KIT INCLUDING AN ACCESSORY BOX AND EQUIPMENT FOR AN AIRCRAFT TURBOMACHINE

Abstract

Assembly (10) comprising an accessory housing (12) and equipment (14) for an aircraft turbomachine (1), the accessory housing (12) comprising a gear train (20) having gears (22) meshed with each other and having axes of rotation (A) parallel to each other and to a main axis (Y), the equipment (14) comprising first pieces of equipment (14a) each having a shaft (24) parallel to said main axis (Y) and coupled to the gear train (20), the assembly (10) further comprising a relay housing (16) which is connected to the accessory housing (12) by a transfer shaft (18) parallel to said main axis (Y) and coupled to the gear train (20), characterized in that the equipment (14) comprises at least one second piece of equipment (14b) which has a shaft (32) perpendicular to said main axis (Y) and coupled to said transfer shaft (18). Abbreviated figure: figure 5

Description

Title of the invention: ASSEMBLY COMPRISING AN ACCESSORY HOUSING AND EQUIPMENT FOR AN AIRCRAFT TURBOMACHINE Technical field of the invention

[0001] The invention relates to an assembly comprising an accessory housing and equipment for an aircraft turbomachine, as well as an aircraft turbomachine comprising such an assembly. Technical background

[0002] The state of the art includes in particular document WO-A1-2015 / 140476.

[0003] As is well known, an aircraft turbomachine extends along a longitudinal axis and comprises, from upstream to downstream in the direction of gas flow, a fan, at least one compressor, an annular combustion chamber, at least one turbine, and finally a combustion gas exhaust nozzle. In the case of a twin-spool turbomachine, with low-pressure and high-pressure components respectively, the turbomachine comprises, between the fan and the nozzle, a low-pressure compressor, a high-pressure compressor, the combustion chamber, a high-pressure turbine, and a low-pressure turbine.

[0004] The high-pressure unit comprises a high-pressure shaft that connects the rotor of the high-pressure compressor to the rotor of the high-pressure turbine. The high-pressure shaft is tubular and axially traversed by the low-pressure shaft of the low-pressure unit. This low-pressure shaft connects the rotor of the low-pressure compressor to the rotor of the low-pressure turbine and is further connected, either directly or via a mechanical reducer, to the blower shaft.

[0005] The turbomachine generally comprises a primary flow path extending inside the engine and passing successively through the compressors, the combustion chamber and the turbines, and a secondary flow path extending around the engine, the primary and secondary flows being generated by the blower and separated from each other downstream of the blower.

[0006] An accessory gearbox for a turbomachine is known by the English acronym AGB for "Accessory GearBox". An accessory gearbox is designed to transmit mechanical power from the turbomachine's engine (or gas generator) to equipment such as a pump, an alternator-starter, an air / oil separator, etc. The accessory gearbox comprises a gear train, and each piece of equipment is mounted directly onto the gearbox and has a shaft coupled to this gear train for its rotational drive.

[0007] The gear train is connected to one of the engine shafts via a return shaft, a gearbox, and a transfer shaft. The return shaft extends substantially radially with respect to the longitudinal axis of the turbomachine and comprises a radially internal end coupled to the engine shaft and a radially external end coupled to one end of the transfer shaft by the gearbox. The gearbox is located at a distance from the accessory gearbox, and the transfer shaft provides the connection between these gearboxes and, in particular, the coupling of the return shaft to the gear train.

[0008] In current technology, the accessory housing is generally mounted around a blower housing that surrounds the blower. A disadvantage of the accessory housing's position in this area is that the equipment driven by the accessory housing is also located in this area.

[0009] There is a need to integrate this type of accessory housing as close as possible to the engine, and in particular radially within the secondary flow path that extends around the engine downstream of the fan. This is notably the case in an unfaired propeller turbomachine that does not include a fan casing.

[0010] However, the current architecture of an accessory housing and its connection to the equipment does not allow for the integration of these elements as close as possible to the engine. This difficulty is compounded by the fact that the equipment is becoming increasingly bulky, particularly to meet the hybridization requirements of the turbomachine.

[0011] Since the available space around the engine is much more limited than around a fan housing, the compactness of the accessory box and its associated components becomes essential for optimizing its integration and that of the equipment it houses. This optimal integration avoids interfering with the ideal aerodynamic lines defined by the engine manufacturer and thus prevents adapting these lines to the size of the accessory box and its components. Indeed, such adaptations would negatively impact engine performance, particularly its specific fuel consumption.

[0012] The invention offers a simple, effective and economical solution to this need. Summary of the invention

[0013] To this end, the invention proposes an assembly comprising an accessory housing and equipment for an aircraft turbomachine, the accessory housing comprising a gear train having gears meshed with each other and having axes of rotation parallel to each other and to a main axis, the equipment comprising first pieces of equipment each comprising a shaft parallel to said main axis and coupled to the gear train, the assembly further comprising a relay box which is connected to the accessory box by a transfer shaft parallel to said main axis and coupled to the gear train, characterized in that the equipment comprises at least one second piece of equipment which comprises a shaft perpendicular to said main axis and coupled to said transfer shaft.

[0014] The invention thus proposes to drive some of the equipment by the transfer shaft rather than by the accessory gearbox. Unlike the prior art where all the equipment is mounted on the accessory gearbox and driven by the gearbox's gear train, some of the equipment is offset from the accessory gearbox and driven directly by the transfer shaft. This allows for better distribution of the equipment within the assembly according to its size and thus enables the integration of the assembly into a more confined environment, such as, for example, around an engine and radially within a secondary flow path.

[0015] The assembly according to the invention may comprise one or more of the following features, taken individually or in combination with each other: • the accessory housing has two faces perpendicular to the main axis, the first equipment being mostly located on the side of one of these faces, and the transfer shaft extending on the side of a second of these faces; • the second piece of equipment is located on the side of the second face; • the second piece of equipment is inserted between the second face and the relay box; • the second piece of equipment is inserted between the transfer shaft and one of the first pieces of equipment located on the side of the second face; • the set includes at least two secondary pieces of equipment; • the second equipment is located on two opposite sides of the shaft transfer ; • the shafts of the second equipment are inclined relative to each other at an angle between 90° and 180°, preferably between 100° and 150°; • the assembly further includes a return shaft which is coupled to the transfer shaft via the relay box, this return shaft being inclined relative to the main axis.

[0016] The present invention further relates to a turbomachine for an aircraft, comprising an assembly as described above.

[0017] The turbomachine according to the invention may comprise one or more of the following features, taken individually or in combination with each other: • the main axis of the assembly is parallel to a longitudinal axis of the turbomachine; • the assembly is located downstream of a blower housing, and is surrounded by an annular flow channel of a secondary airflow; • the assembly extends at least in part around an inter-compressor and / or a high-pressure compressor;

[0018] — one of the second elements is an electrical machine. Brief description of the figures

[0019] Other features and advantages will become apparent from the following description of a non-limiting embodiment of the invention with reference to the accompanying drawings in which:

[0020] [Fig-1] [Fig.1] is a partial schematic axial cross-sectional view of a aircraft turbomachine;

[0021] [Fig.2] [Fig.2] is a very schematic cross-sectional view of a housing accessories mounted around an aircraft turbomachine;

[0022] [Fig.3] [Fig.3] is a very schematic cross-sectional view of an assembly according to the prior art;

[0023] [Fig.4] [Fig.4] is a schematic perspective view of an assembly according to the previous technique;

[0024] [Fig. 5] [Fig. 5] is a very schematic cross-sectional view of an assembly according to the invention; and

[0025] [Fig.6] [Fig.6] is a schematic perspective view of an assembly according to the invention. Detailed description of the invention

[0026] Fig. 1 shows a turbomachine 1 which has a longitudinal axis X.

[0027] The turbomachine 1 comprises a gas generator which includes, conventionally along this axis X, a low-pressure compressor 1a, a high-pressure compressor 1b, an annular combustion chamber 1e, a high-pressure turbine Id, a low-pressure turbine 1e, and an exhaust nozzle Ih. The high-pressure compressor 1b and the high-pressure turbine Id are connected by a high-pressure shaft 2 and together form a high-pressure (HP) body. The low-pressure compressor 1a and the low-pressure turbine 1e are connected by a low-pressure shaft 3 and together form a low-pressure (LP) body.

[0028] A blower S is mounted upstream of the gas generator and is driven by a blower shaft 4 which is connected to the BP shaft 3 by means of a mechanical reducer 10. This reducer 10 is generally of the planetary or epicyclic type.

[0029] The low pressure compressors 1a and high pressure compressors 1b are axially separated from each other by an intermediate housing or inter-compressor housing 5. The blower S is surrounded by a blower housing 6 which is connected to the inter-compressor housing 5.

[0030] The blower S generates an airflow F which splits into a primary flow Fl and a secondary flow F2. The primary flow Fl flows into a primary channel VI of the gas generator and successively passes through the low-pressure compressor 3, the high-pressure compressor 1b, etc. The secondary flow F2 flows into a secondary channel V2 which extends between the gas generator and the blower housing 6.

[0031] The present invention relates in particular to the integration of an accessory housing 10 into a turbomachine 1 such as that shown in [Fig.1].

[0032] Fig. 2 shows a mounting configuration of an assembly 10 with accessory housing 12 in a turbomachine 1 and figures 3 and 4 show an assembly 10 according to the prior art.

[0033] The assembly 10 of figures 3 and 4 includes an accessory box 12, equipment 14, a relay box 16 and a transfer shaft 18.

[0034] The accessory housing 12 includes a gear train 20 comprising gears 22 meshed with each other and comprising axes of rotation A parallel to each other and to a main axis Y which can be confused with the axis X of the turbomachine 1.

[0035] The equipment 14 each includes a shaft 24 parallel to the main axis Y and coupled to the gear train 20. The axes of rotation of the shafts 24 are therefore coincident with the axes A or are parallel to these axes A.

[0036] The relay box 16 is connected to the accessory box 12 by the transfer shaft 18 which is parallel to the main axis Y and coupled to the gear train 20.

[0037] Furthermore, a return shaft 26 extends from the relay box 16 to one of the shafts of the gas generator for the purpose of transferring power onto or from that shaft.

[0038] It is therefore understood that the return shaft 26 is coupled to one of the shafts of the turbomachine 1, such as the low-pressure shaft 3, for the purpose of power injection or extraction. The return shaft 26 is coupled to the transfer shaft 18 via the relay housing 16, and the transfer shaft 18 is coupled to the gear train 20 of the accessory housing 12.

[0039] We can see in [Fig.3] that the accessory housing 12 has two faces 28, 30 perpendicular to the main axis Y and that the equipment 14 is distributed and mounted on the two faces 28.

[0040] Figures 2 and 4 show that the accessory housing 12 has a generally curved or banana-like shape and can thus have a U or V shape. This shape allows it to conform best to the shape of the element around which it is mounted. In the prior art, the element around which the accessory housing 12 and the assembly 10 are mounted is the blower housing 6.

[0041] The present invention proposes an improvement to the assembly which allows its integration as close as possible to the gas generator and in particular around the inter-compressor housing 5 and / or the high-pressure compressor 1b. It is therefore understood that, in the prior art, the assembly 10 is mounted radially outside the V2 channel, around the blower housing 6, and that it is proposed to mount it radially inside this V2, around the inter-compressor housing 5 and / or the high-pressure compressor 1b, within the framework of the present invention ([Fig.2]).

[0042] Figures 5 and 6 illustrate an embodiment of the invention in which the elements already described above are designated by the same references.

[0043] The assembly 10 of figures 5 and 6 includes an accessory box 12, equipment 14, a relay box 16 and a transfer shaft 18.

[0044] The accessory housing 12 includes a gear train 20 comprising gears 22 meshed with each other and having axes of rotation A parallel to each other and to a main axis Y which can be confused with the axis X of the turbomachine 1.

[0045] The relay box 16 is connected to the accessory box 12 by the transfer shaft 18 which is parallel to the main axis Y and coupled to the gear train 20.

[0046] A return shaft 26 extends from the relay box 16 to one of the shafts of the gas generator for the purpose of transferring power onto or from that shaft.

[0047] The idler shaft 26 is thus coupled to one of the shafts of the turbomachine 1, such as the low-pressure shaft 3, for the purpose of power injection or extraction. The idler shaft 26 is coupled to the transfer shaft 18 via the relay housing 16, and the transfer shaft 18 is coupled to the gear train 20 of the accessory housing 12. The idler shaft 26 can be inclined with respect to the main Y-axis.

[0048] The accessory housing 12 has two faces 28, 30 perpendicular to the main axis Y.

[0049] According to the invention, the equipment 14 is divided into two categories, the first equipment 14a and the second equipment 14b.

[0050] The first equipment 14a is mounted directly on the accessory housing 12 and is driven directly by the gear train 20. The first equipment 14a each has a shaft 24 parallel to the main axis Y and coupled to the gear train 20.

[0051] The second equipment 14b is mounted on the transfer shaft 18 and is driven directly by the transfer shaft 18. The second equipment 14b each has a shaft 32 perpendicular to the main axis Y and coupled to the transfer shaft 18. The axes B of rotation of the shafts 32 are therefore perpendicular to the axes A.

[0052] The accessory housing 12 has two faces 28, 30 perpendicular to the main axis Y. The first equipment 14a is mostly located on the side of one of these faces 30, and the transfer shaft 18 extends on the side of a second of these faces 28.

[0053] The second equipment 14b is preferably located on the side of the second of the faces 28. More particularly, it can be seen in the drawings that the second equipment 14b is intercalated between the second of the faces 28 and the relay box 16.

[0054] The second equipment 14b can be intercalated between the transfer shaft 18 and one of the first equipment 14a located on the side of the second of the faces 28.

[0055] The number of second equipment 14b is at least equal to two. This number is two in the example shown.

[0056] In the example shown, it can also be seen that the second equipment 14b is located on two opposite sides of the transfer shaft 18.

[0057] The shafts 32 of the second equipment 14b can be inclined relative to each other at an angle α between 90° and 180°, preferably between 100° and 150°. This angle α can be chosen so that the equipment 14b and their shafts 32 together adopt a curved shape comparable to that of the accessory housing 12, which facilitates the integration of the assembly 10, in particular around the inter-compressor housing 5 and / or the high-pressure compressor 1b.

[0058] One of the second elements 14b is, for example, an electrical machine.

[0059] The coupling of the shaft 32 of each of the equipment 14b to the transfer shaft 18 can be achieved by means of bevel gears, for example. This can allow the equipment 14b to be driven at a higher rotational speed than the shafts 24 of the equipment 14a, and limit the torsional dynamics of the shafts.

[0060] The present invention offers several advantages, including: • increased compactness, • a reduced angular footprint, • a reduced mass, • simplified torsional dynamics, and • better maintenance.

Claims

Demands

1. An assembly (10) comprising an accessory housing (12) and equipment (14) for an aircraft turbomachine (1), the accessory housing (12) comprising a gear train (20) having gears (22) meshed with each other and having axes of rotation (A) parallel to each other and to a main axis (Y), the equipment (14) comprising first pieces of equipment (14a) each having a shaft (24) parallel to said main axis (Y) and coupled to the gear train (20), the assembly (10) further comprising a relay housing (16) which is connected to the accessory housing (12) by a transfer shaft (18) parallel to said main axis (Y) and coupled to the gear train (20), characterized in that the equipment (14) comprises at least one second piece of equipment (14b) having a shaft (32) perpendicular to said axis main (Y) and coupled to said transfer tree (18).

2. Assembly (10) according to claim 1, wherein the accessory housing (12) has two faces (28, 30) perpendicular to said main axis (Y), the first equipment (14a) being mostly located on the side of a first of these faces (30), and the transfer shaft (18) extending on the side of a second of these faces (28).

3. Assembly (10) according to claim 2, wherein the or each second piece of equipment (14b) is located on the side of the second of the faces (28).

4. Assembly (10) according to claim 3, wherein the second equipment (14b) is intercalated between the second of the faces (28) and the relay box (16).

5. Assembly (10) according to any one of claims 2 to 4, wherein the or one of the second equipment (14b) is intercalated between the transfer shaft (18) and one of the first equipment (14a) located on the side of the second of the faces (28).

6. Assembly (10) according to any one of the preceding claims, wherein it comprises at least two second equipment (14b).

7. Assembly (10) according to claim 5, wherein the second equipment (14b) is located on two opposite sides of the transfer shaft (18).

8. Assembly (10) according to claim 5 or 6, wherein the shafts (32) of the second equipment (14b) are inclined to one another with respect to

9.

10.

11.

12.

13. the other at an angle (a) between 90° and 180°, preferably between 100° and 150°. Assembly (10) according to any one of the preceding claims, wherein it further comprises a return shaft (26) which is coupled to the transfer shaft (18) via the relay housing (16), this return shaft (26) being inclined with respect to the main axis (Y). Turbomachine (1) for an aircraft, comprising an assembly (10) according to any one of the preceding claims. Turbomachine (1) according to claim 10, wherein the main axis (Y) of the assembly (10) is parallel to a longitudinal axis (X) of the turbomachine. Turbomachine (1) according to claim 10 or 11, wherein the assembly (10) is located downstream of a blower casing (6), and is surrounded by an annular flow channel (V2) of a secondary airflow (F2). Turbomachine (1) according to claim 12, wherein the assembly (10) extends at least in part around an inter-compressor casing (5) and / or a high-pressure compressor (1b).

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