Accessory relay box and aircraft turbomachine comprising such a box

Abstract

The invention relates to an accessory relay box (50) for an aircraft turbomachine, comprising: - a casing (52), a reduction gear (62) and a freewheel (64) which are permanently integrated into the casing, the accessory relay box being configured to interface with a starter (54) of the turbomachine which is intended for starting the turbomachine, the reduction gear and the freewheel being dedicated to the starter of the turbomachine. Figure for the abstract: Fig 2B.

Description

Title of the invention: Accessory relay box and aircraft turbomachine comprising such a box Technical field

[0001] The present disclosure relates to an accessory relay box for an aircraft turbomachine and to an aircraft turbomachine comprising such an accessory relay box. Prior art

[0002] Known aircraft turbomachines generally comprise an accessory gear box or AGB (known in English terminology as "Accessory GearBox") which uses the movement of the engine shaft to drive various accessories such as fuel pumps, electric generators, lubrication unit, starter, oil separator and other components which constitute all of the auxiliary equipment of the engine and power generation of the aircraft.

[0003] [Fig.l] illustrates, in a longitudinal section, a known aircraft turbomachine architecture (here, for example, it is a double-flow turbojet) of longitudinal shape centered around a longitudinal axis XX'. The turbomachine 10 generally comprises, successively from upstream to downstream in the direction of circulation of the air flow illustrated by the arrows F (i.e. from left to right in the figure), a fan 12 (known in English terminology as a "fan") which supplies air to a primary vein 14 and to a secondary vein 16 producing the majority of the thrust force of the turbomachine, and which is arranged coaxially with respect to the primary vein 14 in an annular duct 18. This duct 18 comprises successively from upstream to downstream stator blades 20 and an intermediate structural casing 22.

[0004] The primary vein 14 successively comprises, from upstream to downstream, one or more low-pressure compression stages 24, one or more high-pressure compression stages 26, a combustion chamber 28, one or more high-pressure turbine stages 30, one or more low-pressure turbine stages 32 and an exhaust casing of which the structural arms 34 can be seen.

[0005] As shown in the figure, a low pressure drive shaft 36 connects the low pressure turbine 32 to the low pressure compressor 24 and to the fan 12.

[0006] A radial shaft 38 (housed in an arm of the intermediate casing 22) extends from a high pressure drive shaft 39 (which connects the high pressure turbine 30 to the high pressure compressor 26) to a right angle gearbox 40 which, in turn, is connected to an accessory relay box 42.

[0007] Thus, the movement is transmitted to the accessory relay box 42 from the high pressure motor shaft 39, via the radial shaft 38 and the angle gearbox 40.

[0008] In this type of turbomachine architecture there is a constant need to seek to reduce the size of the various components and in particular of the accessory relay box equipped with its accessories.

[0009] Indeed, the axial size of an accessory, that is to say the size of this accessory in an axial direction parallel to the longitudinal axis XX' of the turbomachine, can be prohibitive for the installation of the accessory relay box in a turbomachine, whether in an inter-vein compartment (see reference 37 in [Fig.l]) or in a fan compartment as is the case in the figure.

[0010] The present invention thus aims to reduce the overall axial size of the accessory relay housing equipped with accessories. Statement of the invention

[0011] To this end, the present invention proposes a configuration of an accessory relay box for an aircraft turbomachine which in particular makes it possible to achieve this aim and which comprises: - a casing, - a reducer and a freewheel which are permanently integrated into the casing, the accessory relay box being configured to interface with a starter of the turbomachine which is intended for starting the turbomachine, the reducer and the freewheel being dedicated to the starter of the turbomachine.

[0012] The integration in the casing of the accessory relay box of the reducer and the freewheel dedicated to the starter of the turbomachine and which, normally, are integrated into this starter, makes it possible to reduce the overall axial size of the accessory relay box equipped with the starter. This arrangement thus makes it possible to more easily install the accessory relay box in different locations of the turbomachine, in particular in the inter-vein compartment or in the fan compartment.

[0013] According to other possible characteristics: - the casing comprises a first and a second opposite wall, the first wall being intended to interface with the starter of the turbomachine, the accessory relay box comprising in the casing a shaft line dedicated to the starter and which comprises a pinion shaft which extends between the first and second opposite walls, in an axial direction perpendicular to these walls, the pinion shaft comprising two opposite ends, a first end of which is arranged on the side of the first wall of the housing and the second end is arranged on the side of the opposite second wall of the housing, the freewheel being arranged in the housing on the side of the second end of the pinion shaft;

[0014] - the freewheel is mounted inside the pinion shaft;

[0015] - the second opposite wall of the casing is externally equipped with a port of manual control (HCP) arranged in axial alignment with the shaft line dedicated to the starter and which is configured to allow, on command, when the turbomachine is stopped on the ground, the manual drive of a gear system internal to the casing;

[0016] - the manual control port (HCP) is connected to a drive shaft connected to the freewheel dedicated to the starter; - the accessory relay housing includes a rotating seal between the manual control port (HCP) and the drive shaft;

[0017] - the accessory relay housing comprises inside the casing a shaft of transmission extending axially within the pinion shaft between a first end coupled to the reducer and a second opposite end which extends to the second opposite wall of the housing for coupling to equipment external to the housing;

[0018] - the second opposite end of the transmission shaft is intended to be coupled to an external oil pump to the crankcase;

[0019] - the second opposite end of the transmission shaft is intended to be coupled to an electric motor external to the casing and which is dedicated to the operation of the turbomachine when the aircraft is on the ground (ETM);

[0020] - the freewheel is mounted outside the pinion shaft;

[0021] - the second opposite wall of the casing has an external protrusion which extends axially away from the casing and which allows the freewheel to be housed; - the accessory relay housing comprises at least one other shaft line which extends parallel to the axial direction of the starter shaft line and which is intended to interface with another accessory, the second opposite wall of the housing being intended to interface with this other accessory; - the reducer is arranged in the housing on the side of the first end of the pinion shaft; - the reducer is arranged outside the pinion shaft; - the reducer is arranged between the first end of the pinion shaft and the first wall of the housing; - the reducer is coupled to a fusible member arranged inside the pinion shaft.

[0022] The invention also relates to an aircraft turbomachine comprising an aircraft turbomachine accessory relay box as briefly explained above. above. Brief description of the drawings

[0023] Other characteristics and advantages of the subject of the present disclosure will emerge from the following description of embodiments, given as non-limiting examples, with reference to the appended figures.

[0024] [Fig-1] [Fig.l] is a schematic view in longitudinal section of a turbo reactor according to the prior art;

[0025] [Fig.2A] [Fig.2A] is an enlarged schematic view of the accessory relay housing of [Fig.l] to which a starter motor is attached;

[0026] [Fig.2B] [Fig.2B] is a schematic view similar to that of [Fig.2A] showing a new arrangement of accessory relay housing and starter according to an exemplary embodiment of the invention;

[0027] [Fig.3] [Fig.3] is a schematic view similar to that of [Fig.2B] showing an accessory relay box according to another possible embodiment;

[0028] [Fig.4] [Fig.4] is a schematic view similar to that of [Fig.2B] showing an accessory relay box according to another possible embodiment;

[0029] [Fig.5] [Fig.5] is a schematic view similar to that of [Fig.2B] showing an accessory relay box according to an exemplary possible embodiment;

[0030] [Fig.6] [Fig.6] is a schematic view similar to that of [Fig.2B] showing an accessory relay box according to another possible embodiment. Detailed description

[0031] The present invention applies in particular to an aircraft turbomachine such as that shown in [Fig.l] and described above.

[0032] However, the invention can be applied to other turbomachines such as, for example, a single-spool turbomachine, a non-ducted fan turbomachine, a triple-spool machine, a gas turbine, a helicopter turboshaft engine, etc.

[0033] Figures 2A and 2B are comparative schematic views which illustrate the principle underlying the invention.

[0034] More particularly, [Fig.2A] (prior art) schematically represents, according to an axial view taken along an axis parallel to the longitudinal axis XX' of the turbomachine illustrated in [Fig.l] (axis offset laterally relative to the axis XX'), the accessory relay housing 42 equipped with a turbomachine starter 44 arranged externally to the housing and axially offset relative to the housing on the left thereof. Only the reduction gear 44a and the freewheel 44b of the starter 44 are visible in the figure and are represented very schematically inside the starter which is symbolized by dotted lines. In a known manner, the starter 44 is intended for starting the turbomachine so that the engine shaft reaches a speed of sufficient rotation.

[0035] Generally, the accessory relay housing 42 comprises a shaft line dedicated to the starter 44, comprising a pinion shaft 45 extending axially inside the housing and which comprises, at the external periphery of the web 46 of the pinion, a toothing 46a making it possible to mesh with other gear elements of the gear train of the housing, two elements of which, denoted 43 and 47, are shown in the figure, arranged on two other parallel shaft lines.

[0036] As shown in [Fig.2A], the reducer 44a of the starter 44 is connected to the input of the freewheel 44b which, in turn, is connected to one end of a fusible keel which can be associated with a decoupler, which are jointly represented by the reference 48 at a wall of the accessory relay housing 42 which is located at the interface between the starter and the housing. The fusible keel 48 is arranged inside the housing. It protects against over-torque and locally has a reduction in section (frangible zone) which is configured to break in the event that the mechanical torque applied by the starter to the accessory relay housing exceeds a predetermined threshold. The decoupler serves, for its part, to limit the mechanical torque applied by the accessory relay housing to the starter. It will be noted that the fusible keel and the decoupler have different threshold values.

[0037] The other end of the assembly formed by the fusible keel and the decoupler 48 is connected to the inside of the pinion shaft 45 via a splined interface 49.

[0038] [Fig.2B] illustrates the principle of the invention applied to the configuration of [Fig.2A] and shows how this configuration is modified.

[0039] The references used for the elements of [Fig.2A] have been modified to the extent that both the accessory relay box and the starter have been modified.

[0040] The accessory relay box 50 comprises a casing 52 inside which are housed the various elements of the gear train making it possible to drive the various accessories mounted on the casing, from the angle transmission box 40 of [Fig.l].

[0041] The housing 52 comprises two opposite walls, namely a first wall 52a and a second opposite wall 52b spaced axially from one another in the axial direction parallel to the longitudinal axis XX' of the turbomachine (the axis XX' is shown in [Fig.2B] only to recall the axial orientation but its location on the turbomachine of [Fig.l] is different as indicated in [Fig.l]).

[0042] The first wall 52a is intended to interface with the known starter 54 of the turbomachine surrounded here by dotted lines but represented in more detail than in [Fig.2A].

[0043] The accessory relay box 50 comprises, inside the casing 52, a shaft line L1 dedicated to the starter 54 and which comprises a pinion 56 comprising a shaft pinion shaft 56a extending between the two opposite walls 52a and 52b, parallel to the axial direction of the shaft line L1 (and therefore perpendicular to the walls). The pinion shaft 56a has two opposite ends, a first end 56al of which is arranged on the side of the first wall 52a. The second opposite end 56a2 is, for its part, arranged on the side of the second opposite wall 52b of the casing.

[0044] The pinion 56 also comprises a pinion web 56b which extends radially (in a transverse plane perpendicular to the shaft line L1) and away from the pinion shaft 56a. The pinion web 56b comprises, at its external periphery, a toothing 56bl making it possible to mesh with other gear elements 58 and 60 (e.g.: pinions) arranged, inside the casing, along other lines of drive shafts respectively L2 and L3 which are here shown parallel to the shaft line LL. These other lines of drive shafts can be used to drive other accessories (not shown here) mounted on the housing 50.

[0045] The casing 52 of the accessory relay box 50 integrates a reducer 62 and a freewheel 64 which are both dedicated to the starter 54 of the turbomachine, unlike [Fig.2A], where the reducer 44a and the freewheel 44b are housed inside the starter 44 itself.

[0046] As shown in [Fig.2B], the freewheel 64 is arranged in the casing 52 on the side of the second end 56a2 of the pinion shaft 56a (it will be noted that in other alternative configurations not shown here the freewheel can be arranged on the side of the first end 56al of the pinion shaft 56a). The reducer 62 is, for its part, arranged on the side of the first end 56al of this shaft and, more particularly, between this first end and the first wall 52a, in particular outside the shaft.

[0047] In the embodiment shown in [Fig.2B], the freewheel 64 is shown mounted inside the pinion shaft 56a but it can however be mounted externally to this shaft.

[0048] Furthermore, the reducer 62 is connected to one end 65a of a fusible keel and a decoupler jointly represented by the reference 65 and arranged inside the casing 52.

[0049] The other end 65b of the assembly 65 is connected to the freewheel 64, for example to the hub of the freewheel while the outer body of the freewheel is connected to the pinion shaft 56a.

[0050] On the side of the reducer 62 which is oriented facing the first wall 52a, a shaft 66 secured to the starter 54, for example the shaft of the air turbine of the starter, passes through the first wall 52a to partially penetrate inside the casing by one end 66a. This end is provided with teeth or any other means of meshing or coupling with one of the pinions of the reducer 62. The reducer generally has an epicyclic gear train structure and many architectures can be envisaged. The end 66a of the shaft (the sun gear) is connected to satellites, the number of which can be between 1 and 5 (in practice more often 3), which can have two stages (two teeth as in the figure) or a single stage (a single tooth in a configuration not shown). These satellites mesh on a crown which is connected to the end 65a of the fusible keel (by splines).

[0051] The permanent integration in the casing 52 of the accessory relay box 50 of a part of the starter which is formed by the reducer 62 and the freewheel 64 has several consequences:

[0052] - the distance between the guide bearings (represented by dotted lines on both sides) ends of the shaft on [Fig.2B]) of the pinion shaft 56a of the shaft line L1 dedicated to the starter is reduced compared to the configuration of [Fig.2A];

[0053] - the diameter of the pinion shaft 56a (and therefore the internal diameter of the web 56b) is increased compared to the configuration of [Fig.2A], while the external diameter of the veil or tooth diameter 56b 1 remains unchanged;

[0054] - the length of the pinion shaft 56a on the side of the pinion which is oriented towards the starter 54 (i.e. on the side of the first end 56al) is reduced compared to the configuration of [Fig.2A].

[0055] Despite these modifications, the distance d between the first wall 52a of the casing and the plane P of the gear train of the casing is unchanged.

[0056] This arrangement also results in a gain G in axial size of the accessory relay box 50 equipped with the starter 54 compared to the configuration of [Fig.2A].

[0057] This reduction in axial size is illustrated in [Fig.2B] in which the starter 44 of [Fig.2A] is partially illustrated in the upper left part for the purposes of comparison.

[0058] [Fig.3] illustrates an exemplary embodiment according to the invention which takes up the general configuration of [Fig.2B] (the references used in [Fig.2B] are taken up for the elements which are unchanged) by adding to the accessory relay box 70 an additional possibility of driving from the shaft line L1 dedicated to the starter 54.

[0059] In particular, a manual control port HCP (known in English terminology as "Hand Crank Port"), denoted 72, is mounted externally on the second wall 52b, in axial alignment with the shaft line L1 and is configured to interface, on command, with the gear system internal to the casing and to allow, on command, the manual drive of this system. This manual control port 72 is only used when the aircraft is on the ground, during maintenance operations.

[0060] In the configuration illustrated in [Fig. 3], the port 72 is coupled to a drive shaft 74 which extends inside the housing and is connected to the freewheel 64 by one end of this shaft. The opposite end of the shaft 74 is connected to the port 72 and is used only during maintenance operations, as mentioned above. Furthermore, a rotating seal 76 is mounted between the shaft 74 and the manual control port 72.

[0061] Thus, following the starting of the turbomachine by the starter, when the starter disconnects thanks to the freewheel 64, the gear train of the accessory relay box becomes driven by the turbomachine, and as a result the HCP function is also disconnected, which makes it possible not to rotate the HCP shaft 74 during normal operation of the engine.

[0062] By virtue of the arrangement described above, the installed rotary joint 76 is used episodically (it does not rotate continuously), only when the HCP function is required. The sealing of the HCP manual control port can therefore be ensured by a rotary joint whose cost and wear are relatively reduced compared to a joint which would necessarily be sized for higher speeds if the HCP shaft 74 were to continue to rotate during normal operation of the engine following start-up.

[0063] [Fig.4] illustrates an exemplary embodiment according to the invention which takes up the general configuration of [Fig.2B] (the references used in [Fig.2B] are taken up for the elements which are unchanged) by adding to the accessory relay box 80 an additional possibility of driving from the shaft line L1 dedicated to the starter 54.

[0064] More particularly, a transmission shaft 82 extends axially inside the casing 52, in particular inside the pinion shaft 56a, between a first end 82a of the shaft coupled to the reduction gear 62, in particular to a pinion 62a (here this is the second stage of a two-stage satellite) of the reduction gear, and a second opposite end 82b. The second end 82b extends to the second opposite wall 52b of the casing (and may even project externally beyond the wall and therefore the casing) to be coupled to equipment external to the casing such as an oil pump 84.

[0065] The external equipment such as the oil pump 84 is thus connected to the output of the reducer 62 integrated into the accessory relay box 80.

[0066] Such an arrangement makes it possible to drive a low-capacity pump which ensures the supply of oil during a so-called marginal lubrication phase, carried out only at low speed, i.e. in particular when starting the turbomachine or during a "motoring" phase. This phase is a wind phase Engine rotation in which the engine (HP shaft) is driven at low speed, on the ground, by the starter or an electric motor. This allows the combustion chamber to be ventilated and the turbomachine's fuel system to be primed.

[0067] Indeed, at low rotational speed of the high-pressure body of the turbomachine, in particular when starting the latter, the drive speed of the gear train of the accessory relay housing by the high-pressure body is insufficient for the main lubrication unit (including a main feed pump) mounted on the housing to be driven at its nominal speed. The main feed pump of the unit is not properly primed or, in any case, does not provide a sufficient flow rate to ensure correct lubrication of the various components of the turbomachine which require it (in particular the starter reducer). During the engine ventilation phase, the engine rotates slowly while the pump rotates quickly (primed pump). The low-capacity pump thus provides the same flow rate as the main feed pump but at a speed 10 to 20 times lower than that of the main feed pump.

[0068] A low capacity oil pump such as pump 84 of [Fig.4] makes it possible to overcome this drawback.

[0069] Such a pump is generally disconnected during normal operation of the engine, i.e. when the starter is in disconnected mode. This arrangement makes it possible to take into account marginal lubrication needs without having to oversize the main lubrication unit of the turbomachine to cover such needs.

[0070] [Fig.5] illustrates another exemplary embodiment according to the invention which takes up the general configuration of [Fig.2B] (the references used in [Fig.2B] are taken up for the elements which are unchanged) by adding to the accessory relay box 90 an additional possibility of driving from the shaft line L1 dedicated to the starter 54.

[0071] More particularly, a transmission shaft 92 extends axially inside the casing 52, in particular inside the pinion shaft 56a, between a first end 92a of the shaft coupled to the reducer 62, in particular to a pinion 62b of the reducer, and a second opposite end 92b. The second end 92b extends to the second opposite wall 52b of the casing which it passes through to project externally beyond the wall (and therefore the casing) and to be coupled to equipment external to the casing such as an electric motor called ETM (known in English terminology as "Engine Turning Motor") 94. Such an ETM motor is used on the ground in order to turn the engine shaft of the turbomachine at very low speed for a relatively long time, this in order to standardize the temperature of the rotor and therefore to reduce the thermal gradient present on this rotor.

[0072] External equipment such as motor 94 is thus connected to the input of the reducer 62 integrated into the accessory relay box 90, input which is already connected to the turbine shaft 66 of the starter as mentioned above. The reducer 62 is in fact used to reduce the speed between the motor 94 of the ETM which needs to rotate quickly and the shaft 56a connected to the output of the reducer 62. The shaft 92 could therefore not be connected to a slower rotating pinion such as the output pinion of the reducer.

[0073] This arrangement makes it possible to share the reduction gear requirements of the starter 54 and the motor 94 by eliminating the specific reduction gear of the motor 94 and allowing this motor to use the reduction gear 62 of the starter integrated into the casing 52.

[0074] Furthermore, as for the previous drive configurations from the shaft line L1 dedicated to the starter, the motor 94, which is only used when the aircraft is on the ground, disconnects during normal operation from the turbomachine engine, which makes it possible to suppress its rotation and therefore avoids any wear of its internal parts when its use is not required. Thus, its reliability is increased. Alternatively, the cost of its design can be revised downwards due to less wear of its internal parts.

[0075] [Fig.6] illustrates another exemplary embodiment according to the invention which takes up possibly the general configuration of [Fig.2B] (the references used in [Fig.2B] are repeated for the elements which are unchanged) and modifies the accessory relay box 100 by axially offsetting the freewheel 64' outside the pinion shaft 56a', always on the side of the second opposite end 56a2' of this shaft.

[0076] In this new configuration, the pinion shaft 56a' is elongated compared to the configuration of [Fig.2B] (the length of the pinion shaft 56a' is identical to the length of the shaft 45 of [Fig.2A]) and the freewheel 64' is positioned at the end of the shaft. The second wall 52b' of the casing is modified in order to form an external protrusion 102 (in alignment with the shaft line L1) which extends axially away from the casing (and from the first wall 52a), which makes it possible to house, in this axial protrusion, the axial extension of the pinion shaft 56a' and the freewheel 64'. The second end 65b' of the fusible keel and decoupler assembly 65' is also modified to follow the offset of the freewheel 64' and is thus lengthened compared to the configuration of [Fig.2B].

[0077] The elongation of the pinion shaft 56a' has the effect of moving the guide bearings p1 and p2 of this shaft, which are arranged at its two opposite ends 56al and 56a2', away from each other. This arrangement makes it possible to ensure better guidance of the axis of rotation of this shaft and therefore to cause less wear of the straight teeth due to better parallelism between the axes of the pinion shafts.

[0078] Furthermore, the axial offset of the freewheel 64' makes it possible not to increase the internal diameter of the pinion shaft dedicated to the starter, which makes it possible to limit its mass.

[0079] Such an arrangement is possible without increasing the axial size of the assembly comprising the accessory relay box 100 and accessories equipping this box insofar as the axial size of the protrusion 102 is less than the axial size of an accessory or equipment 104 mounted on another shaft line such as the line L2 parallel to the line L1, on the same second wall 52b' as that on which the axial protrusion 102 is shaped.

[0080] The axial size of the accessory relay housing assembly 100 and accessories is denoted D in [Fig.6].

[0081] Although the present description refers to specific exemplary embodiments, modifications may be made to these examples without departing from the general scope of the invention as defined by the claims. Furthermore, individual features of the various embodiments illustrated or mentioned may be combined in additional embodiments. Therefore, the description and the drawings should be considered in an illustrative rather than restrictive sense.

Claims

Claims

1. Accessory relay housing (50; 70; 80; 90; 100) for an aircraft turbomachine, the accessory relay housing being configured to interface with a starter (54) of the turbomachine which is intended for starting the turbomachine, the accessory relay housing comprising: a casing (52) comprising first and second opposite walls (52a, 52b; 52b'), the first wall (52a) being intended to interface with the starter (54) of the turbomachine, a reduction gear (62) and a freewheel (64; 64') which are permanently integrated into the casing and dedicated to the starter of the turbomachine, in the casing, a shaft line (L1) dedicated to the starter and which comprises a pinion shaft (56a; 56a') extending between the first and second walls opposite, in an axial direction perpendicular to these walls, the pinion shaft (56a;56a') comprising two opposite ends of which a first end (56al) is arranged on the side of the first wall (52a) of the casing and the second end (56a2; 56a2') is arranged on the side of the second opposite wall (52b; 52b') of the casing, the freewheel (64; 64') dedicated to the starter being arranged in the casing on the side of the second end (56a2; 56a2') of the pinion shaft.;

2. Accessory relay housing (50; 70; 80; 90) for an aircraft turbomachine according to claim 1, in which the freewheel (64) is mounted inside the pinion shaft (56a).

3. Accessory relay housing (50; 70; 80; 90) for an aircraft turbomachine according to the preceding claim, in which the second opposite wall (52b) of the casing is externally equipped with a manual control port (72) arranged in axial alignment with the shaft line (L1) dedicated to the starter (54) and which is configured to allow, on command when the turbomachine is stopped on the ground, the manual drive of a gear system internal to the casing.

4. Accessory relay box (50; 70; 80; 90) for an aircraft turbomachine according to the preceding claim, in which the manual control port (72) is connected to a drive shaft (74) connected to the freewheel (64) dedicated to the starter.

5. Accessory relay housing (50; 70; 80; 90) for an aircraft turbomachine according to the preceding claim, comprising a seal rotating seal (76) between the manual control port (72) and the drive shaft (74).

6. An accessory relay housing (80; 90) for an aircraft turbomachine according to claim 2, comprising inside the casing a transmission shaft (82; 92) extending axially inside the pinion shaft (56a) between a first end (82a; 92a) coupled to the reduction gear (62) and a second opposite end (82b; 92b) which extends to the second opposite wall (52b) of the casing to be coupled to equipment external (84; 94) to the casing.

7. Accessory relay housing (80) for an aircraft turbomachine according to the preceding claim, in which the second opposite end (82b) of the transmission shaft (82) is intended to be coupled to an oil pump (84) external to the casing.

8. Accessory relay housing (90) for an aircraft turbomachine according to claim 6, in which the second opposite end (92b) of the transmission shaft (92) is intended to be coupled to an electric motor (94) external to the casing and which is dedicated to the operation of the turbomachine when the aircraft is on the ground.

9. An accessory relay housing (100) for an aircraft turbomachine according to claim 1, wherein the freewheel (64') is mounted outside the pinion shaft (56a').

10. Accessory relay housing (100) for an aircraft turbomachine according to the preceding claim, in which the second opposite wall (52b') of the casing comprises an external protrusion (102) which extends axially away from the casing (52) and which makes it possible to house the freewheel (64').

11. Accessory relay housing (100) for an aircraft turbomachine according to the preceding claim, comprising at least one other shaft line (L2) which extends parallel to the axial direction of the shaft line (L1) of the starter and which is intended to interface with another accessory (104), the second opposite wall (52b') of the casing being intended to interface with this other accessory.

12. Accessory relay housing (50; 70; 80; 90; 100) for an aircraft turbomachine according to one of claims 1 to 11, in which the reducer (62) is arranged in the casing on the side of the first end (56al) of the pinion shaft (56a; 56a').

13. Accessory relay box (50; 70; 80; 90; 100) for an aircraft turbomachine according to the preceding claim, in which the reducer (62) is arranged outside the pinion shaft (56a;56a').

14. Accessory relay housing (50; 70; 80; 90; 100) for an aircraft turbomachine according to the preceding claim, in which the reducer (62) is arranged between the first end (56al) of the pinion shaft (56a; 56a') and the first wall (52a) of the casing.

15. Accessory relay housing (50; 70; 80; 90; 100) for an aircraft turbomachine according to the preceding claim, in which the reducer (62) is coupled to a fusible member (65) arranged inside the pinion shaft (56a; 56a').

16. Aircraft turbomachine comprising an accessory relay box (50; 70; 80; 90; 100) for an aircraft turbomachine according to one of the preceding claims.

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