A performance test device and test method for central transmission bevel gear of aircraft engine

Abstract

The present invention provides a performance test device and test method for central transmission bevel gears of aircraft engines, including a bevel gear casing assembly and a simulated gas turbine rotor casing assembly; the bevel gears of the bevel gear casing assembly are connected to a load generator for power load output; a transmission error test device and a dynamic stress test device are installed on the bevel gears; the simulated gas turbine shaft of the simulated gas turbine rotor casing assembly is connected to an electric motor through a transmission mechanism; a spring for applying axial force and a dynamic stress test device are installed at the rear end of the simulated gas turbine shaft; a central transmission active bevel gear and a transmission error test device are installed at the front end of the simulated gas turbine shaft, and the central transmission active bevel gear is meshed with the bevel gear in the first casing; a simulation disk is installed between the front end and the rear end of the simulated gas turbine shaft. The device of the present invention solves the problem that the existing aircraft engines cannot install a test measurement structure to perform performance tests on the central transmission bevel gears.

Description

Technical Field

[0001] The invention relates to a performance test device and a test method for a central transmission bevel gear of an aero-engine, which are used for a dynamic parameter measurement test of a central transmission bevel gear under a truly simulated aero-engine gas rotor working condition, and belong to the field of aerospace technology. Background Art

[0002] The accessory drive is an important part of the aircraft engine. The power source of the accessory drive parts installed in the aircraft engine is transmitted through a pair of central drive bevel gears installed in front of the engine gas rotor. The active bevel gear is installed on the front end of the gas turbine shaft through a spline connection; the passive bevel gear is installed on the front intake casing, and its internal spline is connected to a spline shaft to transmit power to the accessory drive casing to extract and transmit power. During use, the central drive bevel gear is affected by the different high-speed working conditions of the gas generator rotor and the vibration characteristics of the rotor, resulting in complex vibration excitation of the central drive bevel gear. During use, faults such as poor contact marks, cracks in the spokes, and excessive vibration have occurred many times. Therefore, it is necessary to test the transmission error and dynamic stress of the central bevel gear pair under various working conditions during the development period, and quantitatively evaluate its dynamic state. According to the test data, the structural design of the bevel gear is guided to achieve good dynamic response characteristics of the bevel gear.

[0003] At present, due to space and structural limitations, it is not possible to fully test the central transmission bevel gear pair in the whole machine state. Only individual engine structures can be tested for partial dynamic stress. Therefore, it is necessary to conduct tests simulating real working conditions, which can better simulate the working conditions of the whole machine to complete the performance test and evaluation of the central transmission bevel gear. Summary of the invention

[0004] The purpose of the present invention is to provide a device that can simulate the working conditions of a gas generator rotor in a complete machine state, and perform vibration test measurements on the transmission error and dynamic stress of a central transmission bevel gear pair, optimize the design parameters and modify the structure of the bevel gear through the test measurement data, and ultimately reduce the transmission error of the bevel gear, reduce the dynamic stress of the spoke plate, and improve the reliability of the bevel gear.

[0005] In order to achieve the above-mentioned purpose, the test device of the present invention adopts the following structural design scheme:

[0006] An aircraft engine central transmission bevel gear performance test device comprises a bevel gear casing assembly and a simulated gas turbine rotor casing assembly;

[0007] The bevel gear casing assembly comprises a first casing, wherein the bevel gear in the first casing is connected to a load generator for power load output;

[0008] Install a transmission error test device and a dynamic stress test device on the bevel gear;

[0009] The simulated gas turbine rotor casing assembly comprises a second casing, and the simulated gas turbine shaft in the second casing is connected to the electric motor through a transmission mechanism;

[0010] A spring for applying axial force is installed at the rear end of the simulated gas turbine shaft to simulate the stress state of the entire simulated gas turbine shaft on the engine;

[0011] At the end of the simulated gas turbine shaft rear end, a dynamic stress test device is installed;

[0012] A central transmission driving bevel gear is installed at the front end of the simulated gas turbine shaft, and the central transmission driving bevel gear is meshed with the bevel gear in the first casing;

[0013] A device for testing transmission errors is also installed at the front end of the simulated gas turbine shaft;

[0014] A simulated disk is mounted between the front and rear ends of the simulated gas turbine shaft.

[0015] Specific:

[0016] In the bevel gear casing assembly, a bevel gear is installed in the first casing through a third deep groove ball bearing; the bevel gear is connected to the load generator through a spline shaft;

[0017] On the upper part of the bevel gear, a first grating disk of a first circular grating encoder for testing a transmission error device is installed by locking with a nut, and a first reading head faces the first grating disk for data acquisition and output to a test acquisition system;

[0018] Strain gauges are pasted on the spokes of the bevel gears;

[0019] A first slip ring energizing pneumatic ring for dynamic stress testing is also installed on the spoke surface of the bevel gear. The first slip ring energizing pneumatic ring is connected to the test line of the strain gauge. The strain gauge converts the spoke shape into an electrical signal and transmits the signal to the first slip ring energizing pneumatic ring. The first slip ring energizing pneumatic ring rotates with the shaft and transmits the signal to the second static ring. The second static ring is connected to the test system to collect and output data.

[0020] Specific:

[0021] In the simulated gas turbine rotor casing assembly, the gear shaft of the driving gear is installed in the second casing through the first deep groove ball bearing and the second deep groove ball bearing; the motor is connected to the gear shaft of the driving gear through a spline;

[0022] The rear end of the simulated gas turbine shaft is supported by a second deep groove ball bearing; a driven gear is installed at the rear end of the simulated gas turbine shaft; and the driven gear is meshed with the driving gear.

[0023] At the end of the rear end of the simulated gas turbine shaft, a second slip ring energizing dynamic ring and a second static ring for dynamic stress testing are installed, and a test line is connected to the second slip ring energizing dynamic ring, and the test line is connected to a strain gauge pasted on the bevel gear spoke of the bevel gear casing assembly; the strain gauge converts the spoke shape into an electrical signal, and transmits the signal to the second slip ring energizing dynamic ring through a lead wire, and the second slip ring energizing dynamic ring rotates with the shaft and transmits the signal to the second static ring, and the second static ring is connected to the test system for data acquisition and output.

[0024] The front end of the simulated gas turbine shaft is installed in the first casing of the bevel gear casing assembly through a first deep groove ball bearing with elastic support; the central transmission active bevel gear is installed at the front end of the simulated gas turbine shaft, and the central transmission active bevel gear is pressed and installed in front of the first deep groove ball bearing with a self-locking nut.

[0025] A second circular grating encoder for testing the transmission error device is also installed at the front end of the simulated gas turbine shaft. The second circular grating encoder includes a second grating disk and a second reading head. The second grating disk is installed on the simulated gas turbine shaft. The second reading head completes data acquisition facing the second grating disk and outputs it to the test acquisition system.

[0026] The simulation disk includes a simulation engine compressor blade disk and a simulation turbine disk.

[0027] The gas turbine rotor casing assembly design of the present invention adopts a bearing support method consistent with the actual state of the engine to support the simulated gas turbine shaft. At the same time, in order to simulate the axial force of the compressor on the bevel gear, a spring device is added to the outer ring of the bearing at one end to achieve the application of axial force; axial flow, centrifugal and other compressor simulation blades and gas turbine simulation disks are installed on the simulated gas turbine shaft to achieve structural characteristics consistent with the actual state of the whole machine. The central active bevel gear is installed at the front of the simulated gas turbine shaft, close to the end of the compressor blade disk, and a small cylindrical gear is installed at the other end as a driven gear. The gears are as small in size and small in modulus as possible, and the difference between the outer diameter of the gear and the diameter of the simulated gas turbine shaft is as small as possible so as not to affect the dynamic state of the entire simulated gas turbine shaft. The small cylindrical gear is meshed with the driving gear, i.e., the large cylindrical gear, which is installed in the casing. The two are designed to increase the speed. The driving gear is designed with an internal spline to connect the input motor to realize power input. The above simulated gas turbine shaft and gears are installed as a whole in the gas turbine rotor casing. A measuring device for measuring transmission error is designed at the bevel gear end of the simulated gas turbine shaft, and a measuring device for measuring dynamic stress is designed and installed at the other end.

[0028] The main function of the bevel gear casing assembly is to complete the installation support of the central passive bevel gear, and at the same time connect the gas turbine rotor casing assembly with the load power device. The power is transmitted through the spline shaft to connect the load. At the same time, a test device for measuring the transmission error of the central transmission bevel gear is designed and installed inside the casing.

[0029] The above components are combined and assembled to complete the construction of the entire test device. After the entire device is connected to the test instrument, the dynamic characteristics test of the central transmission bevel gear can be completed.

[0030] According to the test device of the above invention, the dynamic stress and transmission error test of the central bevel gear can be completed. The specific test method is as follows, which is divided into several steps:

[0031] The first step is to test the test device established by installing the above structural invention. The motor is powered on to drive the entire device to operate. During operation, the load generator is not loaded with excitation power generation, that is, it runs idle. During the entire operation process, the speed is gradually increased from 10% of the designed rated speed to 120% of the speed, and each speed is kept for 1 minute. During the test, the vibration sensor installed randomly on the outside is monitored for vibration to ensure that the vibration speed value does not exceed 20mm / s and there is no leakage of lubricating oil.

[0032] The second step is to repeat the first step and load the load generator during operation. The loading power is synchronously increased to 120% of the rated power according to 10% of the speed. Check the vibration and leakage to ensure that the vibration speed does not exceed 20mm / s and there is no lubricating oil leakage. During operation, check whether the sensor signals of the first grating disk, the first reading head, the second reading head, the second grating disk, the first slip ring energizing dynamic ring, the second static ring, the second slip ring energizing dynamic ring, and the second static ring are connected and displayed normally. Check and debug the abnormal parts until they work normally.

[0033] The third step is to collect data on the transmission error and dynamic stress of each speed and power state for 5 minutes in a steady state according to various working conditions of the central transmission bevel gear of the test. After the collection is completed, the machine is shut down for 1 hour after running for 30 minutes at the rated state, and then the data on the transmission error and dynamic stress of each speed and power state for 5 minutes in a steady state are repeated. After the collection is completed, the machine can be shut down to complete the test. The data collection of the above entire test is completed by the relevant computer acquisition system, and the acquisition system does not belong to the content included in the present invention.

[0034] The device and method of the present invention solve the problem that the existing aircraft engine cannot install a test measurement structure to perform performance testing on the central transmission bevel gear, and provide a method for structural performance research of the central transmission bevel gear. According to the structure of the central transmission bevel gear of different models of aircraft engines, the relevant parameters and structure can be changed to adapt to the use of different working conditions test research. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] Figure 1 It is a schematic diagram of the structure of the present invention. DETAILED DESCRIPTION

[0036] The specific technical solution of the present invention is described in conjunction with the accompanying drawings.

[0037] like Figure 1 As shown, an aircraft engine central transmission bevel gear performance test device includes a bevel gear casing assembly and a simulated gas turbine rotor casing assembly;

[0038] The simulated gas turbine rotor casing assembly includes a second casing 2; the electric motor P1 is connected to the gear shaft of the driving gear 32 in the second casing 2 through a spline for inputting power and speed, the gear shaft of the driving gear 32 is supported by a first deep groove ball bearing 30 and a second deep groove ball bearing 31, the driving gear 32 is meshed with the driven gear 27, and the driven gear 27 is installed on the rear end of the simulated gas turbine shaft 21 through an interference fit.

[0039] The front and rear ends of the simulated gas turbine shaft 21 are supported by a first deep groove ball bearing 14 and a second deep groove ball bearing 28 with elastic supports, respectively;

[0040] A spring 29 that applies axial force is installed at the rear of the outer ring of the second deep groove ball bearing 28, so that the simulated gas turbine shaft 21 is forced toward the front end; it is used to simulate the stress state of the entire simulated gas turbine shaft 21 on the engine;

[0041] At the end of the rear end of the simulated gas turbine shaft 21, a second slip ring energizing dynamic ring D1 and a second static ring D2 for dynamic stress testing are installed. The second slip ring energizing dynamic ring D1 is connected to a test line, and the test line is connected to a strain gauge pasted on the spoke plate of the bevel gear 11 of the bevel gear casing assembly; the strain gauge converts the spoke shape into an electrical signal, and transmits the signal to the second slip ring energizing dynamic ring D1 through a lead wire. The second slip ring energizing dynamic ring D1 rotates with the shaft and transmits the signal to the second static ring D2. The second static ring D2 is connected to a test system to complete data acquisition and output.

[0042] The front end of the simulated gas turbine shaft 21 is located inside the first casing 1 of the bevel gear casing assembly;

[0043] A central transmission driving bevel gear 12 is installed at the front end of the simulated gas turbine shaft 21. The central transmission driving bevel gear 12 is pressed and installed at the front of the first deep groove ball bearing 14 by a self-locking nut 15. The central transmission driving bevel gear 12 is meshed with the bevel gear 11 of the bevel gear casing assembly.

[0044] A second circular grating encoder for testing the transmission error device is also installed at the front end of the simulated gas turbine shaft 21. The second circular grating encoder includes a second grating disk B2 and a second reading head B1. The second grating disk B2 is assembled to the simulated gas turbine shaft 21 through an interference fit. The second reading head B1 completes data acquisition facing the second grating disk B2 and outputs it to the test acquisition system.

[0045] A simulated disk is installed between the front end and the rear end of the simulated gas turbine shaft 21, and the simulated disk includes a simulated engine compressor blade disk and a simulated turbine disk;

[0046] A simulated engine compressor blade disk, comprising a first simulated engine compressor blade disk 22 and a second simulated engine compressor blade disk 23;

[0047] The simulated turbine disk includes a first simulated turbine disk 24, a second simulated turbine disk 25, and a third simulated turbine disk 26;

[0048] The structure parameters such as the structure and weight of each level of the simulated disk can be adjusted according to the different structures of the engine. Each simulated disk is assembled on the rotor shaft through the interference fit of the stepped shaft.

[0049] In the bevel gear casing assembly, inside the first casing 1, a support position is designed for the first deep groove ball bearing 14 to complete the support of one end of the simulated gas turbine shaft 21;

[0050] A bevel gear 11 meshing with the central transmission active bevel gear 12 is designed and installed in the first casing 1. The bevel gear 11 is supported by a third deep groove ball bearing 13. The bevel gear 11 is connected to the load generator P2 through a spline shaft 17 to complete the power load output of the entire test system.

[0051] On the upper part of the bevel gear 11, the first grating disk A1 of the first circular grating encoder for testing the transmission error device is locked and installed by a nut 16, and the first reading head A2 faces the first grating disk A1 to complete data acquisition and output to the test acquisition system. On the spoke surface of the bevel gear 11, the first slip ring energizing pneumatic ring C1 for dynamic stress test is installed by colloid bonding. The first slip ring energizing pneumatic ring C1 is connected to the test line on the strain gauge attached to the spoke of the bevel gear 11. The strain gauge converts the spoke shape into an electrical signal, and transmits the signal to the first slip ring energizing pneumatic ring C1 through the lead wire. The first slip ring energizing pneumatic ring C1 rotates with the shaft and transmits the signal to the second static ring C2. The second static ring C2 is connected to the test system to complete data acquisition and output.

[0052] According to the test device of the above invention, the dynamic stress and transmission error test of the central bevel gear can be completed. The specific test method is as follows, which is divided into several steps:

[0053] The first step is to test the test device installed with the above structural invention. The motor P1 is powered on to drive the entire device to operate. During operation, the load generator P2 is not loaded with excitation power generation, that is, it runs idle. During the entire operation process, the speed is gradually increased from 10% of the designed rated speed to 120% speed, and each speed is kept for 1 minute. During the test, the vibration sensor installed randomly on the outside is monitored for vibration to ensure that the vibration speed value does not exceed 20mm / s and there is no leakage of lubricating oil.

[0054] The second step is to repeat the first step and load the load generator P2 during operation. The loading power is synchronously increased to 120% of the rated power according to 10% of the speed. Check the vibration and leakage to ensure that the vibration speed does not exceed 20mm / s and there is no lubricating oil leakage. During operation, check whether the sensor signals at the first grating disk A1, the first reading head A2, the second reading head B1, the second grating disk B2, the first slip ring energizing dynamic ring C1, the second static ring C2, the second slip ring energizing dynamic ring D1, and the second static ring D2 are connected and displayed normally. Check and debug the abnormal parts until they work normally.

[0055] The third step is to collect data on the transmission error and dynamic stress of each speed and power state for 5 minutes in a steady state according to various working conditions of the central transmission bevel gear of the test. After the collection is completed, the machine is shut down for 1 hour after running for 30 minutes at the rated state, and then the data on the transmission error and dynamic stress of each speed and power state for 5 minutes in a steady state are repeated. After the collection is completed, the machine can be shut down to complete the test. The data collection of the above entire test is completed by the relevant computer acquisition system, and the acquisition system does not belong to the content included in the present invention.

[0056] The device can solve the problem that the performance parameters of bevel gears cannot be measured under the complete engine state, and can accurately simulate the dynamic characteristics of the central transmission bevel gear pair under the influence of the engine turbine shaft, and can simultaneously measure the transmission error and web stress of the bevel gear under various speed conditions. By changing the structure of the simulated blades and disks, the characteristics of gas turbine rotors with different structures can be adapted. By changing the transmission ratio of a pair of cylindrical gears and adjusting the speed of the drive motor, it can adapt to turbine rotors with different speed states, and adapt to the data collection of dynamic characteristics of bevel gears under various speed conditions of engines of different models.

[0057] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and changes. Any modification, equivalent replacement, and improvement made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A performance test device for central transmission bevel gears of aircraft engines, It is characterized in that It includes a bevel gear casing assembly and a simulated gas turbine rotor casing assembly; The bevel gear casing assembly comprises a first casing (1), wherein the bevel gear (11) in the first casing (1) is connected to a load generator (P2) for power load output; A transmission error testing device and a dynamic stress testing device are installed on the bevel gear (11); The simulated gas turbine rotor casing assembly comprises a second casing (2), wherein the simulated gas turbine shaft (21) in the second casing (2) is connected to the electric motor (P1) via a transmission mechanism; A spring (29) for applying an axial force is installed at the rear end of the simulated gas turbine shaft (21) to simulate the stress state of the entire simulated gas turbine shaft (21) on the engine; A dynamic stress testing device is installed at the end of the simulated gas turbine shaft (21) rear end; A central transmission driving bevel gear (12) is installed at the front end of the simulated gas turbine shaft (21), and the central transmission driving bevel gear (12) is meshed with the bevel gear (11) in the first casing (1); A transmission error testing device is also installed at the front end of the simulated gas turbine shaft (21); A simulated disk is installed between the front end and the rear end of the simulated gas turbine shaft (21).

2. An aircraft engine central transmission bevel gear performance test device according to claim 1, It is characterized in that In the bevel gear casing assembly, a bevel gear (11) is installed in the first casing (1) via a third deep groove ball bearing (13); the bevel gear (11) is connected to a load generator (P2) via a spline shaft (17); A first grating disk (A1) of a first circular grating encoder for testing a transmission error device is installed on the upper part of the bevel gear (11) by locking with a nut (16), and a first reading head (A2) is directly opposite to the first grating disk (A1) for data acquisition and output to a test acquisition system; A strain gauge is pasted on the spoke plate of the bevel gear (11); A first slip ring energizing dynamic ring (C1) for performing a dynamic stress test is also installed on the radial plate surface of the bevel gear (11). The first slip ring energizing dynamic ring (C1) is connected to a test line of the strain gauge. The strain gauge converts the radial plate shape into an electrical signal and transmits the signal to the first slip ring energizing dynamic ring (C1). The first slip ring energizing dynamic ring (C1) rotates with the shaft and transmits the signal to the second static ring (C2). The second static ring (C2) is connected to a test system to collect and output data.

3. The performance test device for central transmission bevel gear of an aircraft engine according to claim 1, It is characterized in that In the simulated gas turbine rotor casing assembly, the gear shaft of the driving gear (32) is installed in the second casing (2) via a first deep groove ball bearing (30) and a second deep groove ball bearing (31); the motor (P1) is connected to the gear shaft of the driving gear (32) via a spline; The rear end of the simulated gas turbine shaft (21) is supported by a second deep groove ball bearing (28); a driven gear (27) is installed at the rear end of the simulated gas turbine shaft (21); and the driven gear (27) is meshed with the driving gear (32).

4. The performance test device for central transmission bevel gear of an aircraft engine according to claim 1, It is characterized in that A second slip ring induced electromechanical ring (D1) and a second static ring (D2) for dynamic stress testing are installed at the end of the rear end of the simulated gas turbine shaft (21); a test line is connected to the second slip ring induced electromechanical ring (D1); the test line is connected to a strain gauge pasted on a spoke plate of a bevel gear (11) of a bevel gear casing assembly; the strain gauge converts the spoke plate shape into an electrical signal, and transmits the signal to the second slip ring induced electromechanical ring (D1) through a lead wire; the second slip ring induced electromechanical ring (D1) rotates with the shaft and transmits the signal to the second static ring (D2); the second static ring (D2) is connected to a test system for data acquisition and output.

5. The performance test device for central transmission bevel gear of an aircraft engine according to claim 1, It is characterized in that The front end of the simulated gas turbine shaft (21) is installed in the first casing (1) of the bevel gear casing assembly through a first deep groove ball bearing (14) with elastic support; the central transmission active bevel gear (12) is installed at the front end of the simulated gas turbine shaft (21), and the central transmission active bevel gear (12) is pressed and installed on the front part of the first deep groove ball bearing (14) using a self-locking nut (15).

6. The performance test device for central transmission bevel gear of an aircraft engine according to claim 1, It is characterized in that A second circular grating encoder for testing a transmission error device is also installed at the front end of the simulated gas turbine shaft (21). The second circular grating encoder comprises a second grating disk (B2) and a second reading head (B1). The second grating disk (B2) is installed on the simulated gas turbine shaft (21). The second reading head (B1) faces the second grating disk (B2) to complete data acquisition and output to the test acquisition system.

7. The performance test device for central transmission bevel gear of an aircraft engine according to claim 1, It is characterized in that The simulation disk includes a simulation engine compressor blade disk and a simulation turbine disk.

8. A test method for a performance test device for central transmission bevel gears of an aircraft engine according to any one of claims 1 to 7, It is characterized in that The following steps are involved: The first step is to test the test device, power up the motor (P1) to drive the entire test device to run, and during the operation, the load generator (P2) is not loaded with excitation power generation, that is, it runs idle. During the entire operation process, the speed is gradually increased from 10% of the designed rated speed to 120% speed, and each speed is kept for 1 minute. During the test, the vibration sensor installed randomly outside is used to monitor the vibration to ensure that the vibration speed value does not exceed 20 mm / s, and there is no lubricating oil leakage; The second step is to repeat the first step and load the load generator (P2) during operation. The loading power is synchronously increased to 120% of the rated power according to 10% of the speed. The vibration and leakage are checked to ensure that the vibration speed value does not exceed 20mm / s and there is no lubricating oil leakage. During the operation, the sensor signals at various locations are connected and displayed normally. Any abnormal locations are checked and debugged until they work normally. The third step is to collect data on the transmission error and dynamic stress for 5 minutes in a steady state at each speed and power state according to the various working conditions of the central transmission bevel gear in the test. After the collection is completed, the machine is shut down for 1 hour after running at the rated state for 30 minutes, and then the data on the transmission error and dynamic stress for 5 minutes in a steady state are repeated at each speed and power state. After the collection is completed, the machine can be shut down to complete the test.

Images