Starting and launching integrated device of aero-engine

Abstract

The utility model relates to an aero-engine starting and starting integrated device, which belongs to the technical field of equipment simulation and consists of a fixed bottom plate, and a torque coupling, a high-speed gear box and a high-speed permanent magnet motor which are arranged on the fixed bottom plate and are connected in sequence, the torque coupling and the aero-engine power output shaft, the high-speed gear box high-speed shaft and the torque coupling, and the high-speed gear box low-speed shaft and the high-speed permanent magnet motor are in adaptive stable connection through flanges respectively, and the torque coupling and the aero-engine power output shaft are stably supported by a supporting seat arranged on the table top of the fixed bottom plate. Torque transmission among the aero-engine power divider shaft, the torque coupler, the high-speed gear box and the high-speed permanent magnet motor is achieved, a torque sensor communication interface is connected with a lower computer, a motor communication interface is connected with the lower computer, and the problems that in the prior art, aero-engine power extraction based on a flying attachment casing is poor in universality and short in service life are solved.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of equipment simulation, especially relates to an aero-engine starting and launching integrated device. BACKGROUND

[0002] When the aero-engine is tested on the ground, the air turbine starter or the gas turbine starter on the fly-attached casing is usually used to start the aero-engine, and after the aero-engine is successfully started, the power is extracted through the direct-current or alternating-current generator and the hydraulic pump on the fly-attached casing.

[0003] Since the fly-attached casing is generally a special accessory for the aero-engine, it needs to be adapted to different air turbine starters, gas turbine starters, alternating-current generators, direct-current generators and hydraulic pumps, which not only has high cost but also lacks universality; on the other hand, the existing power extraction mode based on the fly-attached casing is complex, and the service life of the fly-attached casing is generally limited, which is difficult to meet the long-time testing requirements of the aero-engine. SUMMARY

[0004] In view of the above analysis, the utility model aims to provide an aero-engine starting and launching integrated device to solve the problems of poor universality and short service life of the existing fly-attached casing for extracting the power of the aero-engine.

[0005] The utility model mainly aims to realize the following technical scheme:

[0006] An aero-engine starting and launching integrated device, the aero-engine comprising a power output shaft and a torque coupling, a high-speed gear box and a high-speed permanent magnet motor connected in sequence and arranged on the fixed bottom plate;

[0007] The torque coupling is connected to the power output shaft through a flange;

[0008] The high-speed gear box comprises a high-speed shaft and a low-speed shaft, and the high-speed shaft is connected to the torque coupling through a flange;

[0009] The high-speed permanent magnet motor comprises a motor rotor, and the motor rotor is connected to the low-speed shaft through a flange.

[0010] Based on the further improvement of the above scheme, the device further comprises a support seat, the support seat comprising a support base and a first ring with a fixing groove arranged on the upper surface of the support base; the support base is fixedly arranged on the fixed bottom plate; and the flange plate connected to the flange of the power output shaft is fixedly arranged in the first ring.

[0011] Based on the further improvement of the above scheme, the torque coupling further comprises a torque sensor, wherein,

[0012] The torque sensor comprises a first flange plate, a second flange plate, a flange shaft, a transmission shaft,

[0013] The first flange plate and the second flange plate are arranged at two ends of the flange shaft respectively.

[0014] The transmission shaft is arranged in the shaft hole of the flange shaft, the output end of the transmission shaft is outwardly extended from the end face of the first flange plate, and the input end of the transmission shaft is outwardly extended from the end face of the second flange plate.

[0015] The second flange plate is connected with the high-speed shaft through a flange.

[0016] Based on the further improvement of the above scheme, the torque coupling further comprises a base, wherein,

[0017] The end face of the first flange plate of the torque sensor is connected with the end face of the flange.

[0018] The base comprises a base seat and a second ring with a fixing groove arranged on the base seat, the second flange plate is fixedly arranged in the second ring, and the base seat is fixedly arranged on the upper surface of the support base.

[0019] Based on the further improvement of the above scheme, the torque coupling further comprises a connecting shaft arranged in the shaft center of the flange connecting the second flange plate and the high-speed shaft, the high-speed shaft is further provided with a shaft hole, one end of the connecting shaft is connected with the input end of the transmission shaft, and the other end of the connecting shaft is inserted into the shaft hole of the high-speed shaft.

[0020] Based on the further improvement of the above scheme, the base seat of the torque coupling is further provided with a torque sensor power supply port and a torque sensor communication interface, the torque sensor power supply port is connected with an external power supply, and the torque sensor communication interface is connected with a lower computer.

[0021] Based on the further improvement of the above scheme, the high-speed gear box further comprises a box body, a box cover, and a high-ratio gear set, wherein,

[0022] The box body is provided with a box base at the bottom, and the box base is fixedly connected with the fixed bottom plate.

[0023] The high-ratio gear set is arranged in the inner cavity of the box body.

[0024] The box body is open at one side.

[0025] The high-speed shaft is connected with the high-ratio gear set by being inserted into the box body through the opening arranged on the upper part of the opposite side of the opening side of the box body.

[0026] The box cover covers the opening of the box body, the box cover is provided with an opening at the lower part, and the low-speed shaft is connected with the high-ratio gear set by being inserted into the box body through the opening of the box cover.

[0027] A further improvement based on the above scheme is characterized in that an oil injection hole is provided on the upper part of the left upright side of the box opening, and an oil outlet hole is provided on the lower part.

[0028] A smoke exhaust pipe is installed on the right vertical side of the box opening.

[0029] Based on the further improvement of the above scheme, the high-speed permanent magnet motor also includes a speed sensor and a motor communication interface. The speed sensor is set on the motor rotor and is connected to the lower-level machine through the motor communication interface.

[0030] Based on the further improvement of the above scheme, the high-speed permanent magnet motor is also equipped with a motor power transmission interface;

[0031] When the device is in startup mode, the motor power transmission interface is connected to the power distribution cabinet;

[0032] When the device is in load mode, the motor power transmission interface is connected to the resistor box.

[0033] Compared with the prior art, the present invention can achieve at least one of the following beneficial effects:

[0034] 1. An integrated aero-engine starter unit consisting of a torque sensor, a high-speed gearbox, and a high-speed permanent magnet motor connected in sequence. The torque sensor is connected to the aero-engine power output shaft via a flange and is capable of collecting the torque generated when the aero-engine rotates. The collected torque is transmitted to the host computer via a communication interface. The torque sensor is connected to the high-speed shaft of the high-speed gearbox via a flange, and the low-speed shaft of the high-speed gearbox is connected to the rotor of the high-speed permanent magnet motor via a flange. The rotor of the high-speed permanent magnet motor is also equipped with a speed sensor. Through the rigid connection of the aero-engine power output shaft, torque sensor, high-speed gearbox, and high-speed permanent magnet motor, the aero-engine can be started by the high-speed permanent magnet motor in start-up mode. After the aero-engine enters autonomous rotation, the high-speed permanent magnet motor can switch to load mode and rotate with the aero-engine to achieve the purpose of extracting the speed of the high-speed permanent magnet motor and extracting the power of the aero-engine.

[0035] 2. High-speed permanent magnet motors, high-speed gearboxes, and torque couplings are all common and highly durable. By using customized flanges to adapt the torque couplings to the interfaces of aero engines, not only are the requirements for connection rigidity and durability met, but implementation is also easy and can meet the long-term testing needs of aero engines.

[0036] The above technical solutions can be combined with each other to realize more optional combination solutions. Other features and advantages of the present application will be described in the following content, and some advantages can be apparent from the description or can be understood by implementing the present application. The purposes and other advantages of the present application can be realized and obtained through the content specifically indicated in the description and the drawings. BRIEF DESCRIPTION OF DRAWINGS

[0037] The drawings are only for the purpose of illustrating specific embodiments and are not considered as limiting the present application, and the same reference signs represent the same components throughout the drawings.

[0038] Figure 1 It is a schematic view of the overall structure of the embodiment of the present application.

[0039] Figure 2 It is a schematic view of the torque sensor connection structure of the embodiment of the present application.

[0040] Figure 3 It is a schematic view of the torque coupling support structure of the embodiment of the present application.

[0041] Figure 4 It is a schematic view of the high-speed gear box structure of the embodiment of the present application.

[0042] Figure 5 It is a schematic view of the high-speed gear box and high-speed permanent magnet motor connection structure of the embodiment of the present application.

[0043] REFERENCE SIGNS:

[0044] Q1: an aero-engine;

[0045] Q1-1: a power take-off shaft;

[0046] Q2: a torque coupling;

[0047] Q2-1: a flange connecting the torque sensor and the power take-off shaft;

[0048] Q2-2: a flange torque sensor;

[0049] Q2-2a: a torque sensor first flange; Q2-2b: a torque sensor second flange; Q2-2c: a torque sensor flange shaft; Q2-2d: a torque sensor transmission shaft;

[0050] Q2-3: a flange connecting the torque sensor and the high-speed gear box;

[0051] Q2-4: a base;

[0052] Q2-4a: Base plate; Q2-4b: Second ring; Q2-4c: Torque sensor communication interface; Q2-4d: Torque sensor power supply port;

[0053] Q2-5: Output end of drive shaft;

[0054] Q2-6: Input end of drive shaft;

[0055] Q3: Support base;

[0056] Q3-1: Support base; Q3-2: First ring;

[0057] Q4: High-speed gearbox;

[0058] Q4-1: Box body;

[0059] Q4-1a: Box base;

[0060] Q4-2: High-speed shaft;

[0061] Q4-3: Box lid;

[0062] Q4-4: Low-speed shaft;

[0063] Q4-5: Oil injection hole;

[0064] Q4-6: Oil outlet hole;

[0065] Q5: High-speed permanent magnet motor;

[0066] Q5-1: Motor rotor; Q5-2: Speed ​​sensor; Q5-3: Power transmission interface;

[0067] Q6: Fix the base plate. Detailed Implementation

[0068] The preferred embodiments of the present invention will now be described in detail with reference to the accompanying drawings, which constitute a part of this application and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not intended to limit the scope of the present invention.

[0069] A specific embodiment of this utility model discloses an integrated starter-generator device for an aircraft engine, such as... Figure 1 As shown.

[0070] The aero-engine Q1 includes a power output shaft, and the device includes a fixed base plate Q6, and a torque coupling Q2, a high-speed gearbox Q4, and a high-speed permanent magnet motor Q5, which are disposed on the fixed base plate Q6 and connected in sequence.

[0071] The torque coupling Q2 is connected to the power output shaft Q1-1 via a flange;

[0072] The high-speed gearbox Q4 includes a high-speed shaft Q4-2 and a low-speed shaft Q4-5, the high-speed shaft Q4-2 is connected with the torque coupling Q2 through a flange;

[0073] The high-speed permanent magnet motor Q5 includes a motor rotor Q5-1, the motor rotor Q5-1 is connected with the low-speed shaft Q4-5 through a flange.

[0074] The device for extracting power of an aero-engine during ground bench test needs to support driving the aero-engine to start, and rotate and extract power after the aero-engine starts.

[0075] In the embodiment, the torque sensor Q2-2, the high-speed gearbox Q4 and the high-speed permanent magnet motor Q5 are fixedly arranged on the fixed base plate Q6 and connected in sequence to establish a rigid connection, and the whole connection structure of the torque sensor Q2-2 and the aero-engine power output shaft Q1-1 is connected.

[0076] As shown in Figure 2 , Figure 3 Further, the torque coupling Q2 further includes a torque sensor Q2-2, wherein,

[0077] The torque sensor Q2-2 includes a first flange plate Q2-2a, a second flange plate Q2-2b, a flange shaft Q2-2c and a transmission shaft Q2-2d,

[0078] The first flange plate Q2-2a and the second flange plate Q2-2b are respectively arranged at two ends of the flange shaft Q2-2c;

[0079] The transmission shaft Q2-2d is arranged at the center of the flange shaft Q2-2c, an output end of the transmission shaft Q2-2d is outwardly extended from an end surface of the first flange plate Q2-2a, and an input end of the transmission shaft Q2-2d is outwardly extended from an end surface of the second flange plate Q2-2b;

[0080] The second flange plate Q2-2b is connected with the high-speed shaft Q4-2 through a flange.

[0081] In order to meet the requirements of the structural stability and durability of the mechanical structure for power output in the test, the flange type electromagnetic torque sensor is adopted in the embodiment, which specifically comprises a flange shaft and first and second flange plates Q2-2a and Q2-2b arranged at both ends of the flange shaft, a transmission shaft arranged in the shaft hole of the flange shaft Q2-2c, and a permanent magnet disc arranged on the back of the end surface of the second flange plate Q2-2b. The first flange plate Q2-2a is connected to the power take-off shaft Q1-1 of the aero-engine through the flange Q2-1, and the second flange plate Q2-2b is connected to the high-speed gearbox Q4 through the flange. The first flange plate Q2-2a is connected to the flange Q2-1 through bolts, and the first flange plate Q2-2a and the connected flange Q2-1, and the second flange plate Q2-2b and the connected flange Q2-3 are fixed by the clamp, thereby further improving the stability of the connection between the first flange plate Q2-2a and the flange Q2-1, and the second flange plate Q2-2b and the flange Q2-3.

[0082] Generally, the power take-off shaft of the aero-engine is provided with a flange plate, the center of the power take-off shaft flange plate is provided with a rotating shaft, and the high-speed shaft of the high-speed gearbox is also provided with a flange plate. Therefore, the non-standard flange is made to adapt to the connection between the power take-off shaft flange plate end surface and the torque sensor first flange plate end surface, and the torque sensor second flange plate end surface and the high-speed gearbox high-speed shaft flange plate end surface, which helps to improve the universality of the device of the embodiment. The rotating shaft of the power take-off shaft of the aero-engine is located at the center of the power take-off shaft flange plate of the aero-engine.

[0083] Further, the device further comprises a support seat Q3, which comprises a support base Q3-1 and a first ring Q3-2 provided on the upper surface of the support base Q3-1 and having a fixing groove; the support base Q3-1 is fixedly arranged on the fixed base plate Q6; the flange plate of the flange Q2-1 connected to the power take-off shaft is fixedly arranged in the first ring Q3-2.

[0084] Further, the torque coupling Q2 further comprises a base Q2-4, wherein,

[0085] The end surface of the torque sensor first flange plate Q2-2a is connected to the end surface of the flange Q2-1.

[0086] The base Q2-4 comprises a base base Q2-4a and a second ring Q2-4b provided on the base and having a fixing groove, the second flange plate Q2-2b is fixedly arranged in the second ring Q2-4b, and the base base Q2-4a is fixedly arranged on the upper surface of the support base Q3-1.

[0087] The high-speed gear box Q4 and the high-speed permanent magnet motor Q5 are large in size, the aero-engine power take-off shaft Q1-1 has a certain length, and the torque sensor Q2-2 is relatively short in size. In order to ensure the safety and reliability during the test process, the stability of the aero-engine power take-off shaft Q1-1 and the torque sensor Q2-2 shaft concentric connection needs to be ensured.

[0088] A support base Q3-1 is arranged at the position where the fixed platform table surface is connected with the torque coupling Q2 of the aero-engine power take-off shaft Q1-1. The torque coupling base Q2-4 includes a base base Q2-4a and a second ring Q2-4b provided on the base and having a fixed groove. The height of the support base Q3-1 is consistent with the height of the bottom of the torque coupling base Q2-4. The torque coupling base Q2-4a and the upper surface of the support base Q3-1 are fixedly connected. The torque sensor second flange plate Q2-2b is fixedly arranged in the second ring Q2-4b. A first ring Q3-2 is further arranged on the upper surface of the support base Q3-1 at the position corresponding to the aero-engine power take-off shaft Q1-1 and the torque coupling Q2 connecting flange Q2-1. The first ring Q3-2 is fixedly arranged on the upper surface of the support base Q3-1 through a base. The flange plate Q2-1 connected with the aero-engine power take-off shaft is fixedly arranged in the first ring Q3-2. Based on the support of the first ring Q3-2 fixedly arranged with the flange Q2-1 to the aero-engine power take-off shaft Q1-1, the support of the second ring Q2-4b fixedly arranged with the torque sensor second flange plate Q2-2b to the torque sensor Q2-2, and the overall support structure of the first ring Q3-2, the second ring Q2-4b arranged on the upper surface of the support base Q3-1, and the support base Q3-1 arranged on the fixed base plate Q6 table, the structural stability of the aero-engine power take-off shaft and the torque coupling is ensured.

[0089] The torque sensor first flange plate Q2-2a, the second flange plate Q2-2b and the flange shaft Q2-2c are fixedly arranged. The torque is transmitted by the transmission shaft arranged at the center of the flange shaft Q2-2c. The output end of the transmission shaft is outwardly extended from the end surface of the first flange plate Q2-2a. The aero-engine power take-off shaft Q1-1 is connected with the transmission shaft of the torque sensor. The output end of the transmission shaft is outwardly extended from the end surface of the second flange plate Q2-2b. The high-speed shaft Q4-2 of the high-speed gear box is connected. During the aero-engine test, the torque sensor transmission shaft Q2-2d is driven by the aero-engine power take-off shaft Q1-1, and the high-speed shaft Q4-2 of the high-speed gear box is further driven to rotate.

[0090] Further, the torque coupling Q2 further comprises a connecting shaft arranged in the shaft center connecting the second flange plate Q2-2b and the flange of the high-speed shaft Q4-2; the high-speed shaft Q4-2 is further provided with a shaft hole; one end of the connecting shaft is connected to the transmission shaft input end Q2-6, and the other end extends into the shaft hole of the high-speed shaft Q4-2.

[0091] The flange increases the connecting distance between the second flange plate Q2-2b of the torque sensor and the high-speed shaft Q4-2 of the high-speed gearbox, and a connecting shaft needs to be used to establish the connection between the transmission shaft input end Q2-6 and the high-speed shaft Q4-2 of the high-speed gearbox, wherein the high-speed shaft Q4-2 of the high-speed gearbox is further provided with a shaft hole, and the cross-sectional shape of one end of the connecting shaft connecting the high-speed shaft of the high-speed gearbox is adapted to the cross-sectional shape of the shaft hole of the high-speed shaft of the high-speed gearbox.

[0092] Further, the torque coupling base further comprises a torque sensor power supply port Q2-4d and a torque sensor communication interface Q2-4c, the torque sensor power supply port Q2-4d is connected to an external power supply, and the torque sensor communication interface Q2-4c is connected to a lower computer.

[0093] The torque collected by the torque sensor is transmitted to the lower computer through the torque sensor communication interface Q2-4c arranged in the torque coupling base Q2-4a. The torque coupling base is further provided with a torque sensor power supply port Q2-4d, preferably, the torque sensor is powered by UPS, and the UPS is connected to the torque sensor power supply port Q2-4d to supply power to the torque sensor.

[0094] As shown in Figure 4 Further, the high-speed gearbox Q4 further comprises a gearbox Q4-1, a cover Q4-3, and a high-ratio gear set, wherein,

[0095] The bottom of the gearbox Q4-1 is provided with a gearbox base Q4-1a, and the gearbox base Q4-1a is fixedly connected with the fixed bottom plate Q6;

[0096] The high-ratio gear set is arranged in the inner cavity of the gearbox Q4-1;

[0097] One side of the gearbox Q4-1 is open;

[0098] The high-speed shaft Q4-2 extends into the gearbox Q4-1 through the opening arranged on the opposite upper part of the open side of the gearbox Q4-1 to connect the high-ratio gear set;

[0099] The cover Q4-3 covers the opening of the gearbox Q4-1, the lower part of the cover Q4-3 is provided with an opening, and the low-speed shaft Q4-4 extends into the gearbox through the cover opening to connect the high-ratio gear set.

[0100] The high-speed gear box Q4 is used to transmit and increase the torque and adjust the rotating speed through the gear ratio. Since the rotating speed of the aero-engine is very high, the same rotating speed will cause the motor to malfunction. Therefore, the high-speed gear box is used to connect the high-speed shaft of the high-speed gear box to the high-speed shaft of the aero-engine, and the torque is transmitted to the low-speed shaft through the gear ratio setting. When the aero-engine is started, the low rotating speed of the motor can be output as a high rotating speed through the high-speed gear box.

[0101] The high-speed gear box Q4 is fixedly arranged on the fixed base plate Q6 through the base Q4-1a. The gear box body Q4-1 is open on one side, and the opening is directed to the high-speed permanent magnet motor Q5. The high gear ratio gear set is arranged in the inner cavity of the gear box body Q4-1. The cover Q4-3 covers the opening of the gear box body and seals the gear box body Q4-1. The opening of the gear box body is provided with an opening hole on the opposite side. The high-speed shaft Q4-2 is connected to the high gear ratio gear set through the opening hole of the gear box body. The cover Q4-1 is provided with an opening hole below. The low-speed shaft Q4-4 is connected to the high gear ratio gear set through the opening hole of the cover.

[0102] As shown in Figure 5 , further, the upper part of the left vertical side of the opening of the gear box body is provided with an oil injection hole Q4-5, and the lower part is provided with an oil outlet hole Q4-6.

[0103] The right vertical side of the opening of the gear box body is provided with a smoke exhaust pipe.

[0104] Since the gears in the high-speed gear box will also rotate at high speed when the aero-engine is tested, it is necessary to inject lubricating oil into the high-speed gear box to improve the operating efficiency of the gears in the high-speed gear box and reduce wear. The opening hole Q4-5 is arranged above the left vertical side of the opening of the gear box body, and the oil outlet hole Q4-6 is arranged below the left vertical side of the opening of the gear box body, which facilitates the injection of lubricating oil and the discharge of waste oil. The right vertical side of the opening of the gear box body is also provided with a smoke exhaust pipe, which is used to exhaust the oil smoke generated by the high-speed rotation of the gears in the high-speed gear box due to heating of the lubricating oil, and further helps to dissipate the heat of the high-speed gear box.

[0105] The low-speed shaft Q4-4 of the high-speed gear box is connected to the high-speed permanent magnet motor Q5 through a flange. Specifically, the low-speed shaft Q4-4 of the high-speed gear box is connected to the rotor Q5-1 of the high-speed permanent magnet motor through a non-standard flange, which satisfies the adaptation of the high-speed gear box Q4 and the high-speed permanent magnet motor Q5, and further improves the versatility of the device.

[0106] As shown in Figure 5 , further, the high-speed permanent magnet motor Q5 is also provided with a motor power transmission interface Q5-3.

[0107] When the device is in the starting mode, the motor power transmission interface Q5-3 is connected to the power distribution cabinet.

[0108] When the device is in load mode, the motor power supply interface Q5-3 is connected to the resistance box.

[0109] When the aircraft engine needs to be started, it is in the starting mode, and the motor power supply interface Q5-3 of the high-speed permanent magnet motor is connected to the power distribution cabinet, and the high-speed permanent magnet motor is powered and rotated by the power distribution cabinet to drive the aircraft engine to start rotating.

[0110] When the aircraft engine reaches self-rotation speed, it is switched to load mode, and the motor power supply interface Q5-3 of the high-speed permanent magnet motor is switched to connect the resistance box. The aircraft engine rotates to drive the high-speed permanent magnet motor to rotate and generate electric energy, which is consumed by the resistance box to avoid failure of the high-speed permanent magnet motor. Because in the load mode, the aircraft engine rotates to drive the high-speed permanent magnet motor to rotate and generate a large amount of electric energy, it is necessary to cool the resistance box to ensure stable operation of the load mode.

[0111] Further, the high-speed permanent magnet motor further comprises a speed sensor Q5-2 and a motor communication interface, the speed sensor Q5-2 is arranged on the motor rotor Q5-1, and the speed sensor Q5-2 is connected to the lower computer through the motor communication interface.

[0112] The speed sensor Q5-2 arranged on the high-speed permanent magnet motor is transmitted to the lower computer through the motor communication interface, which is convenient for extracting the parameters required by the aircraft engine power.

[0113] The high-speed permanent magnet motor has the characteristics of simple structure, flexible configuration, large output torque, economic durability, easy control, integrated starting and launching, and service life of more than 10,000 hours. Compared with the existing technology of starting the aircraft engine by gas turbine starter or air turbine starter, it has obvious advantages in extracting the power of the aircraft engine with the help of hydraulic oil circuit.

[0114] The aero-engine starting integrated device disclosed by the embodiment is composed of a fixed bottom plate Q6, a torque coupling Q2 arranged on the fixed bottom plate Q6, a high-speed gear box Q4, and a high-speed permanent magnet motor Q5 connected in sequence, wherein the torque coupling Q2 is respectively connected with the aero-engine power output shaft Q1-1, the high-speed gear box high-speed shaft Q4-2 and the torque coupling Q2, and the high-speed gear box low-speed shaft Q4-4 and the high-speed permanent magnet motor Q5 through non-standard flanges, the torque coupling Q2 and the aero-engine power output shaft Q1-1 are supported and fixed through the support seat Q3 arranged on the table surface of the fixed bottom plate Q6, torque transmission is realized between the aero-engine power output shaft Q1-1, the torque coupling Q2, the high-speed gear box Q4 and the high-speed permanent magnet motor Q5, and the lower computer is connected through the torque sensor communication interface Q2-4c and the motor communication interface, so that the aero-engine test parameters and power extraction are facilitated, and compared with the prior art, the problem of poor universality and short service life of the existing aero-engine power extraction based on the aircraft nacelle is solved.

[0115] Those skilled in the art can understand that the programs / software involved in the above embodiments are common methods in the prior art, and the present application does not involve any improvement in software. The present application only needs to connect various devices with corresponding functions through the connection relationship given in the embodiments of the present application, and does not involve any improvement in program / software. As for the connection mode between various hardware devices with corresponding functions, it can be realized by using the prior art, and will not be described in detail here.

[0116] The above is only a preferred specific embodiment of the present application, but the protection scope of the present application is not limited to this. Any person skilled in the art can easily think of changes or replacements within the technical range disclosed by the present application, which should be covered within the protection scope of the present application.

Claims

1. An aircraft engine starting and launching device, said aircraft engine comprising a power take-off shaft, characterized in that, The device comprises a fixed base plate, and a torque coupling, a high-speed gear box and a high-speed permanent magnet motor which are sequentially connected on the fixed base plate; The torque coupling is connected with the power output shaft through a flange; The high-speed gear box comprises a high-speed shaft and a low-speed shaft, and the high-speed shaft is connected with the torque coupling through a flange; The high-speed permanent magnet motor comprises a motor rotor, and the motor rotor is connected with the low-speed shaft through a flange.

2. The starting and launching device of claim 1, wherein, The device further comprises a support seat, which comprises a support base and a first ring with a fixed groove arranged on the upper surface of the support base; the support base is fixedly arranged on the fixed base plate; and a flange plate connected with the flange of the power output shaft is fixedly arranged in the first ring.

3. The aircraft engine starting and launching device of claim 2, wherein, The torque coupling further comprises a torque sensor, wherein, The torque sensor comprises a first flange plate, a second flange plate, a flange shaft and a transmission shaft; The first flange plate and the second flange plate are respectively arranged at two ends of the flange shaft; The transmission shaft is arranged in the shaft hole of the flange shaft, and the output end of the transmission shaft protrudes outward from the end surface of the first flange plate, and the input end of the transmission shaft protrudes outward from the end surface of the second flange plate; The second flange plate is connected with the high-speed shaft through a flange.

4. The starting and launching device of claim 3, wherein The torque coupling further comprises a base, wherein, The first flange plate of the torque sensor is connected with the aero-engine power output shaft through a flange; The base comprises a base seat and a second ring with a fixed groove arranged on the base seat, and the second flange plate is fixedly arranged in the second ring, and the base seat is fixedly arranged on the upper surface of the support base.

5. The aircraft engine starting and launching device of claim 4, wherein The torque coupling further comprises a connecting shaft arranged in the shaft center of the flange connecting the second flange plate and the high-speed shaft; the high-speed shaft is further provided with a shaft hole; one end of the connecting shaft is connected with the input end of the transmission shaft, and the other end of the connecting shaft protrudes into the shaft hole of the high-speed shaft.

6. The aircraft engine starting and launching device of claim 5, wherein, The base seat of the torque coupling is further provided with a torque sensor power supply port and a torque sensor communication interface; the torque sensor power supply port is connected with an external power supply, and the torque sensor communication interface is connected with a lower computer.

7. The aircraft engine starting and launching device of claim 6, wherein, The high-speed gear box further comprises a box body, a box cover and a high-ratio gear set, wherein, The bottom of the box body is provided with a box base, and the box base and the fixed base plate are fixedly connected; The high-ratio gear set is arranged in the inner cavity of the box body; One side of the box body is open; The high-speed shaft protrudes into the box body through the opening arranged on the upper part of the opposite side of the box body to connect the high-ratio gear set; The box cover covers the opening of the box body, and the lower part of the box cover is provided with an opening, and the low-speed shaft protrudes into the box body through the opening of the box cover to connect the high-ratio gear set.

8. The aircraft engine starting and launching device of claim 7, wherein, An oil injection hole is arranged on the upper part of the left vertical side of the opening of the box body, and an oil outlet hole is arranged on the lower part of the opening of the box body; A smoke exhaust pipe is arranged on the right vertical side of the opening of the box body.

9. The aircraft engine starting and launching device of claim 8, wherein, The high-speed permanent magnet motor further comprises a speed sensor and a motor communication interface; the speed sensor is arranged on the motor rotor, and the speed sensor is connected with a lower computer through the motor communication interface.

10. The aircraft engine starting and launching device of claim 9, wherein, The high-speed permanent magnet motor is further provided with a motor power transmission interface; When the device is in the starting mode, the motor power transmission interface is connected with a power distribution cabinet. When the device is in the load mode, the motor power interface is connected to the resistance box.

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