Method and Structure for Detecting Angle Oscillation of Aircraft Engine Main Pump Regulator

Abstract

This invention relates to the field of aero-engine maintenance technology, and in particular to a method and structure for detecting the angle oscillation of an aero-engine main pump regulator that meets the performance requirements of the high-pressure guide vane. The method includes the following steps: a) First, connect the main pump regulator to be tested to the fixing mechanism on the testing device; b) Install the aero-engine's high-pressure compressor actuator on the corresponding high-pressure bracket of the testing device, and install the aero-engine's low-pressure compressor actuator on the corresponding low-pressure bracket of the testing device; c) Install the feedback mechanisms of the high-pressure compressor and low-pressure compressor on the testing device; d) Check the linearity and oscillation of the guide vane angle; e) Repeat step d again; f) If the linearity and oscillation of the guide vane angle are unqualified, return it to the repair or assembly process for troubleshooting; if the linearity and oscillation of the guide vane angle are qualified, the main pump regulator is delivered to the engine assembly and testing process.

Description

Technical Field

[0001] This invention relates to the field of aircraft engine maintenance technology, and in particular to a method and structure for detecting the angle oscillation of an aircraft engine main pump regulator. Background Technology

[0002] Parameter oscillation is a significant repair quality issue for aero-engines. During operation, it can cause fluctuations in other parameters such as n2 (high-pressure rotor speed) and T4 (low-pressure turbine after-temperature). This can range from preventing the engine from participating in flight training to causing excessive engine vibration. During maintenance, α2 oscillation faults frequently occur in the main pump regulator's high-pressure compressor adjustable guide vane angle, including some from unused new engines. This indicates a lack of research in this area both domestically and internationally. Therefore, to ensure the safety and reliability of aircraft and engines and improve the repair quality of aviation equipment, it is necessary to conduct research on suppressing α2 oscillation faults in aero-engine main pump regulators. This research aims to prevent α2 oscillation faults and thus avoid property damage to engines and aircraft due to inadequate repair methods, thereby impacting aircraft operation. Summary of the Invention

[0003] The technical problem to be solved by this invention is to provide a method and structure for detecting the angle oscillation of the main pump regulator high-pressure guide vane in aero-engines, thereby ensuring that the main pump regulator can meet the performance requirements of the engine high-pressure guide vane in subsequent operation.

[0004] The technical solution adopted by this invention to solve its technical problem is: a method for detecting the angle swing of an aero-engine main pump regulator, comprising the following steps: a) First, the detection device is fixedly installed on the ground. After all components of the main pump regulator are repaired, the main pump regulator to be tested is connected to the fixing mechanism on the detection device; b) The high-pressure compressor actuator of the aero-engine is installed on the high-pressure bracket corresponding to the detection device, and the low-pressure compressor actuator of the aero-engine is installed on the low-pressure bracket corresponding to the detection device, and the corresponding sensors are installed; c) The feedback mechanisms of the high-pressure compressor and the low-pressure compressor are installed on the detection device, and the feedback mechanisms are connected to the high-pressure feedback dial of the main pump regulator and the low-pressure... The feedback dials are connected to the corresponding terminals, ensuring that the movement of the feedback mechanism is the same as the actual operation of the engine; d. Start the engine and adjust the inlet air pressure, set the temperature of the aviation kerosene in the engine to the ambient temperature, and simultaneously set the engine intake air temperature to the range of -60℃ to 220℃. Then adjust the engine speed and check the linearity and oscillation of the high-pressure compressor guide angle of the main pump regulator; e. After setting the temperature of the aviation kerosene in the engine to 115±5℃, repeat step d again; f. If the linearity and oscillation of the guide angle are not up to standard, return it to the repair or assembly process for troubleshooting; if the linearity and oscillation of the guide angle are up to standard, the main pump regulator is delivered to the engine assembly and test run process.

[0005] Furthermore, in step b, there are two high-pressure compressor actuators for the aero-engine and two high-pressure supports for the detection device, with a one-to-one correspondence between the high-pressure compressor actuators and the high-pressure supports.

[0006] Furthermore, in step b, there are two low-pressure compressor actuators for the aero-engine and two low-pressure supports for the detection device, with a one-to-one correspondence between the high-pressure compressor actuators and the low-pressure supports.

[0007] Furthermore, in step c, the feedback mechanism is a feedback cable.

[0008] Furthermore, in step d, the engine inlet pressure is P = 1.57 MPa.

[0009] Furthermore, in step d, when the engine intake air temperature is -60℃, -45℃, 0℃, 15℃, 45℃, 80℃, 185℃ and 220℃ respectively, the engine speed is adjusted, and then the linearity and oscillation of the high-pressure compressor guide angle of the main pump regulator under the corresponding conditions are checked.

[0010] Furthermore, the detection structure of the main pump regulator angle oscillation detection method for aero-engines includes a base plate and a mounting plate mounted on the base plate. The mounting plate is provided with a fixing structure for fixing the main pump regulator. The mounting plate is provided with a high-pressure bracket and a low-pressure bracket, which are respectively matched and connected to the high-pressure compressor actuator and the low-pressure compressor actuator. The feedback mechanisms of the high-pressure compressor and the low-pressure compressor are respectively installed on the detection device, and the feedback mechanisms are respectively connected to the high-pressure feedback dial and the low-pressure feedback dial of the main pump regulator.

[0011] Furthermore, the feedback mechanism is a feedback cable or a feedback rod.

[0012] Furthermore, a rotating shaft is provided on the base plate, and the mounting plate is rotatably mounted on the rotating shaft via a bushing.

[0013] Furthermore, the base plate is provided with a mounting plate locking plate on its side, and the mounting plate locking plate is provided with a limit groove. The mounting plate limit bolt on the mounting plate is slidably disposed in the limit groove, and a limit nut is provided on the mounting plate limit bolt.

[0014] The beneficial effects of this invention are as follows: During actual testing, if the high-pressure guide angle of the main pump regulator is found to oscillate beyond the standard, it indicates poor repair quality and instability of the components. In this case, the main pump regulator will no longer be installed in the engine and will undergo re-inspection, i.e., returned to the repair or assembly process for troubleshooting. Traditional testing methods cannot quickly and effectively inspect the main pump regulator. If a substandard main pump regulator is installed in the engine, it may lead to faults such as high-pressure guide oscillation or n2 speed oscillation. Therefore, this method can effectively identify the main pump regulator and, if necessary, perform targeted troubleshooting, thus preventing and controlling the α2 oscillation fault of the main pump regulator. This invention is particularly applicable to the testing process after the repair of the aero-engine main pump regulator. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the present invention.

[0016] Figure 2 This is a front view of the present invention.

[0017] Figure 3 This is a top view of the present invention.

[0018] The components in the diagram are labeled as follows: base plate 1, mounting plate locking plate 101, limit nut 102, limit slide groove 103, mounting plate 2, high pressure support 3, high pressure strut 4, first high pressure bracket 5, high pressure tie rod 6, second high pressure bracket 7, third high pressure bracket 8, mounting lug 9, first low pressure bracket 10, low pressure tie rod 11, second low pressure bracket 12, third low pressure bracket 13, low pressure strut 14, feedback tie rod 15, low pressure tie rod bracket 16, bushing 17, rotating shaft 18, high pressure tie rod bracket 19, shaft mounting seat 20. Detailed Implementation

[0019] The invention will be further described below with reference to the accompanying drawings.

[0020] like Figure 1 , Figure 2 , Figure 3The method for detecting the angle sway of the main pump regulator of an aero-engine, as shown, includes the following steps: a) First, fix the detection device on the ground. After all components of the main pump regulator have been repaired, connect the main pump regulator to be tested to the fixing mechanism on the detection device; b) Install the high-pressure compressor actuator of the aero-engine on the high-pressure bracket corresponding to the detection device, and install the low-pressure compressor actuator of the aero-engine on the low-pressure bracket corresponding to the detection device, and install the corresponding sensors; c) Install the feedback mechanisms of the high-pressure compressor and the low-pressure compressor on the detection device, and connect the feedback mechanisms to the high-pressure feedback dial and the low-pressure feedback dial of the main pump regulator respectively, ensuring that the movement of the feedback mechanisms is the same as the actual operation of the engine; d) Start the engine. The engine is then adjusted, with the preferred inlet pressure being P = 1.57 MPa. The temperature of the aviation kerosene inside the engine is set to the ambient temperature, while the engine intake air temperature is within the range of -60℃ to 220℃, preferably at -60℃, -45℃, 0℃, 15℃, 45℃, 80℃, 185℃, and 220℃. The engine speed is then adjusted, and the linearity and oscillation of the high-pressure compressor guide angle of the main pump regulator are checked. e. After setting the aviation kerosene temperature inside the engine to 115±5℃, step d is repeated. f. If the linearity and oscillation of the guide angle are not up to standard, the engine is returned to the repair or assembly process for troubleshooting. If the linearity and oscillation of the guide angle are up to standard, the main pump regulator is delivered to the engine assembly and testing process. Corresponding to the above-described detection method, the detection device includes a base plate 1 and a mounting plate 2 disposed on the base plate 1. The mounting plate 2 has a fixing structure for fixing the main pump regulator. A high-pressure bracket and a low-pressure bracket are also provided on the mounting plate 2. The high-pressure bracket and the low-pressure bracket are respectively matched and connected to the high-pressure compressor actuator and the low-pressure compressor actuator. The feedback mechanisms of the high-pressure compressor and the low-pressure compressor are respectively installed on the detection device, and the feedback mechanisms are respectively connected to the high-pressure feedback dial and the low-pressure feedback dial of the main pump regulator. Preferably, to allow the mounting plate 2 to be flexibly adjusted in angle as needed, a rotating shaft 18 is provided on the base plate 1, and the mounting plate 2 is rotatably mounted on the rotating shaft 18 via a bushing 17. In order to realize the rotation and locking of the mounting plate 2, the bottom plate 1 is preferably provided with a mounting plate locking plate 101 on the side. The mounting plate locking plate 101 is provided with a limiting groove 103. The mounting plate limiting bolt on the mounting plate 2 is slidably provided in the limiting groove 103, and a limiting nut 102 is provided on the mounting plate limiting bolt.

[0021] The purpose of this invention is to overcome the two-chamber problem caused by the equal areas of the high and low pressure piston chambers in existing simulated actuator cylinders. It provides a device and method for simulating the angle of the high-pressure compressor guide vane in aero-engines, solving the problem of α2 oscillation failure in the main pump regulator of a certain type of aero-engine during flight operation, and achieving effective control of the aero-engine's inability to participate in flight due to α2 oscillation failure. By studying and determining the cause of the α2 oscillation failure in the main pump regulator, a dedicated performance testing device was designed and manufactured. An engine actuator cylinder with the same operating environment as the engine was installed on this device, and inspection measures and standards for the angle oscillation of the high-pressure guide vane were established. Through the application of this invention, improvements have been made to the repair methods of the main pump regulator, filling a gap in domestic and international repair practices and effectively reducing the occurrence of α2 oscillation failure in the main pump regulator.

[0022] In practical operation, the high-pressure compressor actuator of an aero-engine typically has two actuators. Preferably, the high-pressure support of the detection device in step b has two actuators, with a one-to-one correspondence between the high-pressure compressor actuator and the high-pressure support, thus ensuring the stable fixation of the high-pressure compressor actuator. Based on the same concept, in step b, the low-pressure compressor actuator of the aero-engine typically has two actuators, and the low-pressure support of the detection device has two actuators, with a one-to-one correspondence between the high-pressure compressor actuator and the low-pressure support. Furthermore, as control feedback for the high-pressure feedback dial and the low-pressure feedback dial, the preferred feedback mechanism is a feedback cable or a feedback rod 15.

Claims

1. A method for detecting the angle oscillation of an aircraft engine main pump regulator, characterized in that, Includes the following steps: a. First, fix the testing device on the ground. After all the components of the main pump regulator have been repaired, connect the main pump regulator to be tested to the fixing mechanism on the testing device. b. Install the high-pressure compressor actuator of the aero-engine on the high-pressure bracket corresponding to the detection device, install the low-pressure compressor actuator of the aero-engine on the low-pressure bracket corresponding to the detection device, and install the corresponding sensor. c. Install the feedback mechanisms of the high-pressure compressor and the low-pressure compressor on the detection device, and connect the feedback mechanisms to the high-pressure feedback dial and the low-pressure feedback dial of the main pump regulator respectively, and ensure that the movement of the feedback mechanism is the same as the actual operation of the engine. d. Start the engine and adjust the inlet air pressure. Set the temperature of the aviation kerosene in the engine to the ambient temperature, and the engine intake air temperature to be within the range of -60℃ to 220℃. Then adjust the engine speed and check the linearity and oscillation of the high-pressure compressor guide angle of the main pump regulator. e. After setting the temperature of the aviation kerosene in the engine to 115±5℃, repeat step d again; f. If the linearity and oscillation of the guide angle are not up to standard, the device shall be returned to the repair or assembly process for troubleshooting; if the linearity and oscillation of the guide angle are up to standard, the main pump regulator shall be delivered to the engine assembly and test run process.

2. The method for detecting the angle oscillation of the main pump regulator of an aero-engine as described in claim 1, characterized in that: In step b, there are two high-pressure compressor actuators for the aero-engine and two high-pressure supports for the detection device. The high-pressure compressor actuators and the high-pressure supports are set up in a one-to-one correspondence.

3. The method for detecting the angle oscillation of the main pump regulator of an aero-engine as described in claim 1, characterized in that: In step b, there are two low-pressure compressor actuators for the aero-engine and two low-pressure supports for the detection device. The high-pressure compressor actuators and the low-pressure supports are set up in a one-to-one correspondence.

4. The method for detecting the angle oscillation of the main pump regulator of an aero-engine as described in claim 1, 2, or 3, characterized in that: In step c, the feedback mechanism is a feedback cable.

5. The method for detecting the angle oscillation of the main pump regulator of an aero-engine as described in claim 1, 2, or 3, characterized in that: In step d, the engine inlet pressure is P = 1.57 MPa.

6. The method for detecting the angle oscillation of the main pump regulator of an aero-engine as described in claim 1, 2, or 3, characterized in that: In step d, when the engine intake air temperature is -60℃, -45℃, 0℃, 15℃, 45℃, 80℃, 185℃ and 220℃ respectively, the engine speed is adjusted, and then the linearity and oscillation of the high pressure compressor guide angle of the main pump regulator are checked under the corresponding conditions.

7. A detection structure for implementing the aircraft engine main pump regulator angle oscillation detection method as described in any one of claims 1 to 6, the detection device comprising a base plate (1) and a mounting plate (2) disposed on the base plate (1), characterized in that: The mounting plate (2) is provided with a fixing structure for fixing the main pump regulator. The mounting plate (2) is provided with a high-pressure bracket and a low-pressure bracket. The high-pressure bracket and the low-pressure bracket are respectively matched and connected to the high-pressure compressor actuator and the low-pressure compressor actuator. The feedback mechanisms of the high-pressure compressor and the low-pressure compressor are respectively installed on the detection device, and the feedback mechanisms are respectively connected to the high-pressure feedback dial and the low-pressure feedback dial of the main pump regulator.

8. The detection structure for implementing the method for detecting the angle sway of the main pump regulator of an aero-engine as described in claim 7, characterized in that: The feedback mechanism is a feedback cable or a feedback rod.

9. The detection structure for implementing the method for detecting the angle sway of the main pump regulator of an aero-engine as described in claim 7, characterized in that: The base plate (1) is provided with a rotating shaft (18), and the mounting plate (2) is rotatably mounted on the rotating shaft (18) through the bushing (17).

10. The detection structure for implementing the method for detecting the angle sway of the main pump regulator of an aero-engine as described in claim 9, characterized in that: The base plate (1) is provided with a mounting plate locking plate (101) on its side. The mounting plate locking plate (101) is provided with a limiting groove (103). The mounting plate limiting bolt on the mounting plate (2) is slidably disposed in the limiting groove (103). The mounting plate limiting bolt is matched with a limiting nut (102).

Images