. Similarly, the second pump 26, 30 can be a lubricant supply pump or a lubricant recovery pump.

[0067] The first and second pumps 24, 26, 28, 30 can be Gerotor pumps, vane pumps, or any type of pump consisting of discs placed side by side. The aforementioned pumps have the advantage of being extremely compact.

[0068] A feed pump allows the lubricant to be conveyed from the lubricant reservoir to the various elements to be lubricated located in different enclosures of the turbomachine 1.

[0069] A recovery pump allows the lubricant to be conveyed from one or more chambers of the turbomachine 1, in which elements to be lubricated are placed, to the lubricant reservoir.

[0070] A pump 24, 26, 28, 30 may comprise one or more modules 25, 27, 29, 31 arranged axially side by side, each module 25, 27, 29, 31 comprising a rotating element 25a, 27a, 29a which is arranged axially between two fixed flanges 25b, 27b, 29b. When a pump comprises several modules, the moving elements of the different modules form part of the rotor of the corresponding pump.

[0071] As illustrated in Figure 11, a pump module 25, 27, 29, 31 which is directly adjacent to a bottom wall 35, 41 of a support 34, 40 may have one of two flanges 25b, 27b, 29b which is formed in the bottom wall 35, 41, so as to minimize the axial footprint of the pump.

[0072] Similarly, a pump module 25, 27, 29, 31 which is directly adjacent to a cap 36, 42 may have one of the two flanges 25b, 27b, 29b which is formed in the cap 36, 42, so as to minimize the axial footprint of the pump.

[0073] Advantageously, as illustrated in Figures 4 and 5, the first transmission shaft 23 comprises a first end which is rotationally linked with the gear 20a, 20b and a second end which is rotationally linked with the rotor 21a, 22a of the equipment 21, 22.

[0074] Advantageously, the second rotor 26a of the second pump 26, 30 is driven in rotation by the gear 20a, 20b via a second transmission shaft 47. The second transmission shaft 47 can be linked in rotation with the gear 20a, 20b or with the first transmission shaft 23. Two elements are for example linked in rotation via connecting means (such as splines) or by shrink fitting.

[0075] The first and second drive shafts 23, 47 can be guided in rotation relative to the housing 17 via one or more bearings (for example, plain bearings). A drive shaft 23, 47 is, for example, guided in rotation relative to the corresponding bottom wall via a first bearing and relative to the corresponding cap via a second bearing.

[0076] Advantageously, the first pump 24, 28 includes an inlet 48a, 50a and an outlet 48b, 50b formed at least partly in the first support 34.

[0077] Advantageously, in the same way, the second pump 26, 30 includes an inlet 49a and an outlet 49b formed at least partly in the second support 40. The inlet and outlet of a pump are, for example, each formed by a radial orifice made in the corresponding support.

[0078] The inlets of the first and second pumps 24, 26, 28, 30 can be connected to a common inlet port which is formed in the housing 17. The inlet port is intended to be connected to an external pipeline which can be partially formed in the housing 17.

[0079] The inlets of the first and second pumps 24, 26, 28, 30 are then connected to the inlet port via one or more internal pipes 78. The internal pipe(s) 78 may be formed partly or entirely within the housing 17, or may be separate from the housing 17.

[0080] The outlets of the first and second pumps 24, 26, 28, 30 can be connected to a common outlet port which is formed in the housing 17. The outlet port is intended to be connected to an external pipeline which can be partially formed in the housing 17.

[0081] The outlets of the first and second pumps 24, 26, 28, 30 are then connected to the outlet port via one or more internal pipes 79. The internal pipe(s) 79 may be formed partly or entirely within the housing 17, or may be separate from the housing 17.

[0082] Advantageously, the arrangement of the internal pipes 78, 79 in the accessory box 16 (particularly around the pumps 24, 28) will allow lubricant (or oil) to be sent to the equipment 21, 22 from its interface 37, 38. Such an arrangement will make it possible to replace an external flexible pipe which would bring lubricant from the supply circuit to the equipment 21, 22.

[0083] One or more accessories (filters, strainers, valves, sensors, pipes, etc.) can be associated with the first and second pumps. The accessory(ies) can be formed partially or entirely within the housing 17.

[0084] According to the embodiment illustrated in the figures, the first and second walls 18, 19 are axially connected to each other by a peripheral wall 51. The housing 17 comprises a frame 52, and first and second covers 53, 54 attached to the frame 52. The frame 52 is a solid part obtained, for example, by molding or additive manufacturing. The first wall 18 is partly formed by the frame 52 and partly by the first cover 53. The second wall 19 is also partly formed by the frame 52 and partly by the second cover 54. The frame 52 also includes several brackets 55, to allow its attachment to a structural housing of the turbomachine 1.

[0085] According to the embodiment illustrated in the figures, the gear wheels 20a, 20b are part of a gear train 33 comprising a plurality (or cascade) of gear wheels placed inside the housing 17 and meshed with each other.

[0086] The gear train 33 is rotationally coupled with a rotor of the gas generator 6 via an input gearbox 56 (also known by the English acronym IGB for "Inlet GearBox" >>), a radial drive shaft 57 (also known by the English acronym RDS for "Radial Drive Shaft"), a transfer gearbox 58 (also known by the English acronym TGB for "Transfer GearBox") and a horizontal drive shaft 59 (also known by the English acronym HDS for "Horizontal Drive Shaft").

[0087] Gears are mostly coupled in rotation with the rotors of various equipment (or accessories), to drive them or to be driven by them.

[0088] More specifically, as illustrated in particular in Figure 2, the toothed wheel 20a is coupled in rotation with the rotor 21a of the main fuel pump 21 (also known by the English acronym MFP for "Main Fuel Pump" >>) via a first drive shaft 23. The main fuel pump 21 is attached externally to the second wall 19 of the housing 17.

[0089] The toothed wheel 20b is coupled in rotation with the rotor 22a of an integrated drive generator 22 (also known by the English acronym IDG for "Integrated Driven Generator" >>) via a first drive shaft 23. The integrated drive generator 22 is externally attached to the first wall 18 of the housing 17.

[0090] The toothed wheel 20c is coupled in rotation with the rotor of an air turbine starter 60 (also known by the English acronym ATS for "Air Turbine Starter" >>) which is externally reported on the first wall 18 of the housing 17.

[0091] The gear 20d is rotationally coupled with the rotor of a lubricant supply pump 61. The supply pump 61 delivers the lubricant from the lubricant reservoir to the various components to be lubricated located in different enclosures of the turbomachine 1. The supply pump 61 is located inside the housing 17. The supply pump 61 is associated with a filter 62 which is located downstream of the outlet of the supply pump 61, following the direction of lubricant flow. The filter 62 is associated with a pressure relief valve 63, a bypass valve 64, and a differential pressure sensor 65. The gear 20d is also rotationally coupled with the rotor of a lubricant recovery pump 66. The recovery pump 66 allows the lubricant to be conveyed from one or more chambers of the transfer case 58, in which elements to be lubricated are placed, to the lubricant reservoir.The recovery pump 66 is located inside the casing 17.

[0092] The toothed wheel 20e is coupled in rotation with the rotor of a permanent magnet alternator 67 (also known by the English acronym PMA for "Permanent Magnet Alternator" >>) which is externally attached to the second wall 19 of the casing 17.

[0093] The toothed wheel 20f is coupled in rotation with a hand crank drive end 68 (also known by the English acronym HCP for "Hand Crank Pad") which is attached externally to the first wall 18 of the housing 17.

[0094] The toothed wheel 20g is coupled in rotation with the rotor of a hydraulic pump 69 (also known by the English acronym EDP for "Engine Driven Pump" >>) which is externally attached to the first wall 18 of the housing 17.

[0095] The various equipment 21, 22, 60, 67-69 (or accessories) attached to the first and second walls 18, 19 of the housing 17 are not part of the accessory housing 16.

[0096] According to the embodiment illustrated in the figures, and in particular Figures 2, 4, and 5, the gear 20a is double and free to rotate about an axis A. The gear 20a thus comprises an internal hub 70, a first external tooth 71, and a second external tooth 72. The teeth 71 and 72 are axially separated from each other. The first and second teeth 71 and 72 are respectively radially connected to the internal hub 70 via first and second webs 73 and 74. The gear 20b is single and free to rotate about an axis B. The gear 20b thus comprises an internal hub and an external tooth 76 which are radially connected to each other via a web 77.

[0097] Compared to previous art, the axial dimension of the internal hubs 70 has been significantly reduced to allow the integration of the pumps within the housing.

[0098] According to the first embodiment of the invention, the accessory housing 16 internally comprises a first pump 24, which is axially arranged between the gear 20a and the main fuel pump 21. The first pump 24 is a lubricant recovery pump. Here, the first pump 24 conveys lubricant from the rear chambers of the turbomachine 1, in which components to be lubricated are located, to the lubricant reservoir. The fuel pump 21 is externally mounted on an interface 37 formed on the second wall 19 (receiving wall).

[0099] As illustrated in the figures, particularly Figures 4 and 5, the first pump 24 is housed in the first cavity 32 of the housing 17. The first cavity 32 is formed in a first support 34 of the housing 17, which projects axially inwards from the second wall 19 (receiving wall). The first support 34 is integral with a portion of the second wall 19, which is formed in the frame 52. The first pump 24 is located axially between the second wall 19 and the gear 20a. The first cavity 32 is axially delimited by a bottom wall 35 of the first support 34 at a distal end of the first support 34 and by a first cap 36 attached to the second wall 19 at a proximal end of the first support 34. The first cap 36 is surrounded by the interface 37, which receives the fuel pump 21. The first transmission shaft 23 is rotationally linked with the toothed wheel 20a via complementary splines.According to the first embodiment, the accessory housing 16 further includes internally a second pump 26 which is arranged axially between the gear 20a and the first wall 18 (non-receiving wall). The second rotor 26a of the second pump 26 is driven in rotation by the gear 20a. The second pump 26 is also a lubricant recovery pump. The second pump 26 also allows lubricant to be conveyed from rear compartments of the turbomachine 1, in which components to be lubricated are located, to the lubricant reservoir.

[0100] As illustrated in the figures, particularly Figures 4 and 5, the second pump 26 is housed in a second cavity 39 of the housing 17. This second cavity 39 is formed in a second support 40 of the housing 17, which projects axially inwards from the first wall 18 (the non-receiving wall). The second support 40 is integral with a portion of the first wall 18, which is formed in the first cover 53. The second pump 26 is located axially between the first wall 18 and the gear 20a. The second cavity 39 is axially delimited by a bottom wall 41 of the second support 40 at a distal end of the second support 40 and by a second cap 42 attached to the first wall 18 at a proximal end of the second support 40. The second rotor 26a of the second pump 26 is driven in rotation by the toothed wheel 20a via a second transmission shaft 47.As illustrated in the figures and in particular figures 4 and 5, the gear wheel 20a is guided in rotation relative to the housing 17 via a first bearing 43 and a second bearing 44 arranged axially on either side of the gear wheel 20a.

[0101] The first bearing 43 is arranged axially between the first web 73 and the first pump 24. The first bearing 43 is housed partly in a first housing 45 which is formed externally in the first support 34 and at the distal end of the first support 34. The first bearing 43 comprises an outer ring housed partly in the first housing 45, an inner ring attached to a first bearing surface of the hub 70 of the gear 20a and rolling elements (here rollers) arranged between the outer and inner rings.

[0102] The second bearing 44 is arranged axially between the second web 74 and the second pump 26. The second bearing 44 is housed partly in a second housing 46 which is formed externally in the second support 40 and at the distal end of the second support 40. The second bearing 44 comprises an outer ring housed partly in the second housing 46, an inner ring attached to a second bearing surface of the hub 70 of the gear 20a and rolling elements (here rollers) arranged between the outer and inner rings.

[0103] According to the first embodiment, the first pump 24 comprises a single first module 25. The first module 25 includes a rotatable element 25a which is axially arranged between two fixed flanges 25b. The flange 25b of the first module 25 that is directly adjacent to the bottom wall 35 of the first support 34 is formed in the bottom wall 35. The flange 25b of the first module 25 that is directly adjacent to the first cap 36 is formed in the first cap 36. The first pump 24 includes an inlet 48a and an outlet 48b, both formed entirely within the first support 34.

[0104] According to the first embodiment, the second pump 26 also comprises a single second module 27. The second module 27 includes a rotatable element 27a that is axially arranged between two fixed flanges 27b. The flange 27b of the second module 27 that is directly adjacent to the bottom wall 41 of the second support 40 is formed in the bottom wall 41. The flange 27b of the second module 27 that is directly adjacent to the second cap 42 is formed in the second cap 42. The second pump 26 includes an inlet 49a and an outlet 49b, both formed entirely within the second support 40.

[0105] According to the second embodiment of the invention, the accessory housing 16 includes internally a first pump 28 which is arranged axially between the gear wheel 20b and the integrated drive generator 22, and a second pump 30 which is arranged axially between the gear wheel 20b and the second wall 19 (non-receiving wall).

[0106] The first and second pumps 28 and 30 are lubricant recovery pumps. The first pump 28 conveys lubricant from the forward chambers of the turbomachine 1, in which components to be lubricated are located, to the lubricant reservoir. The second pump 30 conveys lubricant from the accessory housing 16 to the lubricant reservoir. The generator 22 is externally mounted on an interface 38 formed on the first wall 18 (receiving wall).

[0107] In the second embodiment, the first and second pumps 28, 30 are integrated into the housing 17 in the same way as the first and second pumps 24, 26 in the first embodiment. The first cap 36 is thus surrounded by the interface 38, which receives the generator 22. The gear 20b is guided in rotation in the same way as the gear 20a in the first embodiment.

[0108] According to the second embodiment, the first pump 28 comprises two first modules 29 arranged axially side by side. Each first module 29 comprises a rotatable element 29a arranged axially between two fixed flanges 29b. The rotatable elements 29a of the first two modules 29 form part of the first rotor 28a of the first pump 28. The first module 29 that is directly adjacent to the bottom wall 35 of the first support 34 has one of its two flanges 29b formed in the bottom wall 35. The first module 29 that is directly adjacent to the first cap 36 has one of its two flanges 29b formed in the first cap 36. The first pump 28 comprises an inlet 50a and an outlet 50b, both formed entirely within the first support 34. According to the second embodiment, the second pump 30 comprises a single second module 31. The second pump 30 includes an inlet and an outlet formed entirely within the second support 40.

[0109] According to the embodiment illustrated in the figures, the accessory housing 16 is delimited externally in particular by the casing 17 (the frame 52 and the first and second covers 53, 54) as well as by the first and second caps 36, 42 (at the level of the pumps 24, 26, 28, 30).

[0110] The inlets 48a, 49a, 50a of the pumps 24, 26, 28, 30 are connected to a common inlet port which is formed in the housing 17. The inlets 48a, 49a, 50a of the pumps 24, 26, 28, 30 are here connected to the inlet port via a common internal channel 78.

[0111] The outlets 48b, 49b, 50b of the pumps 24, 26, 28, 30 are connected to a common outlet port which is formed in the housing 17. The outlets 48b, 49b, 50b of the pumps 24, 26, 28, 30 are here connected to the outlet port via a common internal conduit 79.

Claims

DEMANDS 1. Aircraft turbomachine (1) (2) comprising an assembly (14) including: - an accessory housing (16) comprising a casing (17) having first and second walls (18, 19) opposite each other, the accessory housing (16) comprising internally a toothed wheel (20a, 20b) movable in rotation around an axis (A, B) and arranged axially between the first and second walls (18, 19); - equipment (21, 22) attached externally to a receiving wall which is chosen from the first and second walls (18, 19) of the casing (17), the equipment (21, 22) comprising a rotor (21a, 22a) driven in rotation by the toothed wheel (20a, 20b) via a first transmission shaft (23); characterized in that the accessory housing (16) internally comprises a first pump (24, 28) arranged axially between the gear (20a, 20b) and the equipment (21, 22), the first pump (24, 28) being housed in a first cavity (32) of the housing (17), the first pump (24, 28) comprising a first rotor (24a, 28a) linked in rotation with the first transmission shaft (23), the first cavity (32) being formed in a first support (34) of the housing (17) which projects axially inwards from the receiving wall, the first support (34) being integral with the receiving wall.

2. Turbomachine (1) according to claim 1, characterized in that the first cavity (32) is axially delimited by a bottom wall (35) of the first support (34) at a distal end of the first support (34) and by a first cap (36) attached to the receiving wall at a proximal end of the first support (34).

3. Turbomachine (1) according to the preceding claim, characterized in that the equipment (21, 22) is externally attached to an interface (37, 38) formed on the receiving wall, the interface (37, 38) surrounding the first cap (36).

4. Turbomachine (1) according to any one of claims 1 to 3, characterized in that the gear (20a, 20b) is guided in rotation relative to the housing (17) via a first roller bearing (43) and a second roller bearing (44) arranged axially on either side of the gear (20a, 20b), the first roller bearing (43) being housed at least in part in a housing (45) which is formed externally in the first support (34) and at a distal end of the first support (34).

5. Turbomachine (1) according to any one of claims 1 to 4, characterized in that the first pump (24, 28) comprises an inlet (48a, 50a) and an outlet (48b, 50b) formed at least partly in the first support (34).

6. Turbomachine (1) according to the preceding claim, characterized in that the inlet (48a, 50a) and outlet (48b, 50b) of the first pump (24, 28) are each connected to an internal pipe (78, 79), the internal pipes (78, 79) being placed in the casing (17) of the accessory housing (16).

7. Turbomachine (1) according to any one of the preceding claims, characterized in that the first pump (24, 28) comprises several first modules (25, 29) arranged axially next to each other, each first module (25, 29) comprising a rotationally movable element (25a, 29a) which is arranged axially between two fixed flanges (25b, 29b).

8. Turbomachine (1) according to any one of the preceding claims, characterized in that the accessory housing (16) internally comprises a second pump (26, 30) which is arranged axially between the gear (20a, 20b) and a non-receiving wall which corresponds to the non-receiving wall chosen from the first and second walls (18, 19) of the casing (17), the second pump (26, 30) being housed in a second cavity (39) of the casing (17), the second pump (26, 30) comprising a second rotor (26a) which is driven in rotation by the toothed wheel (20a, 20b).

9. Turbomachine (1) according to the preceding claim, characterized in that the second cavity (39) is formed in a second support (40) of the housing (17) which projects axially inwards from the non-receiving wall, the second support (40) being of one piece with the non-receiving wall.

10. Turbomachine (1) according to the preceding claim, characterized in that the second cavity (39) is axially delimited by a bottom wall (41) of the second support (40) at a distal end of the second support (40) and by a second cap (42) attached to the non-receiving wall at a proximal end of the second support (40).

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