Turbojet engine starting motor device
By using DC brushless external rotor motor and overclutch design, the problem of large volume and weight of the traditional turbojet engine starting motor system is solved, and the lightweight and efficient air intake of the turbojet engine is achieved, and the thrust-to-weight ratio and performance are improved.
Patent Information
- Application Number
- CN202422530380.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-10-18
- Publication Date
- 2025-07-08
- Estimated Expiration
- 2034-10-18
AI Technical Summary
The starting motor system of traditional turbojet engines has a large volume and weight, which affects the engine's intake efficiency, resulting in insufficient thrust-to-weight ratio, limiting engine performance.
The DC brushless outer rotor motor and overpass clutch design are adopted, including bushing, jacket and cylindrical pin. Through the clearance fit and spiral groove structure, the starting motor is lightweight and miniaturized, and a Hall sensor is installed at the air inlet position to measure the speed.
The total weight of the turbojet engine is reduced, the thrust-to-weight ratio is improved, the intake efficiency is increased, and the performance and safety of the engine are improved.
Smart Images
Figure CN223075627U_ABST
Abstract
Description
Technical Field
[0001] The utility model belongs to the technical field of turbojet engines, and particularly relates to a starting motor device for a turbojet engine. Background Technique
[0002] When a turbojet engine starts on the ground, an external power source must be used. Because when the engine rotor does not rotate, the air in the combustion chamber is not compressed, and the air does not flow into the engine. In this case, if fuel is injected and burned in the combustion chamber, only the engine can be burned out, and the engine rotor will not rotate. When the engine speed is very low, even if the maximum allowable value of the gas temperature is maintained in front of the turbine, the engine still cannot start. This is because at a very low speed, the pressure ratio of the compressor is very low, and the efficiency of the compressor and the turbine is also very low. The power generated by the turbine is less than the power required by the compressor. Only when the speed reaches a certain value, and the gas temperature in front of the turbine remains at the maximum allowable value, can the engine operate stably. This speed is called the minimum stable operating speed, and the minimum stable operating speed is generally 10% of the maximum speed. When the engine speed exceeds the minimum stable operating speed, when the gas temperature in front of the turbine is at the maximum allowable value, the turbine efficiency is greater than the compressor power, and the engine speed can rise driven by the remaining power of the turbine. Therefore, an external power source must be used to bring the engine speed above the minimum stable operating speed during the engine startup process.
[0003] The ratio of the thrust of the engine to the weight of the engine is called the thrust-to-weight ratio of the engine. It directly affects the mass and payload of the aircraft. Therefore, it has a direct impact on the maneuverability of the aircraft such as the maximum level flight speed, ceiling, and climbing speed. Therefore, a higher thrust-to-weight ratio is required. When the thrust of the engine is certain, there are strict requirements for the total weight of the engine. The starting motor of the micro turbojet engine is located at the air inlet position, and the traditional brushed motor system design has a large volume and weight, which affects the air intake efficiency of the engine. Summary of the Invention
[0004] The technical problem to be solved by the utility model is to provide a starting motor device for a turbojet engine, which can increase the thrust-to-weight ratio of the turbojet engine and improve the performance of the turbojet engine.
[0005] To solve the above technical problem, the technical solution of the utility model is:
[0006] A turboprop engine starting motor device, the turboprop engine using the turboprop engine starting motor device includes an air intake casing and an engine rotating shaft. At one end of the engine rotating shaft close to the air intake casing, a front shaft nut and a compressor impeller are fixedly arranged. At the other end of the engine rotating shaft, a turbine is fixedly arranged. The turboprop engine starting motor device includes a starting motor and an overrunning clutch. The starting motor has a starting motor shaft. The overrunning clutch includes a bushing, an outer sleeve, and a cylindrical pin. The outer sleeve is sleeved on the outer surface of the bushing. The bushing is sleeved on the outer surface of the starting motor shaft. A set screw is arranged on the bushing and abuts against the outer surface of the starting motor shaft. The cylindrical pin is connected to the bushing, and both ends of the cylindrical pin extend out of the bushing. Two spiral grooves are arranged on the outer sleeve in the circumferential direction, and both ends of the cylindrical pin are respectively inserted into the corresponding spiral grooves.
[0007] Further, a sealing ring is arranged at one end of the outer sleeve facing the front shaft nut.
[0008] Further, the outer sleeve is provided with an outer sleeve arc groove, and the sealing ring is located in the outer sleeve arc groove.
[0009] Further, the front shaft nut is provided with a nut arc groove; when the outer sleeve contacts the front shaft nut to transmit torque, the sealing ring is simultaneously located in the outer sleeve arc groove and the nut arc groove.
[0010] Further, a housing is fixedly arranged on the outer surface of the outer sleeve, and the sealing ring is arranged at the end of the housing facing the front shaft nut.
[0011] Further, the two spiral grooves are respectively defined as spiral groove one and spiral groove two. A horizontal section A is arranged at one end of spiral groove one close to the front shaft nut, and a horizontal section B is arranged at one end of spiral groove two close to the front shaft nut.
[0012] Further, a magnet is arranged on the bushing close to one end facing the starting motor.
[0013] Further, a boss is arranged on the outer surface of the bushing, and the magnet and the set screw are both arranged on the boss.
[0014] Further, two magnetic steels are arranged on the front shaft nut, and a Hall sensor is arranged in the air intake casing.
[0015] Further, a groove is arranged on the outer surface of the starting motor shaft, the bottom of the groove is a plane structure, and the set screw abuts against the bottom of the groove.
[0016] Due to the adoption of the above technical solutions, the beneficial effects of the present utility model are:
[0017] The turboprop engine using the starting motor device of the utility model includes an air inlet casing and an engine rotating shaft. At one end of the engine rotating shaft close to the air inlet casing, a front shaft nut and a compressor impeller are fixedly arranged. At the other end of the engine rotating shaft, a turbine is fixedly arranged. The starting motor device of the turboprop engine includes a starting motor and an overrunning clutch. The starting motor has a starting motor shaft. The overrunning clutch includes a bushing, an outer sleeve, and a cylindrical pin. The outer sleeve is sleeved on the outer surface of the bushing. The bushing is sleeved on the outer surface of the starting motor shaft. A set screw is arranged on the bushing, and the set screw abuts against the outer surface of the starting motor shaft. The cylindrical pin is connected to the bushing, and both ends of the cylindrical pin extend out of the bushing. Two spiral grooves are arranged on the outer sleeve in the circumferential direction, and both ends of the cylindrical pin are respectively inserted into the corresponding spiral grooves. For the starting motor device of the turboprop engine of the utility model, the structure of the overrunning clutch is simple, small in volume and light in weight. When in use, it can reduce the total weight of the turboprop engine, increase the thrust-to-weight ratio of the turboprop engine, and improve the performance of the turboprop engine. BRIEF DESCRIPTION OF THE DRAWINGS
[0018] Figure 1 is a schematic structural diagram of a turboprop engine using the starting motor device of the utility model;
[0019] Figure 2 is a schematic structural diagram of the starting motor device of the turboprop engine of the utility model;
[0020] Figure 3 is Figure 1 a schematic structural diagram of the nut in
[0021] Figure 4 is Figure 3 a sectional view taken along the A-A direction in
[0022] Figure 5 is a perspective view of the first embodiment of the overrunning clutch of the starting motor device of the turboprop engine of the utility model;
[0023] Figure 6 is Figure 5 a schematic structural diagram of the overrunning clutch in
[0024] Figure 7 is Figure 6 a rear view of
[0025] Figure 8 is Figure 6 a side view of
[0026] Figure 9 is Figure 8 a sectional view taken along the B-B direction in
[0027] Figure 10It is a schematic structural diagram of the overrunning clutch of the starting motor device of the turbojet engine of the present utility model in the second embodiment;
[0028] Figure 11 It is a schematic structural diagram of the overrunning clutch of the starting motor device of the turbojet engine of the present utility model in the third embodiment;
[0029] Figure 12 Is Figure 11 The rear view of;
[0030] Figure 13 It is a schematic structural diagram of the overrunning clutch of the starting motor device of the turbojet engine of the present utility model in the fourth embodiment;
[0031] Figure 14 Is Figure 13 The sectional view taken along the line C-C in;
[0032] In the figure, 1, Hall sensor; 2, starting motor; 21, starting motor shaft; 3, thrust bearing; 4, bushing; 41, boss; 5, motor bracket; 6, set screw; 7, outer sleeve; 71, first spiral groove; 711, horizontal section A; 72, second spiral groove; 721, horizontal section B; 8, sealing ring; 9, front shaft nut; 91, nut arc groove; 10, magnet; 11, cylindrical pin; 111, first end; 112, second end; 12, compressor impeller; 13, magnet; 14, housing; 15, inlet casing; 16, engine rotating shaft; 17, turbine. Specific embodiments
[0033] The present utility model will be further described below with reference to the drawings and embodiments.
[0034] Combined with Figure 1 As shown, in this embodiment, the turbojet engine using the starting motor device of the turbojet engine of the present utility model includes an inlet casing 15 and an engine rotating shaft 16. A front shaft nut 9 and a compressor impeller 12 are fixedly arranged at one end of the engine rotating shaft 16 close to the inlet casing 15, and a turbine 17 is fixedly arranged at the other end of the engine rotating shaft 16.
[0035] Combined with Figure 1 , Figure 2 , Figure 3 , and Figure 4 As commonly shown, two magnets 10 are arranged on the front shaft nut 9, and a Hall sensor 1 is arranged in the inlet casing 15. The Hall sensor 1 is preferably installed on the mounting plate in the inlet casing 15. The installation directions of the magnetic poles of the two magnets 10 are the same, and the rotational speed of the engine rotating shaft 16 can be measured by using the Hall sensor 1.
[0036] Combined with Figure 1 And Figure 2As shown together, the turbojet engine starting motor device includes a starting motor 2 and an overrunning clutch, and the starting motor 2 has a starting motor shaft 21.
[0037] The starting motor 2 preferably adopts a DC brushless outer rotor motor, which has the advantages of large power density, small volume, high efficiency, simple structure, large torque at low speed, stable operation performance, and high control accuracy. The housing of the starting motor is made of aluminum alloy material. Compared with the DC brushed motor, the weight is reduced by 26.8%, the diameter is reduced by 21.4%, and the length is reduced by 58.3%. The starting motor 2 is fixedly connected to the motor bracket 5 by screws.
[0038] The motor bracket 5 is designed as a thin and light structure and is integrally formed by casting aluminum alloy. The weight is reduced by 46% compared with the traditional bracket. The motor bracket 5 is designed with three support legs and is connected to the air intake casing 15 by screws.
[0039] When using the turbojet engine starting motor device of the present utility model, the total weight of the turbojet engine is reduced, the thrust-to-weight ratio of the turbojet engine is increased, and the performance of the turbojet engine is improved. Moreover, since the starting motor is located at the air intake position, the DC brushless outer rotor motor of the present utility model is small in volume and light in weight, which improves the air intake efficiency of the turbojet engine.
[0040] The structure of the first embodiment of the overrunning clutch of the turbojet engine starting motor device of the present utility model is as follows:
[0041] Combined Figure 1 、 Figure 2 、 Figure 5 、 Figure 6 、 Figure 7 、 Figure 8 、and Figure 9 As shown together, the overrunning clutch includes a bushing 4, an outer sleeve 7, and a cylindrical pin 11. The outer sleeve 7 is sleeved on the outer surface of the bushing 4, and the outer sleeve 7 and the bushing 4 are preferably in clearance fit. The bushing 4 is sleeved on the outer surface of the starting motor shaft 21. A set screw 6 is provided on the bushing 4, and the set screw 6 abuts against the outer surface of the starting motor shaft 21.
[0042] Preferably, a groove is provided on the outer surface of the starting motor shaft 21, the bottom of the groove is a flat structure, and the set screw 6 abuts against the bottom of the groove.
[0043] The cylindrical pin 11 is connected to the bushing 4. The cylindrical pin 11 is preferably connected to the bushing 4 by an interference fit, and both ends of the cylindrical pin 11 protrude from the bushing 4. Two helical grooves are provided on the outer sleeve 7 in the circumferential direction, and both ends of the cylindrical pin 11 are respectively inserted into the corresponding helical grooves.
[0044] Preferably, the two ends of the cylindrical pin 11 are respectively defined as a first end 111 and a second end 112, and the two spiral grooves are respectively defined as a first spiral groove 71 and a second spiral groove 72. When in use, the first end 111 of the cylindrical pin 11 is inserted into the first spiral groove 71, and the first end 111 of the cylindrical pin 11 can slide freely in the first spiral groove 71; the second end 112 of the cylindrical pin 11 is inserted into the second spiral groove 72, and the second end 112 of the cylindrical pin 11 can slide freely in the second spiral groove 72.
[0045] Preferably, a horizontal section A 711 is provided at one end of the first spiral groove 71 close to the front shaft nut 9, and a horizontal section B 721 is provided at one end of the second spiral groove 72 close to the front shaft nut 9.
[0046] Preferably, a sealing ring 8 is provided at one end of the outer sleeve 7 facing the front shaft nut 9. The sealing ring 8 is preferably an O-ring.
[0047] Further preferably, the outer sleeve 7 is provided with an outer sleeve arc groove, and the sealing ring 8 is located in the outer sleeve arc groove, which can effectively prevent the sealing ring 8 from falling off.
[0048] Preferably, the front shaft nut 9 is provided with a nut arc groove 91. When the outer sleeve 7 contacts the front shaft nut 9 to transmit torque, the sealing ring 8 is simultaneously located in the outer sleeve arc groove and the nut arc groove 91, which can increase the friction force and torque transmission efficiency and prevent slipping. The front shaft nut 9 drives the engine rotating shaft 16 to rotate, so that the turbojet engine obtains an initial starting speed.
[0049] Preferably, a thrust bearing 3 is provided between the end faces of the bushing 4 and the starting motor 2. When the outer sleeve 7 contacts the front shaft nut 9 to transmit torque, the starting motor 2 will bear a large axial force, and the thrust bearing 3 bears this axial force, improving the service life of the starting motor 2.
[0050] The working process of the turbojet engine starting motor device of the present invention is described in detail as follows:
[0051] When the starting motor 2 is not working, the first end 111 of the cylindrical pin 11 is located in the horizontal section A 711, and the second end 112 of the cylindrical pin 11 is located in the horizontal section B 721. When the starting motor 2 starts to work, the starting motor shaft 21 rotates and drives the bushing 4 to rotate at the same time. When the starting motor shaft 21 of the starting motor 2 reaches a certain rotational speed, under the action of centrifugal force, the outer sleeve 7 can move axially out of this position. It moves until it contacts the front shaft nut 9, and the outer sleeve 7 contacts the front shaft nut 9 to transmit torque, and the front shaft nut 9 drives the engine rotating shaft 16 to rotate, so that the turbofan engine obtains an initial starting speed. When the starting motor 2 stops working, the outer sleeve 7 moves axially in the reverse direction. The first end 111 of the cylindrical pin 11 is located in the horizontal section A 711, and the second end 112 of the cylindrical pin 11 is located in the horizontal section B 721, and the outer sleeve 7 stops moving axially. After the turbofan engine ignites successfully, it can effectively prevent the outer sleeve 7 from falling off due to vibration or gravity and contacting the front shaft nut 9, and then the starting motor 2 is driven by the high-speed engine rotating shaft 16 to rotate, forming a reverse potential difference, resulting in the problem of burning out of the starting motor 2, and can effectively ensure the safety and reliability of the starting motor 2.
[0052] The structure of the overrunning clutch in the second embodiment of the starting motor device of the turbofan engine of the present invention is as follows:
[0053] Combined Figure 1 、 Figure 2 、and Figure 10 As commonly shown, a housing 14 is fixedly arranged on the outer surface of the outer sleeve 7, and a sealing ring 8 is arranged at the end of the housing 14 facing the front shaft nut 9.
[0054] An arc-shaped groove of the housing is arranged at the end of the housing 14, and the sealing ring 8 is arranged in the arc-shaped groove of the housing, which can effectively prevent the sealing ring 8 from falling off. When the housing 14 contacts the front shaft nut 9 to transmit torque, the sealing ring 8 is simultaneously located in the arc-shaped groove of the housing and the arc-shaped groove 91 of the front shaft nut.
[0055] The remaining structure is the same as that of the overrunning clutch in the first embodiment, and will not be described in detail here.
[0056] The structure of the overrunning clutch in the third embodiment of the starting motor device of the turbofan engine of the present invention is as follows:
[0057] Combined Figure 1 、 Figure 2 、 Figure 11 、and Figure 12 As commonly shown, the overrunning clutch includes a bushing 4, an outer sleeve 7, and a cylindrical pin 11. The outer sleeve 7 is sleeved on the outer surface of the bushing 4, and the outer sleeve 7 and the bushing 4 are preferably in clearance fit. The bushing 4 is sleeved on the outer surface of the starting motor shaft 21, and a set screw 6 is arranged on the bushing 4, and the set screw 6 abuts against the outer surface of the starting motor shaft 21.
[0058] Preferably, a groove is provided on the outer surface of the starting motor shaft 21, and the bottom of the groove has a flat structure, and the set screw 6 abuts against the bottom of the groove.
[0059] The cylindrical pin 11 is connected to the bushing 4. Preferably, the cylindrical pin 11 is connected to the bushing 4 by an interference fit, and both ends of the cylindrical pin 11 protrude from the bushing 4. The outer sleeve 7 is provided with two spiral grooves in the circumferential direction, and both ends of the cylindrical pin 11 are respectively inserted into the corresponding spiral grooves.
[0060] Preferably, both ends of the cylindrical pin 11 are respectively defined as a first end 111 and a second end 112, and the two spiral grooves are respectively defined as a first spiral groove 71 and a second spiral groove 72. In use, the first end 111 of the cylindrical pin 11 is inserted into the first spiral groove 71, and the first end 111 of the cylindrical pin 11 can freely slide in the first spiral groove 71; the second end 112 of the cylindrical pin 11 is inserted into the second spiral groove 72, and the second end 112 of the cylindrical pin 11 can freely slide in the second spiral groove 72.
[0061] Preferably, a sealing ring 8 is provided at one end of the outer sleeve 7 facing the front shaft nut 9. The sealing ring 8 is preferably an O-ring.
[0062] Further preferably, the outer sleeve 7 is provided with an outer sleeve arc groove, and the sealing ring 8 is located in the outer sleeve arc groove, which can effectively prevent the sealing ring 8 from falling off.
[0063] Preferably, the front shaft nut 9 is provided with a nut arc groove 91. When the outer sleeve 7 contacts the front shaft nut 9 to transmit torque, the sealing ring 8 is simultaneously located in the outer sleeve arc groove and the nut arc groove 91, which can increase the friction force and the torque transmission efficiency and prevent slipping. The front shaft nut 9 drives the engine rotating shaft 16 to rotate, so that the turbofan engine obtains an initial starting speed.
[0064] Preferably, a thrust bearing 3 is provided between the end faces of the bushing 4 and the starting motor 2. When the outer sleeve 7 contacts the front shaft nut 9 to transmit torque, the starting motor 2 will bear a large axial force, and the thrust bearing 3 bears this axial force, which improves the service life of the starting motor 2.
[0065] Preferably, a magnet 13 is provided on the bushing 4 at one end facing the starting motor 2.
[0066] Preferably, a boss 41 is provided on the outer surface of the bushing 4, and the magnet 13 and the set screw 6 are both provided on the boss 41.
[0067] Further preferably, the boss 41 and the bushing 4 are of an integral structure.
[0068] The working process of the turbofan engine starting motor device of the present invention is described in detail as follows:
[0069] During use, one end of the first spiral groove 71 close to the front shaft nut 9 is defined as the A end of the first spiral groove, and the other end is defined as the B end of the first spiral groove; one end of the second spiral groove 72 close to the front shaft nut 9 is defined as the A end of the second spiral groove, and the other end is defined as the B end of the second spiral groove.
[0070] When the starting motor 2 is not working, under the action of the magnet 13, the first end 111 of the cylindrical pin 11 is located at the A end of the first spiral groove, and the second end 112 of the cylindrical pin 11 is located at the A end of the second spiral groove. When the starting motor 2 starts to work, the starting motor shaft 21 rotates and drives the bushing 4 to rotate at the same time. When the starting motor shaft 21 of the starting motor 2 reaches a certain speed, under the action of centrifugal force, the outer sleeve 7 can move axially away from this position. It moves until it contacts the front shaft nut 9. The outer sleeve 7 contacts the front shaft nut 9 to transmit torque, and the front shaft nut 9 drives the engine rotating shaft 16 to rotate, so that the turbojet engine obtains an initial starting speed. When the starting motor 2 stops working, the outer sleeve 7 moves axially in the reverse direction. Under the action of the magnet 13, the first end 111 of the cylindrical pin 11 is located at the A end of the first spiral groove, and the second end 112 of the cylindrical pin 11 is located at the A end of the second spiral groove, and the outer sleeve 7 stops moving axially. After the turbojet engine ignites successfully, it can effectively prevent the outer sleeve 7 from falling off due to vibration or gravity and contacting the front shaft nut 9, and then the starting motor 2 is driven by the high-speed engine rotating shaft 16 to rotate, forming a reverse potential difference, resulting in the problem of burning out the starting motor 2, and can effectively ensure the safety and reliability of the starting motor 2.
[0071] The structure of the overrunning clutch in the fourth embodiment of the starting motor device of the turbojet engine of the present invention is as follows:
[0072] Combined with Figure 1 、 Figure 2 、 Figure 13 、and Figure 14 As commonly shown, a housing 14 is fixedly arranged on the outer surface of the outer sleeve 7, and the sealing ring 8 is arranged at the end of the housing 14 facing the front shaft nut 9.
[0073] An arc-shaped groove of the housing is arranged at the end of the housing 14, and the sealing ring 8 is arranged in the arc-shaped groove of the housing, which can effectively prevent the sealing ring 8 from falling off. When the housing 14 contacts the front shaft nut 9 to transmit torque, the sealing ring 8 is simultaneously located in the arc-shaped groove of the housing and the arc-shaped groove 91 of the front shaft nut.
[0074] The remaining structure is the same as that of the overrunning clutch in the third embodiment, and will not be described in detail here.
[0075] The technical features named with serial numbers involved in this specification (such as spiral groove 1, spiral groove 2, horizontal section A, horizontal section B, first end, second end, A end of spiral groove 1, B end of spiral groove 1, A end of spiral groove 2, B end of spiral groove 2, etc.) are only used to distinguish each technical feature, and do not represent the positional relationship, installation order, working order, etc. between the technical features.
[0076] In the description of this specification, it should be understood that the orientation or positional relationship described by "outer sleeve", "horizontal section A", "horizontal section B", "outer shell", "outer surface", etc. is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation to the present utility model.
[0077] Although the specific embodiments of the present utility model have been described above, those skilled in the art should understand that the described embodiments are only a part of the embodiments of the present utility model, rather than all the embodiments. These are only examples. The protection scope of the present utility model is defined by the appended claims. Without departing from the principle and essence of the present utility model, those skilled in the art can make various changes or modifications to these embodiments without any creative labor, but these changes and modifications all fall within the protection scope of the present utility model.
Claims
1. A starting motor device for a turbojet engine. The turbojet engine using the starting motor device for the turbojet engine includes an air intake casing and an engine rotating shaft. At one end of the engine rotating shaft close to the air intake casing, a front shaft nut and a compressor impeller are fixedly arranged. At the other end of the engine rotating shaft, a turbine is fixedly arranged. It is characterized in that the starting motor device for the turbojet engine includes a starting motor and an overrunning clutch. The starting motor has a starting motor shaft. The overrunning clutch includes a bushing, an outer sleeve, and a cylindrical pin. The outer sleeve is sleeved on the outer surface of the bushing. The bushing is sleeved on the outer surface of the starting motor shaft. A set screw is arranged on the bushing, and the set screw abuts against the outer surface of the starting motor shaft. The cylindrical pin is connected to the bushing, and both ends of the cylindrical pin protrude from the bushing. Two spiral grooves are arranged on the outer sleeve in the circumferential direction, and both ends of the cylindrical pin are respectively inserted into the corresponding spiral grooves.
2. The turbojet engine starting motor device according to claim 1, characterized in that, One end of the outer sleeve facing the front shaft nut is provided with a sealing ring.
3. The turbojet engine starting motor device according to claim 2, characterized in that The outer sleeve is provided with an outer sleeve arc groove, and the sealing ring is located in the outer sleeve arc groove.
4. The turbojet engine starting motor device according to claim 3, characterized in that, The front shaft nut is provided with a nut arc groove; when the outer sleeve contacts the front shaft nut to transmit torque, the sealing ring is simultaneously located in the outer sleeve arc groove and the nut arc groove.
5. The starting motor device of a turbojet engine according to claim 2, characterized in that, The outer surface of the outer sleeve is fixedly provided with a housing, and the sealing ring is arranged at the end of the housing facing the front shaft nut.
6. The turbojet engine starting motor device according to claim 1, characterized in that, The two spiral grooves are respectively defined as spiral groove one and spiral groove two. A horizontal section A is arranged at one end of spiral groove one close to the front shaft nut, and a horizontal section B is arranged at one end of spiral groove two close to the front shaft nut.
7. The turbojet engine starting motor device according to claim 1, characterized in that, Close to the end facing the starting motor, a magnet is arranged on the bushing.
8. The turbojet engine starting motor device according to claim 7, characterized in that, A boss is arranged on the outer surface of the bushing, and the magnet and the set screw are both arranged on the boss.
9. The turbojet engine starting motor device according to claim 1, characterized in that, Two magnetic steels are arranged on the front shaft nut, and a Hall sensor is arranged in the air intake casing.
10. The turbojet engine starting motor device according to claim 1, characterized in that, A groove is arranged on the outer surface of the starting motor shaft, and the bottom of the groove is a plane structure, and the set screw abuts against the bottom of the groove.