Accessory gearbox and aircraft turbine engine comprising such box

Abstract

Accessory gearbox (50) for an aircraft turbine engine, comprising:-a housing (52), a reduction gear (62) and a freewheel (62) permanently integrated into the housing, the accessory gearbox being configured to interface with a starter (54) of the turbine intended to start the turbine, the reduction gear and the freewheel being dedicated to the starter of the turbine.

Description

Technical Field The present disclosure relates to an accessory gearbox for an aircraft turbomachine, and to an aircraft turbomachine comprising such an accessory gearbox. Background Art

[0001] Known aircraft turbomachines typically include an accessory gearbox or AGB which uses the motion of the drive shaft to drive various accessories such as fuel pumps, generators, lubrication units, starters, oil separators and other components that make up the engine and aircraft power generation auxiliary equipment group.

[0002] Figure 1 A known structure of an aircraft turbine (for example, a turbofan engine here) of longitudinal shape centered on the longitudinal axis XX' is shown in a longitudinal cross-sectional view. The turbine 10 generally includes a fan 12 in sequence from upstream to downstream (i.e., from left to right in the figure) along the airflow circulation direction indicated by the arrow F, the fan 12 provides air to a main path 14 and a secondary path 16 that generate most of the thrust of the turbine, and the fan 12 is coaxially arranged in an annular duct 18 relative to the main path 14. The duct 18 includes stator blades 20 and an intermediate structural casing 22 in sequence from upstream to downstream.

[0003] The main path 14 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 are visible.

[0004] As shown, a low pressure drive shaft 36 connects the low pressure turbine 32 to the low pressure compressor 24 and the fan 12 .

[0005] A radial shaft 38 (housed in an arm of the intermediate housing 22 ) extends from a high-pressure drive shaft 39 (which connects the high-pressure turbine 30 to the high-pressure compressor 26 ) to a bevel gearbox 40 , which in turn is connected to an accessory gearbox 42 .

[0006] The movement is thus transmitted from the high pressure drive shaft 39 via the radial shaft 38 and the bevel gearbox 40 to the accessory gearbox 42 .

[0007] In this type of turbine architecture, there is a constant need to reduce the space requirements of the various components, in particular the accessory gearbox equipped with its accessories.

[0008] In fact, the axial space requirement of the accessory, ie the space requirement of the accessory in the axial direction parallel to the longitudinal axis XX' of the turbine, may be disadvantageous for installing the accessory gearbox in the turbine, either in the path compartment (see Figure 1 37) in the figure or in the fan compartment in the figure.

[0009] The present invention therefore aims to reduce the overall axial space requirement of an accessory gearbox equipped with accessories. Summary of the invention

[0010] To this end, the invention proposes a configuration of an accessory gearbox for an aircraft turbomachine, which configuration in particular achieves this object, the accessory gearbox being configured to interface with a turbomachine starter for starting the turbomachine, the accessory gearbox comprising: a housing comprising a first wall and a second opposing wall, the first wall being intended to interface with a starter of the turbomachine; A reduction gear and a free wheel, which are permanently integrated into the housing and are dedicated to the starter of the turbine; an axial line L1 in the housing, which is dedicated to the starter and includes a pinion shaft extending between a first wall and a second opposite wall in an axial direction perpendicular to the first wall, the pinion shaft including two opposite ends, a first end of which is arranged on the side of the first wall of the housing, and a second end of which is arranged on the side of the second opposite wall of the housing, and a free wheel dedicated to the starter is arranged in the housing on the side of the second end of the pinion shaft.

[0011] The integration of the accessory gearbox of the reduction gear in the housing and the freewheel dedicated to the turbine starter, which is usually integrated into the starter, makes it possible to reduce the overall axial space requirement in the accessory gearbox equipped with the starter. In particular, the axial space requirement of the starter is thus reduced. This arrangement thus makes it easier to install the accessory gearbox at different locations in the turbine, in particular in the path compartment or the fan compartment. In addition, this arrangement makes it possible to leave space for the installation of the reduction gear on the side of the first wall.

[0012] According to other possible characteristics: - the first wall of the housing comprises a zone intended to be crossed by the output shaft of the starter, the pinion shaft and the freewheel being coaxial with respect to an axis passing through this zone of the wall; this axis being aligned with the output shaft of the starter passing through the wall in the zone in question; -The freewheel is mounted inside the pinion shaft; - the second opposite wall of the casing is externally equipped with a hand crank port (HCP) arranged in axial alignment with the axis dedicated to the starter and configured to allow manual actuation of the gear system inside the casing on command when the turbine is stopped on the ground; - The hand crank port (HCP) is connected to a drive shaft which is connected to a freewheel dedicated to the starter; - The accessory gearbox includes a rotating seal between the hand crank port (HCP) and the drive shaft; - the accessory gearbox comprises a transmission shaft inside the housing, the transmission shaft extending axially inside the pinion shaft between a first end coupled to the reduction gear and a second opposite end extending to a second opposite wall of the housing for coupling to a device outside the housing; - a second opposite end of the transmission shaft is intended to be coupled to an oil pump outside the housing; - a second opposite end of the transmission shaft is intended to be coupled to an electric motor outside the casing, this electric motor being dedicated to operating the turbine when the aircraft is on the ground (ETM); -The freewheel is mounted outside the pinion shaft; - a second opposing wall of the housing comprises an external protrusion which extends axially away from the housing and which can accommodate the freewheel; - the accessory gearbox comprises at least one other shaft line extending parallel to the axial direction of the shaft line of the starter and intended to interface with another accessory with which the second opposite wall of the housing is intended to interface; - the pinion shaft carries a web provided with teeth at its periphery and arranged in the distance between the two opposite ends of the pinion shaft, the freewheel being arranged between the web and the second opposite wall of the housing; this arrangement of the web makes it possible to drive accessories arranged on the side of each of the two opposite walls of the gearbox (via a gear train coupled to one or more transmission shaft lines), thereby balancing the bearing surfaces on the shaft line(s); -The web is arranged between the reduction gear and the free wheel; - a reduction gear is arranged on the side of the first end of the pinion shaft in the housing; -The reduction gear is arranged outside the pinion shaft; - a reduction gear is arranged between the first end of the pinion shaft and the first wall of the housing; - The reduction gear is coupled to a fusible member disposed inside the pinion shaft. The invention also relates to an assembly comprising an accessory gearbox for an aircraft turbomachine as briefly described above and a starter interfaced with the gearbox, the starter comprising an output shaft arranged coaxially with the pinion shaft. The invention also relates to an aircraft turbomachine comprising an accessory gearbox for an aircraft turbomachine as briefly described above or an assembly as briefly described above. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Other characteristics and advantages of the object of the present disclosure will emerge from the following description of embodiments, given by way of non-limiting example with reference to the accompanying drawings.

[0014] [ Figure 1 ] Figure 1 is a longitudinal sectional schematic diagram of a turbojet engine according to the prior art;

[0015] [ Figure 2A ] Figure 2A yes Figure 1 An enlarged schematic diagram of an accessory gearbox to which the starter is secured;

[0016] [ Figure 2B ] Figure 2B is similar to Figure 2A Schematic diagram showing a new arrangement of an accessory gearbox and a starter according to an exemplary embodiment of the present invention;

[0017] [ Figure 3 ] Figure 3 is similar to Figure 2B Schematic diagram showing an accessory gearbox according to another possible exemplary embodiment;

[0018] [ Figure 4 ] Figure 4 is similar to Figure 2B Schematic diagram showing an accessory gearbox according to another possible exemplary embodiment;

[0019] [ Figure 5 ] Figure 5 is similar to Figure 2B Schematic diagram showing an accessory gearbox according to one possible exemplary embodiment;

[0020] [ Figure 6 ] Figure 6 is similar to Figure 2B Schematic diagram of an accessory gearbox according to another possible exemplary embodiment. DETAILED DESCRIPTION

[0021] The present invention is particularly applicable to Figure 1 An aircraft turbine as shown and described above.

[0022] However, the invention is also applicable to other turbomachines, such as single-shaft turbomachines, uninducted fan turbines, three-shaft machines, gas turbines, helicopter turboshaft engines, etc.

[0023] Figure 2A and Figure 2B It is a comparative schematic diagram for explaining the principle of the present invention.

[0024] More specifically, according to the Figure 1 An axial view taken along an axis of the longitudinal axis XX' of the turbine shown in (the axis being laterally offset relative to the axis XX'), Figure 2A(Prior art) Schematically shows an accessory gearbox 42 equipped with a turbine starter 44, which is arranged outside the gearbox and axially displaced relative to the gearbox on its left side. Only the reduction gear 44a and the freewheel 44b of the starter 44 are visible in the figure and are shown very schematically inside the starter represented by dashed lines. In a known manner, the starter 44 is intended to start the turbine, bringing the drive shaft to a sufficient rotational speed.

[0025] In general, the accessory gearbox 42 includes an axial line dedicated to the starter 44, which includes a pinion shaft 45 extending axially inside the gearbox, and the pinion shaft includes a tooth portion 46a at the periphery of the web 46 of the pinion, which tooth portion 46a enables engagement with other gear elements of the gear system of the gearbox, two elements of which are represented in the figure as 43 and 47, arranged on two other parallel axial lines.

[0026] like Figure 2A As shown, the reduction gear 44a of the starter 44 is connected to the inlet of the free wheel 44b, which in turn is connected to one end of a fusible keel, which can be associated with a disconnector, which is collectively indicated by the reference numeral 48 and is located at the level of the wall of the accessory gearbox 42 located at the interface between the starter and the gearbox. The fusible keel 48 is arranged inside the gearbox. It prevents overtorque and locally has a cross-sectional reduction (fragile area) that is configured to break if the mechanical torque applied by the starter to the accessory gearbox exceeds a predetermined threshold. The disconnector itself serves to limit the mechanical torque applied by the accessory gearbox to the starter. It should be noted that the fusible keel and the disconnector have different thresholds.

[0027] The other end of the assembly formed by the fusible keel and the disconnector 48 is connected to the inside of the pinion shaft 45 via a spline interface 49 .

[0028] Figure 2B Shown is applied to Figure 2A The invention principle of the construction is explained and how to modify the construction is shown.

[0029] Figure 2A The reference numerals of the elements in have been modified because both the accessory gearbox and the starter have been modified.

[0030] The accessory gearbox 50 includes a housing 52, and the housing 52 contains various elements of a gear train for driving various accessories mounted on the housing, such as Figure 1 Bevel gearbox 40.

[0031] The gearbox 52 comprises two opposing walls, namely a first wall 52a and a second opposing wall 52b, which are axially spaced apart from each other in an axial direction parallel to the longitudinal axis XX' of the turbine ( Figure 2B The axis XX' indicated in FIG. is only used to recall the axial orientation, but it Figure 1 The position on the turbine is Figure 1 shown differently).

[0032] The first wall 52a is intended to interface with a starter 54 known in the turbine, here enclosed by a dashed line, but more specifically Figure 2A is shown in more detail in .

[0033] The accessory gearbox 50 includes an axial line L1 dedicated to the starter 54 inside the housing 52, and the axial line L1 includes a pinion 56, which includes a pinion shaft 56a extending between two opposite walls 52a and 52b parallel to the axial direction of the axial line L1 (thus perpendicular to the walls). The pinion shaft 56a is hollow and includes two opposite ends, a first end 56a1 of which is arranged on the inner side of the first wall 52a. The second opposite end 56a2 itself is arranged on the side of the second opposite wall 52b of the housing.

[0034] The pinion 56 also comprises, in the distance between the two opposite ends 56a1 and 56a2, a pinion web 56b extending radially (in a transverse plane perpendicular to the axis line L1) and away from the pinion shaft 56a. The pinion web 56b comprises, on its outer periphery, a toothing 56b1 which enables meshing with other gear elements 58 and 60 (e.g. pinions) arranged inside the housing, which are arranged along other drive axis lines L2 and L3, respectively, which are shown here parallel to the axis line L1. These other drive axis lines can be used to drive other accessories (not shown here) mounted on the housing 50. In particular, due to the position of the web 56b on the pinion shaft 56a so that the web is more or less in a central position relative to the two opposite walls 52a, 52b of the housing, accessories can be arranged on both sides of the wall (in particular on the starter side) without problems of balancing the loads on the drive shafts of these accessories.

[0035] The housing 52 of the accessory gearbox 50 integrates a reduction gear 62 and a free wheel 64, both of which are dedicated to the starter 54 of the turbine, which is similar to Figure 2A different, Figure 2A The intermediate reduction gear 44a and the free wheel 44b are accommodated inside the starter 44 itself.

[0036] like Figure 2BAs shown, the freewheel 64 is arranged on the side of the second end 56a2 of the pinion shaft 56a of the housing 42 and is engaged with the pinion shaft. More specifically, the freewheel 64 is arranged between the web 56b and the second wall 52b of the housing. The reduction gear 62 itself is arranged on the side of the first end 56a1 of the shaft, more specifically, between the first end and the first wall 52a, in particular on the outside of the shaft.

[0037] exist Figure 2B In the exemplary embodiment shown, the freewheel 64 is shown mounted internally to the pinion shaft 56a, but it may also be mounted externally to the shaft.

[0038] Furthermore, a reduction gear 62 is connected to one end 65 a of a fusible keel and disconnector, generally indicated here by reference numeral 65 , and is disposed inside the housing 52 .

[0039] The other end 65b of the assembly 65 is connected to the freewheel 64, for example to a hub of the freewheel, while the outer body of the freewheel is connected to the pinion shaft 56a.

[0040] On the side of the reduction gear 62 oriented to face the first wall 52a, a shaft 66 fixed to the starter 54, for example the shaft of the starter's air turbine, passes through an area of ​​the first wall 52a to partially penetrate the inside of the housing via a through end 66a. The end 66a is provided with a toothed portion or any other device for meshing or coupling with a pinion of the reduction gear 62. The reduction gear generally has an epicyclic gear train structure, and many architectures can be envisioned. The end 66a of the shaft (sun gear) is connected to a planetary gear, the number of which can be between 1 and 5 (actually more commonly 3), and the planetary gear can have two stages (two teeth as shown) or a single stage (a single tooth in a configuration not shown). These planetary gears mesh on a ring gear, which is connected here to the end 65a of the fusible keel (via a spline). In this configuration, both the freewheel and the pinion shaft are coaxially mounted around a (virtual) axis extending the output shaft 66 of the starter (which is aligned), in particular its end 66a. This axis passes through the area of ​​the wall spanned by the starter shaft. In the present exemplary embodiment, the reduction gear of the starter has two stages and is preferably an epicyclic reduction gear, in which case at least three pinions (62b and 62a) are used in each stage to balance the radial forces. In this case, the end 66a of the starter output shaft 66 provided with teeth serves as the sun pinion of the epicyclic reduction gear. Since the reduction gear is coaxial with the freewheel and therefore also with the pinion shaft, their common axis corresponds to the axis of the starter output shaft.

[0041] The permanent integration of a part of the starter formed by the reduction gear 62 and the freewheel 64 in the housing 52 of the accessory gearbox 50 has several consequences: -and Figure 2A Compared with the structure of the starter, the guide bearing of the pinion shaft 56a dedicated to the shaft line L1 of the starter (by Figure 2B The distance between the two ends of the central axis (indicated by the dotted lines) decreases; -and Figure 2A Compared to the configuration of the pinion shaft 56a, the diameter of the pinion shaft 56a (and therefore the inner diameter of the web 56b) is increased, while the outer diameter of the web or the tooth diameter 56b1 remains unchanged; -and Figure 2A Compared with the configuration of the first end 56a, the length of the pinion shaft 56a on the pinion side oriented toward the starter 54 (ie, on the first end 56a1 side) is reduced; -and Figure 2A Compared with the design of the starter, the axial space requirement of the starter is reduced.

[0042] Despite these modifications, the distance d between the first wall 52a of the case and the plane P of the gear train of the case remains unchanged.

[0043] and Figure 2A This arrangement also reduces the axial space requirement of the accessory gearbox 50 equipped with the starter 54 by G compared to the configuration of FIG.

[0044] The reduction in axial space requirements is as follows Figure 2B As shown, Figure 2A The starter 44 is partially shown at the upper left for comparison.

[0045] Figure 3 An exemplary embodiment according to the invention is shown which reproduces the embodiment of the invention by adding an additional drive possibility to the accessory gearbox 70 from the shaft line L1 dedicated to the starter 54. Figure 2B The overall structure of Figure 2B The reference numerals used in the drawings are reproduced for unchanged elements).

[0046] Specifically, a hand crank port HCP, designated 72, is mounted on the exterior of the second wall 52b, axially aligned with the axis line L1, and configured to interface with the gear system inside the housing upon command and allow manual actuation of the system upon command. The hand crank port 72 is only used when the aircraft is on the ground for maintenance operations.

[0047] exist Figure 3 In the illustrated construction, the port 72 is coupled to a drive shaft 74 that extends inside the housing and is connected to the freewheel 64 via one end of the shaft. The opposite end of the shaft 74 is connected to the port 72 and is only used during maintenance operations, as described above. In addition, a rotary seal 76 is installed between the shaft 74 and the crank handle port 72.

[0048] Thus, after the starter starts the turbine, when the starter is disconnected by means of the freewheel 64, the gear train of the accessory gearbox becomes driven by the turbine and thus the HCP function is also disconnected, which makes it possible not to rotate the HCP shaft 74 during normal engine operation.

[0049] Due to the above arrangement, the installed rotating seal 76 is only used occasionally when the HCP function is required (it does not rotate permanently). Therefore, the sealing of the crank port HCP can be ensured by a rotating seal, which has relatively reduced cost and wear compared to a seal that must be sized for a higher speed if the HCP shaft 74 must continue to rotate during normal engine operation after starting.

[0050] Figure 4 An exemplary embodiment according to the invention is shown which reproduces the embodiment of the invention by adding an additional drive possibility to the accessory gearbox 80 from the shaft line L1 dedicated to the starter 54. Figure 2B The overall structure of Figure 2B The reference numerals used in the drawings are reproduced for unchanged elements).

[0051] More specifically, the transmission shaft 82 extends axially between the first end 82a and the second opposite end 82b of the shaft inside the housing 52, especially inside the pinion shaft 56a, and the first end 82a of the shaft is connected to the reduction gear 62, especially the pinion 62a of the reduction gear (here the second stage of the two-stage planetary gear). The second end 82b extends to the second opposite wall 52b of the housing (and can even protrude outwardly beyond the wall, thereby protruding out of the housing) to be connected to equipment outside the housing, such as an oil pump 84.

[0052] Therefore, an external device such as an oil pump 84 is connected to the outlet of the reduction gear 62 integrated into the accessory gear case 80 .

[0053] This arrangement makes it possible to drive a low-capacity pump which ensures the oil supply during lubrication phases, known as marginal lubrication phases, which are carried out only at low speeds, i.e. in particular during the starting of the turbine or during the "motoring" phase. This phase is the engine ventilation phase during which the engine (high-pressure shaft) is driven at low speed on the ground by a starter or an electric motor. This enables combustion chamber ventilation and priming of the turbine fuel system.

[0054] In fact, at low rotation speeds of the high-pressure body of the turbine, and in particular during the start-up of the turbine, the driving speed of the high-pressure body on the gear train of the accessory gearbox is not sufficient to enable the main lubrication unit mounted on the gearbox (including the main supply pump) to be driven at its nominal speed. The main supply pump of this unit is not properly primed or, in any case, does not provide a sufficient flow to ensure proper lubrication of the various components of the turbine that require it (in particular the reduction gear of the starter). During the engine ventilation phase, the engine rotates slowly, while the pump rotates quickly (priming the pump). As a result, the low-capacity pump is supplied with the same flow rate as the main supply pump, but at a speed 10 to 20 times lower than that of the main supply pump.

[0055] Such as Figure 4 The low capacity oil pump of pump 84 in can overcome this disadvantage.

[0056] Such a pump is usually disconnected during normal engine operation, ie when the starter is in disconnect mode.This arrangement enables marginal lubrication needs to be taken into account without having to oversize the main lubrication unit of the turbine to meet these needs.

[0057] Figure 5 Another exemplary embodiment according to the invention is shown, which reproduces the embodiment of the invention by adding an additional drive possibility to the accessory gearbox 90 from the shaft line L1 dedicated to the starter 54. Figure 2B The overall structure of Figure 2B The reference numerals used in the drawings are reproduced for unchanged elements).

[0058] More specifically, the drive shaft 92 extends axially inside the housing 52, in particular inside the pinion shaft 56a, between a first end 92a of the shaft, which is coupled to the reduction gear 62, in particular the pinion 62b of the reduction gear. The second end 92b extends to the second opposite wall 52b of the housing, through which it protrudes outwardly beyond the wall (and therefore beyond the housing) to be coupled to a device outside the housing, such as an electric motor called ETM (engine turning motor) 94. Such ETM motors are used on the ground to rotate the drive shaft of the turbine at a very low speed for a relatively long time, in order to equalize the temperature of the rotor and thus reduce the thermal gradient existing on the rotor.

[0059] Therefore, an external device such as a motor 94 is connected to the inlet of the reduction gear 62 integrated into the accessory gearbox 90, which, as described above, has been connected to the turbine shaft 66 of the starter. The reduction gear 62 is indeed used to reduce the speed between the motor 94 of the ETM, which needs to rotate quickly, and the shaft 56a connected to the outlet of the reduction gear 62. Therefore, the shaft 92 cannot be connected to a pinion with a slower rotation speed, such as the output pinion of the reduction gear.

[0060] This arrangement makes it possible to pool the reduction gear requirements of the starter 54 and the motor 94 by eliminating a specific reduction gear for the motor 94 and allowing the motor to use the reduction gear 62 of the starter integrated in the housing 52 .

[0061] Furthermore, for the previous drive configuration starting from the shaft line L1 dedicated to the starter, the motor 94, which is used only when the aircraft is on the ground, is disconnected from the engine of the turbomachine during normal operation, which makes it possible to eliminate its rotation and therefore avoid any wear of its internal parts when it is not needed. Its reliability is therefore improved. Alternatively, its design costs can be reduced due to less wear of its internal parts.

[0062] Figure 6 Another exemplary embodiment according to the present invention is shown, which basically reproduces Figure 2B The overall structure of Figure 2B The reference numerals used in the drawings are replicated for unchanged elements) and the accessory gearbox 100 is modified by axially offsetting the freewheel 64' to the outside of the pinion shaft 56a', the freewheel 64 still being located on that side of the second opposite end 56a2' of the shaft.

[0063] In this new structure, Figure 2B Compared with the structure of the pinion shaft 56a', the pinion shaft 56b' is elongated (the length of the pinion shaft 56a' is Figure 2A The second wall 52b' of the housing is modified to form an external protrusion 102 (aligned with the axial line L1) which extends axially away from the housing (and away from the first wall 52a), which allows the axial extension of the pinion shaft 56a' and the freewheel 64' to be accommodated in the axial protrusion. The second end 65b' of the fusible keel and disconnector assembly 65' is also modified to follow the offset of the freewheel 64' and thus align with the Figure 2B The structure is lengthened compared to the previous one.

[0064] The elongation of the pinion shaft 56a' has the effect of moving the guide bearings p1 and p2 of the shaft, which are arranged at the two opposite ends 56a1 and 56a2' of the pinion shaft, away from each other. This arrangement ensures better guidance of the axis of rotation of the shaft and therefore less wear on the spur teeth due to better parallelism between the axes of the pinion shafts.

[0065] Furthermore, the axial offset of the freewheel 64 ′ makes it possible not to increase the inner diameter of the pinion shaft dedicated to the starter, thus limiting its mass.

[0066] This arrangement can be envisaged without increasing the axial space requirement of the accessory gearbox 100 and the accessory assembly equipped with the gearbox, as long as the axial space requirement of the protrusion 102 is less than the axial space requirement of an accessory or device 104 mounted on another axial line (such as line L2 parallel to line L1) on the same second wall 52b' as the axial protrusion 102.

[0067] The axial space requirement for the accessory gearbox 100 and accessory components is Figure 6 Indicated as D in the middle.

[0068] Although the present description relates to specific exemplary embodiments, modifications may be applied to these embodiments without departing from the overall scope of the present invention as defined by the claims. Furthermore, the various features of the various illustrated / mentioned embodiments may be combined in additional embodiments. Therefore, the present description and the drawings should be considered in an illustrative rather than a restrictive sense.

Claims

1. An accessory gearbox (50; 70; 80; 90; 100) for an aircraft turbomachine, the accessory gearbox being configured to interface with a starter (54) of the turbomachine, the starter being intended to start the turbomachine, the accessory gearbox include: a housing (52) comprising a first wall and a second opposite wall (52a, 52b; 52b'), the first wall (52a) being intended to interface with a starter (54) of the turbomachine; a reduction gear (62) and a freewheel (64; 64') permanently integrated in the housing and dedicated to the starter of the turbomachine; An axial line (L1) in a housing, the axial line being dedicated to the starter (54) and comprising a pinion shaft (56a; 56a'), the pinion shaft extending between the first wall and the second opposite wall (52a, 52b; 52b') in an axial direction perpendicular to the first wall (52a), the pinion shaft (56a; 56a') comprising two opposite ends, a first end (56a1) being arranged on the side of the first wall (52a) in the housing, and a second end (56a2; 56a2') being arranged on the side of the second opposite wall (52b; 52b') in the housing, the free wheel (64; 64') dedicated to the starter being arranged in the housing on the side of the second end (56a2; 56a2') of the pinion shaft.

2. An accessory gearbox (50; 70; 80; 90; 100) for an aircraft turbomachine according to claim 1, It is characterized in that The first wall (52a) of the housing includes an area which is intended to be spanned by the output shaft (66) of the starter (54), the pinion shaft (56a; 56a') and the freewheel (64; 64') being coaxial with respect to an axis within the area passing through the wall.

3. An accessory gearbox (50; 70; 80; 90) for an aircraft turbomachine according to claim 1 or 2, It is characterized in that The free wheel (64) is mounted inside the pinion shaft (56a).

4. Accessory gearbox (50; 70; 80; 90) for an aircraft turbomachine according to the preceding claim, It is characterized in that The second opposing wall (52b) of the housing is externally provided with a crank handle port (72) which is axially aligned with the shaft line (L1) dedicated to the starter (54) and is configured to allow manual actuation of the gear system inside the housing upon command when the turbine is stopped on the ground.

5. Accessory gearbox (50; 70; 80; 90) for an aircraft turbomachine according to the preceding claim, It is characterized in that The hand crank port (72) is connected to a drive shaft (74) which is connected to a freewheel (64) dedicated to the starter.

6. Accessory gearbox (50; 70; 80; 90) for an aircraft turbomachine according to the preceding claim, It is characterized in that A rotating seal (76) is included between the crank handle port (72) and the drive shaft (74).

7. An accessory gearbox (80; 90) for an aircraft turbomachine according to claim 3, It is characterized in that The housing includes a transmission shaft (82; 92) extending axially inside the pinion shaft (56a) between a first end (82a; 92a) connected to the reduction gear (62) and a second opposite end (82b; 92b) extending to the second opposite wall (52b) of the housing, the second opposite end to be connected to a device (84; 94) outside the housing.

8. Accessory gearbox (80) for an aircraft turbomachine according to the preceding claim, It is characterized in that The second opposite end (82b) of the transmission shaft (82) is intended to be coupled to an oil pump (84) outside the housing.

9. The accessory gearbox (90) for an aircraft turbomachine according to claim 7, It is characterized in that The second opposite end (92b) of the transmission shaft (92) is intended to be coupled to an electric motor (94) outside the casing, the electric motor being dedicated to operating the turbine when the aircraft is on the ground.

10. An accessory gearbox (100) for an aircraft turbomachine according to claim 1 or 2, It is characterized in that The free wheel (64') is mounted outside the pinion shaft (56a').

11. Accessory gearbox (100) for an aircraft turbomachine according to the preceding claim, It is characterized in that The second opposing wall (52b') of the housing comprises an external protrusion (102) extending axially away from the housing (52) and enabling the freewheel (64') to be accommodated.

12. Accessory gearbox (100) for an aircraft turbomachine according to the preceding claim, It is characterized in that It comprises at least one other axial line (L2) extending parallel to the axial direction of the starter's axial line (L1) and intended to interface with another accessory (104), with which the second opposite wall (52b') of the housing is intended to interface.

13. Accessory gearbox (50; 70; 80; 90; 100) for an aircraft turbomachine according to any one of the preceding claims, It is characterized in that The pinion shaft (56a; 56a') carries a web (56b) which is provided with a toothed portion (56b1) at its periphery and is arranged in the distance between the two opposite ends (56a1, 56a2) of the pinion shaft, and the free wheel (64; 64') is arranged between the web (56b) and the second opposite wall (52b; 52b') of the housing.

14. Accessory gearbox (50; 70; 80; 90; 100) for an aircraft turbomachine according to the preceding claim, It is characterized in that The web (56b) is arranged between the reduction gear (62) and the free wheel (64; 64').

15. Accessory gearbox (50; 70; 80; 90; 100) for an aircraft turbomachine according to any one of the preceding claims, It is characterized in that The reduction gear (62) is disposed in the housing on the side of the first end (56a1) of the pinion shaft (56a; 56a').

16. Accessory gearbox (50; 70; 80; 90; 100) for an aircraft turbomachine according to the preceding claim, It is characterized in that The reduction gear (62) is arranged outside the pinion shaft (56a, 56a').

17. Accessory gearbox (50; 70; 80; 90; 100) for an aircraft turbomachine according to the preceding claim, It is characterized in that The reduction gear (62) is disposed between a first end (56a1) of the pinion shaft (56a; 56a) and a first wall (52a) of the housing.

18. Accessory gearbox (50; 70; 80; 90; 100) for an aircraft turbomachine according to the preceding claim, It is characterized in that The reduction gear (62) is coupled to a fusible member (65) disposed inside the pinion shaft (56a; 56a').

19. An assembly comprising an accessory gearbox (50; 70; 80; 90; 100) for an aircraft turbine according to any of the preceding claims and a starter (54) docked with the gearbox, the starter (54) comprising an output shaft (66) arranged coaxially with the pinion shaft (56a; 56a').

20. An aircraft turbomachine comprising an accessory gearbox (50; 70; 80; 90; 100) for an aircraft turbomachine according to any one of claims 1 to 18 or an assembly according to claim 19.

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