Planetary gearbox system and method for operating a planetary gearbox system

Abstract

A planetary gearbox system with a ring gear, a sun gear, a carrier and planetary gears as parts in a geared aircraft turbofan engine, with one static part of the parts being in rest under nominal operation and with a kinematic switch device for decoupling the static part to become a rotatable part or with a kinematic switch device for coupling the rotatable part to become a static part. The invention also relates to a method for operating a planetary gearbox system.

Claims

1. A planetary gearbox system of a geared aircraft turbofan engine, comprising: a plurality of parts including: a ring gear, a sun gear, a carrier, planetary gears, at least one kinematic switch device, wherein a static part of the plurality of parts is in rest under nominal operation, wherein the at least one kinematic switch device is suitable for at least one chosen from: decoupling the static part to become rotatable, and coupling a rotatable part of the plurality of parts to become static, wherein the at least one kinematic switch device comprises two connecting parts and a position change mechanism to automatically trigger a position change in at least one of the two connecting parts relative to at least one chosen from the other of the two connecting parts and an engine part, from a first position into a second position in dependence of a non-nominal torque or a reversal in a direction of a torque effective on at least one chosen from one of the two connecting parts and the engine part, and wherein the position change mechanism comprises at least one chosen from a helical spline connection between the two connecting parts, an explosive bolt device, an automatic clutch device and a hydraulic device, wherein the two connecting parts are directly connected to at least one chosen from a shaft and the ring gear.

2. The planetary gearbox system according to claim 1, wherein the static part which is decouplable or the rotatable part which is couplable is the ring gear of an epicyclic planetary gearbox system or the carrier of a star-design planetary gearbox system.

3. The planetary gearbox system according to claim 1, wherein the at least one kinematic switch device includes at least one chosen from a mechanical fuse for decoupling the static part into a rotatable part and a clutch device for decoupling the static part or coupling the rotatable part.

4. The planetary gearbox system according to claim 1, wherein the decoupling of the static part is triggered by a predetermined kinematic condition.

5. The planetary gearbox system according to claim 4, wherein the predetermined kinematic condition comprises 1) a torque acting on one of the plurality of parts exceeding a threshold value or 2) a direction of torque acting on one of the plurality of parts changing direction.

6. The planetary gearbox system according to claim 1, wherein the decoupling of the static part or coupling of the rotatable part is effected by the kinematic switch device operating an actuator.

7. The planetary gearbox system according to claim 1, wherein the decoupled part generates additional power under rotation.

8. The planetary gearbox system according to claim 1, and further comprising at least one chosen from: wherein torque transmission characteristics of the helical spline connection are asymmetric relative to a torque applied to the helical spline connection, and the automatic clutch device comprises a device for balancing axial loads.

9. The planetary gearbox system according to claim 1, wherein: in the first position, the two connecting parts are mechanically engaged with at least one chosen from each other and with the engine part, so that torque is transmittable between the two connecting parts, and in the second position, the two connecting parts are mechanically disengaged from at least one chosen from each other and the engine part, enabling a free relative movement between the two connecting parts and the engine part.

10. The planetary gearbox system according to claim 1, and further comprising at least one chosen from: wherein at least one chosen from a first one and a second one of the two connecting parts is coupled to a ring gear mount of the gearbox, wherein at least one chosen from the first one and the second one of the two connecting parts is rigidly connected to the ring gear mount of the gearbox, wherein at least one chosen from the first one and the second one of the two connecting parts is one piece with the ring gear mount of the gearbox, and wherein at least one chosen from the first one and the second one of the two connecting parts is coupled with a static structure of the aircraft turbofan engine.

11. The planetary gearbox system according to claim 1, wherein at least one chosen from a first one and a second one of the two connecting parts is coupled to the static part.

12. The planetary gearbox system according to claim 1, wherein the engine part is positioned in the first position fixedly relative to the two connecting parts and in the second position, at least one of the two connecting parts is movable relative to the engine part.

13. The planetary gearbox system according to claim 12, comprising the automatic clutch device, wherein a first one and a second one of the two connecting parts each comprises a contact interface with the engine part, the contact interfaces being parallel to each other or angled to each other.

14. The planetary gearbox system according to claim 1, wherein the engine part comprises a ring structure which is positioned in the first position between the two connecting parts, the two connecting parts also comprising ring structures.

15. The planetary gearbox system according to claim 1, and further comprising a clamping preloading device to apply a predetermined force to the kinematic switch device.

16. The planetary gearbox system according to claim 15, and further comprising an axial retention device.

17. The planetary gearbox system according to claim 1, wherein a connection between at least one of the two connecting parts and the engine part comprises a high friction coating on at least one surface of an interface of the at least one of the two connecting parts and the engine part.

18. The planetary gearbox system according to claim 16, wherein at least one chosen from a connection between the clamping preloading device and the engine part and a connection between the axial retention device and the at least one of the two connecting parts comprises a low friction coating on at least one surface.

19. The planetary gearbox system according to claim 1, wherein the planetary gearbox system is coupled to a propulsive fan of the geared aircraft turbofan engine, the propulsive fan being suitable for at least one chosen from: driving an electrical generator in windmilling operation conditions, and being driven by external power source when decoupled through the automatic clutch device from a primary power source.

20. A method for operating a planetary gearbox system with a ring gear, a sun gear, a carrier and planetary gears as a plurality of parts in a geared aircraft turbofan engine, wherein a static part of the plurality of parts is in rest under nominal operation and the static part is decoupled with a kinematic switch device to become rotatable or a rotatable part is coupled with a kinematic switch device to become static, wherein the kinematic switch device comprises two connecting parts and a position change mechanism to automatically trigger a position change in at least one of the two connecting parts relative to at least one chosen from the other of the two connecting parts and an engine part, from a first position into a second position in dependence of a non-nominal torque or a reversal in a direction of a torque effective on at least one chosen from one of the two connecting parts and the engine part, and wherein the position change mechanism comprises at least one chosen from a helical spline connection between the two connecting parts, an explosive bolt device, an automatic clutch device and a hydraulic device, wherein the two connecting parts are directly connected to at least one chosen from a shaft and the ring gear.

Description

(1) Embodiments of the invention are shown in the figures, where

(2) FIG. 1 shows a schematic drawing of a geared aircraft turbofan engine according to the prior art;

(3) FIG. 2 shows a schematic drawing of the frontal portion of a turbofan engine with a planetary gearbox system (epicyclic planetary arrangement) with different location of kinematic switch devices;

(4) FIG. 3 shows a schematic drawing of the frontal portion of a turbofan engine with a planetary gearbox system (star arrangement) with different location of kinematic switch devices;

(5) FIG. 4A shows a schematic representation of an embodiment of a mechanical switch device in a first engaged position;

(6) FIG. 4B shows a schematic representation of the embodiment in FIG. 4A in a second disengaged position;

(7) FIG. 5A shows a schematic representation of a further embodiment of the kinematic switch device in a first engaged position;

(8) FIG. 5B shows a schematic representation of the embodiment shown in FIG. 5A in a second disengaged position;

(9) FIG. 6A shows a schematic representation of a further embodiment of the kinematic switch device in a first engaged position;

(10) FIG. 6B shows a schematic representation of the embodiment shown in FIG. 6A in a second disengaged position;

(11) FIG. 7 shows a diagram of the torque and power transmission in an embodiment of the kinematic switch device;

(12) FIG. 8A shows a schematic drawing of an embodiment of a kinematic switch device with a means for balancing axial loads under nominal conditions;

(13) FIG. 8B shows the embodiment of FIG. 8 under torques with different rotation directions.

(14) With reference to FIG. 1, a geared turbo fan engine is generally indicated at 10, having a principal and rotational axis 11. The engine 10 comprises, in axial flow series, an air intake 32, a propulsive fan 13 (could be more than one stage), a gearbox 14, an intermediate pressure compressor 15, a high-pressure compressor 16, a combustion equipment 17, a high-pressure turbine 18, an intermediate-pressure turbine 19 and an exhaust nozzle 20. A fan casing 21 generally surrounds the engine 10 and defines the intake 32.

(15) The geared turbofan engine 10 works in the conventional manner so that air entering the intake 32 is accelerated by the propulsive fan 13 to produce two air flows: a first air flow into the intermediate pressure compressor 15 and a second air flow which passes through a bypass duct 22 to provide the main propulsive thrust. The intermediate pressure compressor 15 compresses the air flow directed into it before delivering that air to the high pressure compressor 16 where further compression takes place.

(16) The compressed air exhausted from the high-pressure compressor 16 is directed into the combustion equipment 17 where it is mixed with fuel and the mixture is combusted. The resultant hot combustion products then expand through, and thereby drive the high pressure turbine 18 and intermediate pressure turbine 19 before being exhausted through the nozzle 20 to provide additional propulsive thrust. The high pressure turbine 18 and the intermediate pressure turbine 19, respectively, drive the high pressure compressor 16 and the intermediate pressure compressor 15, each by suitable interconnecting shaft assembly.

(17) An intermediate pressure shaft also drives the propulsive fan 13 via the gearbox 14. The gearbox system 14 comprises a reduction gearbox in that it gears down the rate of rotation of the propulsive fan 13 by comparison with the intermediate pressure compressor 15 and intermediate pressure turbine 19.

(18) The gearbox system 14 in the embodiment shown is an epicyclic planetary gearbox system 14 having a static ring gear 109, rotating and orbiting planet gears 103 supported by a planet carrier 104 and a rotating sun gear 102. In an alternative embodiment, the gearbox 14 has star arrangement, so that the ring gear can be disconnected from the propulsive fan or the carrier from a structure.

(19) The embodiment shown in FIG. 1 has a specific shaft arrangement which is understood not to be limiting. The embodiments described in the following can also work with a 2- or 3-shaft arrangement.

(20) As shown in FIG. 1, geared turbofan engines 10 are known in the art. With increasing power ratings and/or increasing diameters of the propulsive fans 13, the loads on the geared turbofan engine 10 are increasing. Therefore, it seems advisable to introduce flexible measures to operate rotational parts and e.g. counteract potential failure modes or extreme events such as e.g. a fan blade off, a core blade off, a bird strike, a mainline bearing seizure or a gearbox system 14 seizure.

(21) For this purpose the planetary gearbox system 14 comprises kinematic switch device 1 for decoupling a static part of the gearbox system 14 to become a rotatable part or a kinematic switch device 1 for coupling the rotatable part of the gearbox system 14 to become a static part. Different design embodiments using e.g. helical splines and clutch mechanisms will be described in the FIGS. 4 to 8. In general kinematic switch device 1 can e.g. comprise two connecting means 31, 32 (e.g. with helical splines) and means 40 to automatically trigger a position change in least of one of the two connecting parts 31, 32 relative to the respective other connecting part 32, 31 and/or relative to an engine part 41 from a first position into a second position in dependence of a torque T effective on at least one of the two connecting parts 31, 32 and/or the engine part 41, in particular through the transmission via a shaft 106, 108, in particular a non-nominal torque T or a reversal in the direction of the torque T.

(22) In FIG. 2 first some design context for the placement of the kinematic switch device 1 is given. The view of FIG. 1 is a cross-section through the front of a geared turbofan engine 10 (see e.g. FIG. 1). Here, the gearbox 14 is having an epicyclic planetary arrangement.

(23) The turbine (not shown in FIG. 2) is driving the sun gear 102 of the gearbox 14. The torque is transmitted via the planetary gears 103 to the carrier 104 providing the output torque of the gearbox system 14 (indicated by the arrow). The ring gear mount 101 and the ring gear 109 are static relative to the other parts of the gearbox system 14 under nominal conditions.

(24) In the following, three possible locations 1A, 1B, 1C for a kinematic switch device 1 are discussed.

(25) The first location 1A of a kinematic switch device 1 is in the driving shaft 106 of the sun gear 102.

(26) This means that e.g. the connecting parts 31, 32 are part of the driving shaft. The connecting parts 31, 32 (e.g. like the one shown in FIG. 4A, 4B) can change their relative positions to each other as triggered by a change in the torque direction.

(27) An alternative or additional second location 1B is between the static ring gear mount 101 and a fixed part 107 of the air craft engine 10.

(28) A further alternative or additional third location 10 is in an output shaft 108 of the gearbox system 14.

(29) In each case, two connecting parts 31, 32 are under nominal conditions at reststaticrelative to each other. The connecting parts 31, 32 can disengage under non-nominal conditions. But it also possible that after some time in the disengagement position, a reengagement of the connection parts 31, 32 takes place. With the position change of the connection parts 31, 32 the static part 109 of the epicyclic planetary gearbox system 14 can be decoupled and coupled.

(30) In FIG. 3 a similar embodiment to the one in FIG. 2 is described. The main difference is that the gearbox 14 comprises a star arrangement.

(31) The sun gear 102 is driven, driving the planet gears 103 with a fixed carrier 104. The output torque is transmitted via the ring gear 109 and the ring gear mount 101 to the output shaft 108.

(32) The first location 1A of a kinematic switch device 1 in this arrangement is in the driving shaft 106 of the sun gear 102. This means that e.g. the connecting parts 31, 32 are part of the driving shaft. The connecting parts 31, 32 (e.g. like the one shown in FIG. 4A, 4B) can change their relative positions to each other as triggered by a change in the torque direction.

(33) An alternative or additional second location 1B is between the static carrier 104 and a fixed part 107 of the air craft engine 10.

(34) A further alternative or additional third location 10 is in an output shaft 108 of the gearbox system 14.

(35) In each case, two connecting parts 31, 32 are under nominal conditions at reststaticrelative to each other. The connecting parts 31, 32 can disengage under non-nominal conditions. But it is also possible that after some time in the disengagement position, a reengagement of the connection parts 31, 32 takes place. With the position change of the connection parts 31, 32 the static part 104 (i.e. the carrier) of the star design planetary gearbox system 14 can be decoupled and coupled.

(36) FIGS. 2 and 3 show different locations for the kinematic switch device 1. It is understood that other locations are possible.

(37) In FIG. 4A, 4B the operation of an embodiment of a kinematic switch device 1 is shown. This can be used in various locations within the geared turbofan engine, in particular with the geared turbofan engine 10 as shown in FIG. 1.

(38) The kinematic switch device two connecting parts 31, 32. Connecting means in this context that the parts can be connected but the can also become disengaged or reengaged. This can be considered as a switching step.

(39) Typical positions within an aircraft engine of such connecting parts of a kinematic switch device 1 are shown in FIGS. 2 and 3.

(40) A first engaged position is shown in FIG. 4A. Here, the first connecting part 31 is positioned fixedly relative to a ring gear mount 101 or a ring gear 109 of a gearbox system 14 of the geared turbofan engine 10. It should be noted that FIG. 4A shows this geometric relationship only in a very schematic way.

(41) The second connecting part 32 is positioned fixedly relative to an engine part 33, which can be any static part within the geared turbofan engine 10. In FIGS. 2 and 3 the position of a fixed part 107 of an engine is shown.

(42) Furthermore, the kinematic switch device 1 comprises means 40 for automatically triggering a position change (e.g. an disengagement, engagement, reengagement) by bringing at least one of the connecting parts 31, 32 relative to the other connecting parts 32, 31 into a disengagement position in dependence of the effective torque T on the connecting parts 31, 32.

(43) The second position (i.e. the disengagement position) is shown in FIG. 4B.

(44) That means that the first and second connecting parts 31, 32 have moved apart. This can be achieved e.g. by moving the first connecting part 31 relative to the second connecting part 32, by moving the second connecting part 32 relative to the first connecting part 31 or a mutual movement of both connecting parts 31, 32.

(45) In FIG. 4B the connecting parts 31, 32 are moved apart for reasons of clarity. As will be shown in connection with FIG. 5A, 5B the kinematic switch device 1 can comprise further engine parts 41.

(46) The movement of the connecting parts 31, 32 is here demonstrated with two parts 31, 32 assembled axially. As will be shown below, the connecting parts 31, 32 can have other geometric conformations and can perform other movements.

(47) The means 40 for automatically triggering the position change (e.g. engagement, disengagement) comprise in the embodiment shown, a helical spline.

(48) Helical splines have ridges or teeth that mesh with grooves in a mating piece and transfer torque to it. A helical spine comprises equally spaced grooves forming a helix about the shaft. The sides may be parallel or involute. This can either minimize stress concentrations for a stationary joint under high load, or allow for rotary and linear motion between the parts. Another feature of the helical spline is that it reacts differently to torque T in different directions. Furthermore, the helical spline generates an axial load which can open or close the kinematic switch; a helical spline can translate an angular movement into an axial movement. In embodiments shown the helical angle can be between 15 and 75.

(49) In FIG. 4A, the torque T is applied in the nominal direction and is transmitted through the rotating shafts 106 (see FIG. 1) on the connecting parts 31, 32. The connecting parts 31, 32 are connected in the first engaged position so they can absorb the torque T; the helical spline connection is pulling the connecting parts 31, 32 together.

(50) If the direction of the torque T changes (e.g. into the non-nominal direction T), the reverse process happens, i.e. the helical spline connection opens into the second position, disengaging two connecting parts 31, 32.

(51) In other embodiments, the means 40 for automatically trigger the position change can comprise e.g. an explosive bolt device which is activated depending on the acting torque T, T. In addition or alternatively, the means for automatically triggering the position change can comprise an automatic clutch.

(52) It should be noted that the reversal of the torque direction T, T does not have to be connected with a non-nominal event. The disengagement of the kinematic switch device 1 is effected rather in dependence of the torque effectively present at the connecting parts 31, 32.

(53) In FIG. 5A, 5B a different embodiment is shown involving a kinematic switch device 1 coupled with a driven engine part 41 in the first position.

(54) The connecting parts 31, 32 interact in the first position (i.e. an engaged position) with the engine part 41 by clamping it (see FIG. 5A) in the first position. This can also be termed as a three plate flange.

(55) The connecting parts 31, 32 become rotatable as they are moved apart (see FIG. 3B) into the second position (i.e. a disengaged position). In the embodiment shown the engine part 41 is a part of a front panel.

(56) In FIG. 5A the first connection part 31 is coupled to a ring gear mount 101 of the gearbox system 14 (not shown in FIG. 5A). The second connection part 32 is connected to a sleeve. The two connection parts 31, 32 are connected through a helical spline 42. The concept of the helical spline is described in connection with FIG. 4A, 4B so that reference can be made to that description.

(57) In the engaged first position shown in FIG. 5A, the torque path TP is shown. Essentially, the engine part 41 (i.e. sleeve) is clamped between the two connection parts 31, 32.

(58) The connection parts 31, 32 have both ring like sections (i.e. pointing into the radial direction) with parallel interfaces A, B with the engine part 41. The engine part 41 is positioned and clamped between the connection parts 31, 32 by friction-locking. The clamping forces C acting on the interfaces A, B are shown in FIG. 3A.

(59) In other alternatives, the connection parts 31, 32 can be form-locked with the engine part 41. Also, a mixture of form-locking and friction-locking can be used to clamp the engine part 41 in the engaged position.

(60) In FIG. 5B the kinematic switch device 1 is shown in the second position, i.e. a disengaged position. A reversal from of the torque effective on the connection parts 31, 32 has caused the helical spline connection 42 to move apart, but not completely. Therefore, the friction-locking and/or form-locking of the engine part 41 is disengaged. The disengagement now allows a free rotation of the propulsive fan 13 (see e.g. FIG. 2 or 3).

(61) As shown in FIG. 5B the torque path TP no longer passes through the engine part 41, so that the connecting parts 31, 32 can move freely.

(62) In one embodiment, at the interface A, B of the engine part 41 a coating with a high friction (0.3 to 0.9) coefficient (larger than 0.5) is used to facilitate clamping in the engaged position (FIG. 4A, 5A).

(63) In FIG. 6A, 6B a variation of the embodiment in FIG. 5A, 5B is shown so that reference can be made to the respective description.

(64) As in the embodiment shown in FIG. 5A, 5B the first and second connection parts 31, 32 clamp an engine part 41 in a first position. This is the engagement position.

(65) In addition to these parts, a clamping preloading device 50 is in contact with the second connecting part 32. There is a preloading force acting from the preloading device 50 onto the second connecting part 32. Hence, the second connecting part 32 is pressed against the engine part 41 with a pre-clamping. This achieves some friction even if there is no torque and it put the parts in a fixed position under normal operation. This preload has to be overcome by the force generated by the helical spline before the kinematic switch device 1 (e.g. a clutch) is opening. Further, it guarantees the ability of closure of the clutch with the second connecting part 32 in contact guaranteeing the torque path TP through the helical spline.

(66) This arrangement also results in a different torque path TP. The torque path extends into the torque preloading device 50.

(67) In one embodiment, the torque preloading device 50 comprises a plate for an abutment of the second static part 42. Alternatively or in addition, a spring device or an elastic device can provide some additional preloading force to the second static part 42.

(68) In FIG. 6A also an axial retention device 60 is shown, which limits the axial movements of the first connection part 31. In the first position (shown in FIG. 6A) there is no contact between axial retention device 60 and the first connection part 31.

(69) Embodiments as shown in FIG. 5A, 58 only having an additional axial retention device 60 or a torque preloading device 50 are possible.

(70) In FIG. 6B the embodiment of the kinematic switch device 1 is shown in a second position in which the engine part 41 is disengaged from the connection part 31, 32. The first connection part 31 now abuts the axial retention device 60. The disengagement now allows a free rotation of the propulsive fan 13.

(71) The effect of the torque preloading 50 can be seen schematically in FIG. 7 illustrating the transmittable torque T, T through a kinematic switch device 1.

(72) The power which is generated or consumed by a geared turbofan engine 10 with a propulsive fan 13 is plotted on the x-axis. Positive power values represent nominal operation, i.e. the turbine is driving the system. Negative power values represent a non-nominal case in which the system is driven by the propulsive fan 13 (e.g. windmilling in case of a gearbox failure, no driving through turbine).

(73) The transmittable torque T, T is plotted on the y-axis.

(74) In the first quadrant I the geared turbofan engine 10 is turbine driven and the torque T is positive, i.e. the operation is nominal.

(75) Due to a pre-loading of the kinematic switch device 1, there is a positive intercept of the transmittable torque T line with the y-axis.

(76) The slope of the dashed line indicating the transmittable torque T is smaller than the slope of the line representing the torque the ring gear mount. At the point where the transmittable torque T becomes smaller than the ring gear torque, the clutch in the mechanical switch device 1 begins to slip.

(77) In the third quadrant III the sign of the transmittable torque T is reversed and the kinematic switch device 1 moves from the first to the second position disengaging the engine part 41 in the process. The engine part 41 is connected with the propulsive fan 13 which now can turn freely in windmilling mode. Thereby, some torque can be transmitted, which can e.g. drive a generator of generating electrical power.

(78) The torque preloading device 50 has the effect that at zero power generation, i.e. with the engine at rest, some preloaded torque is present. This can be seen by the positive offset O and negative offset O along the y-axis. This implies that for the change in the position of the connecting parts 31, 32 the preloaded torque needs to be overcome before the clamped engine part 41 becomes disengaged.

(79) At the point at which the absolute value of the transmittable torque T becomes smaller than the ring gear mount torque, the clutch (i.e. here the kinematic switch device) disengages.

(80) In FIGS. 8A and 8B an embodiment of a kinematic switch device 1 with two helical spline connections 42A, 42B is shown. The embodiment is a variation of the embodiments described in connection with FIG. 3A, 3B, 4A, 4B so that reference can be made to the respective description.

(81) As in the embodiment of FIG. 4A, 4B the first and second connection parts 31, 32 clamp an engine part 41 in a first position. This is the engagement position shown in FIG. 8A. But here both connection parts 31, 32 comprise helical spline connections 42A, 42B. The rotational arrangement are such that under nominal conditions (FIG. 8A) the torque flow causes axial loads in opposite directions on the engine part 41 (e.g. a front panel).

(82) If the torque direction for some reason is reversed, the helical spline connections 42A, 42B are moving apart, so that no clamping force is acting on the engine part 41 (FIG. 8B). The torque path TP now goes from the first connection part 31 to the second connecting 32 without going through the engine part 41.

(83) The embodiments described herein can e.g. be used in connection with a management of the rotatory behavior of the propulsive fan 13. Under certain operating conditions, the propulsive fan 13 is not required to provide thrust (e.g. windmilling after a gearbox 14 seizure or another failure, descent phase of an airplane). The decoupling of the propulsive fan 13 using a mechanical clutch device 1 provides an operation regime in which the propulsive fan 13 can freely rotate. If e.g. the operation requires a reengagement, the mechanical clutch device 1 couples the propulsive fan 1 back to a torque T source, e.g. a turbine stage.

LIST OF REFERENCE NUMBERS

(84) 1 kinematic switch device 1A location for kinematic switch device 1B location for kinematic switch device 1C location for kinematic switch device 10 geared turbo engine 11 principal rotational axis 12 air intake 13 propulsive fan 14 planetary gearbox system, power gearbox 15 intermediate pressure compressor 16 high-pressure compressor 17 combustion equipment 18 high-pressure turbine 19 intermediate-pressure turbine 20 exhaust nozzle 21 fan casing 22 by-pass duct 31 first connecting part 32 second connecting part 33 engine part 40 means for automatically triggering the kinematic switch device 41 engine part, front panel 42 helical spline connection 42A first helical spline connection 42B second helical spline connection 50 clamping preloading device 60 axial retention device 101 ring gear mount 102 sun gear of power gearbox 103 planetary gear 104 carrier 106 driving shaft of sun gear 107 fixed part of engine 108 output shaft of gearbox 109 ring gear A first interface between parts B second interface between parts O offset of torque due to preloading (nominal direction) O offset of torque due to preloading (non-nominal direction) T torque (nominal direction) T torque (non-nominal direction) TP torque path