CN113916537B - Simulation starting system and starting method for test bed of aircraft engine box - Google Patents
Simulation starting system and starting method for test bed of aircraft engine box Download PDFInfo
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- CN113916537B CN113916537B CN202111031367.6A CN202111031367A CN113916537B CN 113916537 B CN113916537 B CN 113916537B CN 202111031367 A CN202111031367 A CN 202111031367A CN 113916537 B CN113916537 B CN 113916537B
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- 238000004088 simulation Methods 0.000 title claims abstract description 28
- 238000000034 method Methods 0.000 title claims abstract description 15
- 230000005540 biological transmission Effects 0.000 claims abstract description 12
- 239000007858 starting material Substances 0.000 description 5
- 238000005299 abrasion Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000010687 lubricating oil Substances 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
- Testing Of Engines (AREA)
Abstract
The invention relates to a simulation starting system and a starting method for a test bed of an aircraft engine box, and belongs to the field of transmission. The device comprises a loading motor, a main dragging motor, a starting motor, a torque meter a, a torque meter b, a torque meter d, a main speed increasing gearbox, a central bevel gear box, a starting speed increasing gearbox and a clutch b; one end of the input end of the main speed increasing gear box is connected with a torque meter a, the other end of the input end of the main speed increasing gear box is connected with a clutch b, the torque meter a is connected with a loading motor, the clutch b is connected with a main dragging motor, the output end of the main speed increasing gear box is sequentially connected with the torque meter b, a central bevel gear box and an aircraft engine box, and a starting motor is sequentially connected with a starting speed increasing gear box, a torque meter d and the aircraft engine box. The invention realizes the simulated starting test function of the aircraft engine case, and simultaneously has the normal test function, the accessory calibration function and the inertia simulation function, the torque and the rotating speed signals in the whole process are all measured by a sensor or calculated by a transmission ratio, and the precision grade can reach more than 0.2 percent.
Description
Technical Field
The invention relates to a simulation starting system of an aircraft attached test bed, and belongs to the field of transmission.
Background
The aircraft accessory case and the engine accessory case (for short, the aircraft accessory case) are important transmission parts of the engine, and the functions of the aircraft accessory case and the engine accessory case are that the torque output by the ignition of a starter is provided for a high-voltage rotor through a central transmission rod to drive the engine to ignite, and the process is called a starting state; after ignition is successful, the high-voltage rotor returns the torque of the turbine rotor to the aircraft attachment casing through the central transmission rod to drive accessories arranged on the casing to work, and the process is called a working state.
The aircraft engine case is usually not provided with a starter or the starter is not ignited at the test bed, so that the working state of the aircraft engine case can only be simulated in the ground test stage, but the starting state cannot be simulated. On the one hand, in recent years, faults such as exceeding of the metal content of lubricating oil and exceeding of the vibration value caused by abrasion and scratch of a starting face gear are increased increasingly; on the other hand, the aircraft engine case cannot monitor the working parameters of the starting stage on the engine, and great trouble is caused to product improvement. The domestic flying test bed can only singly carry out working state examination, and the simulation starting system is not researched, so the scheme lays a foundation for realizing the simulation starting of the test bed.
Disclosure of Invention
Object of the Invention
The purpose of the invention is that: the simulation starting system of the test bed of the aircraft-attached machine box can realize the torque and rotation speed characteristic simulation of a starting state and the test of the aircraft-attached machine box in a normal working state.
The technical scheme of the invention is as follows: the simulation starting system of the aircraft engine box test bed is characterized by comprising a loading motor 1, a main dragging motor 2, a starting motor 3, a torque meter a4, a torque meter b5, a torque meter d7, a main speed increasing gear box 8, a central bevel gear box 9, a starting speed increasing gear box 10 and a clutch b13; one end of the input end of the main speed increasing gear box 8 is connected with a torque meter a4, the other end of the input end is connected with a clutch b13, the torque meter a4 is connected with a loading motor 1, the clutch b13 is connected with a main dragging motor 2, the output end of the main speed increasing gear box 8 is sequentially connected with a torque meter b5, a central bevel gear box 9 and an aircraft engine case 11, and a starting motor 3 is sequentially connected with a starting speed increasing gear box 10, a torque meter d7 and the aircraft engine case 11.
The start-up and speed-up gearbox 10 is connected to a torque meter c6 and a calibration motor 16.
The starting speed increasing gear box 10 is connected with the aircraft engine and accessory case 11 through a spline or a crowned tooth, and the starting speed increasing gear box 10 can be changed into a form with a clutch c14 or a form without the clutch c14 according to the structure of the aircraft engine and accessory case 11.
The clutch 12 is arranged in the main speed increasing gearbox 8, and the clutch 12 is connected with the torque meter a4 and the loading motor 1.
An inertial flywheel 15 is reserved on the main speed increasing gearbox 8, and the purpose is to realize the moment of inertia simulation when the motor 1 is not loaded.
The rated power of the starting motor 3 is calculated and selected according to the maximum power of the starting process of the aircraft engine case 11, and the starting motor 3 realizes the starting rotation speed control of the aircraft engine case 11 through the starting speed increasing gearbox 10.
The flyer case 11 is also provided with an analog load 17.
In the starting method of the simulation starting system of the test bed of the flywheel attachment casing, a starting motor 3 is used as a power source in a starting test stage, a starting speed increasing gear box 10 is driven and transmitted to a main speed increasing gear box 8 through a torque meter d7, the flywheel attachment casing 11 and a central bevel gear box 9, a main dragging motor 2 rotates along with a rotating speed signal fed back by the starting motor 3, an overrunning clutch 13 is in a disengaging state at the moment, torque characteristics of the starting process are compensated by a loading motor 1 according to a signal fed back by a torque meter b5, and in the starting test stage, not only the starting rotating speed but also the starting torque can be simulated, and at the moment, the working sequence of a transmission chain is as follows: starting motor 3, starting speed-increasing gear box 10, torque instrument d7, flywheel accessory case 11, central cone gear box 9, torque instrument b5, main speed-increasing gear box 8, torque instrument a4 and loading motor 1;
After the required release rotational speed of the flywheel attachment box is reached, the main dragging motor 2 is actively involved, the overrunning clutch 13 is combined, the clutch a12 in the main speed increasing gear box 8 is released, and the loading motor 1 stops running; if the clutch is arranged in the aircraft attachment casing 11, the clutch in the aircraft attachment casing 11 is disconnected at the moment, and the starting motor 3 slowly stops running; if there is no clutch in the aircraft engine case 11, the clutch c14 in the starting speed increasing gear box 10 is disengaged at this time, the starter motor 3 is also slowly stopped, and the working sequence of the transmission chain at this time is: main dragging motor 2, clutch b13, main speed increasing gear box 8, torque meter b5, bevel gear box 9, flywheel accessory case 11 and simulation load 17.
The invention has the beneficial effects that: the invention can realize the simulation start test and the normal operation test of the flywheel attachment casing, the torque and the rotating speed signals are read in real time through the sensor, the control precision can reach more than 0.2 percent, meanwhile, the main dragging motor, the starting motor and the loading motor realize the electric closed loading in a PID control mode, the impact of the engagement and the disengagement of the clutch is reduced to the greatest extent, and meanwhile, the efficiency calibration of the simulation accessories can be realized on the test bed.
The invention can be applied to the ground simulation test bed of the same type.
Drawings
FIG. 1 is a diagram of a simulated starting system of a test bed of an aircraft engine box according to the present invention;
detailed description of the preferred embodiments
The invention is further described below with reference to the accompanying drawings:
The simulation starting system of the aircraft engine box test bed is characterized by comprising a loading motor 1, a main dragging motor 2, a starting motor 3, a torque meter a4, a torque meter b5, a torque meter d7, a main speed increasing gear box 8, a central bevel gear box 9, a starting speed increasing gear box 10 and a clutch b13; one end of the input end of the main speed increasing gear box 8 is connected with a torque meter a4, the other end of the input end is connected with a clutch b13, the torque meter a4 is connected with a loading motor 1, the clutch b13 is connected with a main dragging motor 2, the output end of the main speed increasing gear box 8 is sequentially connected with a torque meter b5, a central bevel gear box 9 and an aircraft engine case 11, and a starting motor 3 is sequentially connected with a starting speed increasing gear box 10, a torque meter d7 and the aircraft engine case 11. The flyer case 11 is also provided with an analog load 17.
The start-up and speed-up gearbox 10 is connected to a torque meter c6 and a calibration motor 16. The operating efficiency of the analog load 17 can be calibrated.
The starting speed increasing gear box 10 is connected with the flywheel attachment casing 11 through a spline or a crowned tooth, and a torque meter d7 is arranged on the input coupler, so that a starting torque value can be read in real time.
The starting speed increasing gear box 10 can be changed into a form with a clutch c14 or a form without the clutch c14 according to the structure of the flywheel attachment casing 11, so as to realize the disconnection of the starting motor 3 after the normal starting of the flywheel attachment.
The clutch 12 is arranged in the main speed increasing gearbox 8, and the clutch 12 is connected with the torque meter a4 and the loading motor 1.
An inertial flywheel 15 is reserved on the main speed increasing gearbox 8, and the purpose is to realize the moment of inertia simulation when the motor 1 is not loaded.
The rated power of the starting motor 3 is calculated and selected according to the maximum power of the starting process of the aircraft engine case 11, and the starting motor 3 realizes the starting rotation speed control of the aircraft engine case 11 through the starting speed increasing gearbox 10.
In the starting method of the simulation starting system of the test bed of the flywheel attachment casing, a starting motor 3 is used as a power source in a starting test stage, a starting speed increasing gear box 10 is driven and transmitted to a main speed increasing gear box 8 through a torque meter d7, the flywheel attachment casing 11 and a central bevel gear box 9, a main dragging motor 2 rotates along with a rotating speed signal fed back by the starting motor 3, an overrunning clutch 13 is in a disengaging state at the moment, torque characteristics of the starting process are compensated by a loading motor 1 according to a signal fed back by a torque meter b5, and in the starting test stage, not only the starting rotating speed but also the starting torque can be simulated, and at the moment, the working sequence of a transmission chain is as follows: starting motor 3, starting speed-increasing gear box 10, torque instrument d7, flywheel accessory case 11, central cone gear box 9, torque instrument b5, main speed-increasing gear box 8, torque instrument a4 and loading motor 1;
After the required release rotational speed of the flywheel attachment box is reached, the main dragging motor 2 is actively involved, the overrunning clutch 13 is combined, the clutch a12 in the main speed increasing gear box 8 is released, and the loading motor 1 stops running; if the clutch is arranged in the aircraft attachment casing 11, the clutch in the aircraft attachment casing 11 is disconnected at the moment, and the starting motor 3 slowly stops running; if there is no clutch in the aircraft engine case 11, the clutch c14 in the starting speed increasing gear box 10 is disengaged at this time, the starter motor 3 is also slowly stopped, and the working sequence of the transmission chain at this time is: main dragging motor 2, clutch b13, main speed increasing gear box 8, torque meter b5, bevel gear box 9, flywheel accessory case 11 and simulation load 17.
Claims (9)
1. The simulation starting system of the test bed of the aircraft engine box is characterized by comprising a loading motor (1), a main dragging motor (2), a starting motor (3), a torque meter a (4), a torque meter b (5), a torque meter d (7), a main speed increasing gear box (8), a central bevel gear box (9), a starting speed increasing gear box (10) and a clutch b (13); one end of the input end of the main speed increasing gear box (8) is connected with a torque meter a (4), the other end of the input end is connected with a clutch b (13), the torque meter a (4) is connected with a loading motor (1), the clutch b (13) is connected with a main dragging motor (2), the output end of the main speed increasing gear box (8) is sequentially connected with a torque meter b (5), a central bevel gear box (9) and an aircraft engine case (11), and a starting motor (3) is sequentially connected with a starting speed increasing gear box (10), a torque meter d (7) and the aircraft engine case (11); after the required release rotational speed of the flywheel attachment box is reached, the main dragging motor (2) is actively involved and combined with the overrunning clutch b (13), the clutch a (12) in the main speed increasing gearbox (8) is released, and the loading motor (1) stops running; if the clutch is arranged in the aircraft engine case (11), the clutch in the aircraft engine case (11) is disconnected at the moment, and the starting motor (3) slowly stops running; if the flywheel attachment casing (11) is free of a clutch, the clutch c (14) in the starting speed increasing gear box (10) is disconnected at the moment, and the starting motor (3) slowly stops running.
2. The simulated starting system of the aircraft engine test bed according to claim 1, wherein the starting speed increasing gearbox (10) is connected with the torque meter c (6) and the calibration motor (16).
3. The aircraft-attached-casing test-bed simulation starting system according to claim 1, characterized in that the starting speed-increasing gearbox (10) is connected with the aircraft-attached casing (11) by means of splines or crowned teeth.
4. The aircraft-attached casing test bed simulation start system according to claim 1, wherein the start-up speed increasing gearbox (10) is modified to be in the form of a clutch c (14) or a clutch c (14) free according to the structure of the aircraft-attached casing (11).
5. The simulated starting system of the test bed of the aircraft engine box according to claim 1, wherein a clutch a (12) is arranged in the main speed increasing gear box (8), and the clutch a (12) is connected with the torque meter a (4) and the loading motor (1).
6. The simulated starting system of the test bed of the aircraft engine box according to claim 1, characterized in that an inertial flywheel (15) is reserved on the main speed increasing gearbox (8) for realizing the moment of inertia simulation when the motor (1) is not loaded.
7. The simulated starting system of the aircraft-attached casing test bed according to claim 1, wherein the rated power of the starting motor (3) is calculated and selected according to the maximum power of the starting process of the aircraft-attached casing (11), and the starting motor (3) realizes the starting rotation speed control of the aircraft-attached casing (11) through a starting speed increasing gearbox (10).
8. The aircraft-attached casing test bed simulation start system according to claim 1, characterized in that a simulation load (17) is also mounted on the aircraft-attached casing (11).
9. The starting method of the aircraft-assisted machine box test bed simulation starting system according to any one of claims 1-8, wherein a starting motor (3) is used as a power source in a starting test stage to drive a starting speed increasing gearbox (10), the starting speed increasing gearbox (10) is transmitted to a main speed increasing gearbox (8) through a torque meter d (7), an aircraft-assisted machine box (11) and a central bevel gearbox (9), the main dragging motor (2) follows rotation according to a rotating speed signal fed back by the starting motor (3), a clutch b (13) is in a disengaging state at the moment, torque characteristics of a starting process are compensated by a loading motor (1) according to a signal fed back by the torque meter b (5), in the starting test stage, starting rotating speed can be simulated, starting torque can be simulated, and the working sequence of a transmission chain at the moment is as follows: the starting motor (3) starts a speed increasing gear box (10), a torque meter d (7), a flywheel accessory case (11), a central cone gear box (9), a torque meter b (5), a main speed increasing gear box (8), a torque meter a (4) and a loading motor (1); after the required release rotational speed of the flywheel attachment box is reached, the main dragging motor (2) is actively intervened and combined with the clutch b (13), the clutch a (12) in the main speed increasing gear box (8) is released, and the loading motor (1) stops running; if the clutch is arranged in the aircraft engine case (11), the clutch in the aircraft engine case (11) is disconnected at the moment, and the starting motor (3) slowly stops running; if the flywheel attachment casing (11) is internally provided with no clutch, the clutch c (14) in the starting speed increasing gear box (10) is disconnected, the starting motor (3) is slowly stopped, and the working sequence of the transmission chain is as follows: the device comprises a main dragging motor (2), a clutch b (13), a main speed increasing gear box (8), a torque meter b (5), a bevel gear box (9), a flywheel attachment casing (11) and a simulation load (17).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202111031367.6A CN113916537B (en) | 2021-09-03 | 2021-09-03 | Simulation starting system and starting method for test bed of aircraft engine box |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111031367.6A CN113916537B (en) | 2021-09-03 | 2021-09-03 | Simulation starting system and starting method for test bed of aircraft engine box |
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| CN113916537A CN113916537A (en) | 2022-01-11 |
| CN113916537B true CN113916537B (en) | 2024-05-28 |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN211336489U (en) * | 2019-09-20 | 2020-08-25 | 中国航发哈尔滨东安发动机有限公司 | Quick switching system of flying auxiliary casing test bed |
| CN113266474A (en) * | 2021-06-01 | 2021-08-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for measuring starting resistance moment of aero-engine under loading condition |
| CN113310701A (en) * | 2021-06-15 | 2021-08-27 | 北京航空工程技术研究中心 | Complete machine tester for mechanical system of military turbofan engine |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8808142B2 (en) * | 2012-04-09 | 2014-08-19 | Hamilton Sundstrand Corporation | Aircraft APU electrical starter torque limiter |
| FR3012636B1 (en) * | 2013-10-24 | 2015-12-25 | Snecma | METHOD FOR NON-REGRESSION OF A DESIGN TOOL OF AN AIRCRAFT ENGINE MONITORING SYSTEM |
| US10266278B2 (en) * | 2016-10-11 | 2019-04-23 | Unison Industries, Llc | Starter issue detection |
| US11486795B2 (en) * | 2019-05-16 | 2022-11-01 | Textron Innovations, Inc. | Engine testing system and process |
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- 2021-09-03 CN CN202111031367.6A patent/CN113916537B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN211336489U (en) * | 2019-09-20 | 2020-08-25 | 中国航发哈尔滨东安发动机有限公司 | Quick switching system of flying auxiliary casing test bed |
| CN113266474A (en) * | 2021-06-01 | 2021-08-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for measuring starting resistance moment of aero-engine under loading condition |
| CN113310701A (en) * | 2021-06-15 | 2021-08-27 | 北京航空工程技术研究中心 | Complete machine tester for mechanical system of military turbofan engine |
Non-Patent Citations (1)
| Title |
|---|
| 飞行模拟机的某型涡扇发动机起动模型;熊海国;郑淑涛;姜洪洲;韩俊伟;;航空动力学报;20100315(03);全文 * |
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