Methods for troubleshooting oil leaks in the sealing device of an aircraft engine afterburner pump

Abstract

This application relates to the field of aero-engine maintenance technology, specifically disclosing a method for troubleshooting oil leakage faults in the sealing device of an aero-engine afterburner pump. The method includes setting up a break-in device, which comprises: a mounting plate, a product support, a splined shaft connector, a diaphragm-type flexible coupling, and a servo motor. The method involves placing the afterburner pump bearing housing and sealing device assembly to be repaired on the product support, with the splined shaft at one end of the afterburner pump bearing housing connected to the diaphragm-type flexible coupling via the first connector of the splined shaft connector. By quantitatively controlling the servo motor's rotational speed, speed uniformity, and circumferential break-in stroke, automated and precise repair of the sealing device assembly is achieved. This addresses the problem in the prior art where, even after the afterburner pump sealing device has been repaired to standard according to current processes, a certain oil leakage rate still exists between the dynamic ring and the graphite ring during use, causing frequent oil leakage faults in the sealing device of the engine afterburner pump in the field.

Description

Technical Field

[0001] This application relates to the field of aircraft engine maintenance technology, specifically to a method for troubleshooting oil leakage faults in the sealing device of an aircraft engine afterburner pump. Background Technology

[0002] The afterburning fuel control system of an aircraft engine consists of two parts: the fuel supply system and the control system. The afterburning pump is a crucial component of the fuel supply system, with two main functions: first, to deliver pressurized fuel to the afterburner; and second, in emergency situations, to draw fuel from the aircraft's fuel tanks and release it through the afterburner. During afterburner operation, based on the throttle position signal, the afterburner pump's return fuel path is cut off. High-pressure fuel from the gear pump drives the inlet valve to open the afterburner pump's inlet fuel path. The impeller outlet pressure continuously increases under the combined action of the sealing device and the inlet fuel, ultimately opening the outlet valve to supply fuel to the afterburning fuel system.

[0003] The sealing device is a core component of the booster pump, controlling the stability of fuel supply and thrust during engine boost. The sealing device mainly consists of a sealing housing, graphite ring, rotating ring, graphite ring bushing, and spring. The structures of the corresponding components on the fuel and oil ends are identical, with the graphite ring and rotating ring in close contact. Severe oil leakage between the rotating and graphite rings can lead to engine malfunctions such as excessive oil consumption; severe fuel leakage can cause abnormal nozzle opening and closing, and low fuel supply pressure. In existing technology, booster pumps frequently experience sealing device leakage failures in the field. Severe leakage poses a significant quality hazard to the normal operation of the engine.

[0004] Based on the structural and performance characteristics of the booster pump's transmission components, it is known that in high-speed operating environments, the perpendicularity error between the rotating ring plane and the theoretical central axis is difficult to eliminate. This leads to leakage of pressurized fuel and lubricating oil through the gap between the rotating ring plane and the graphite ring. During booster pump repair, the sealing device needs to be disassembled and inspected. Disassembly revealed uneven wear on the sealing surfaces of the base and graphite ring of the leaking sealing device. Following the original repair method, the sealing contact surface of the rotating ring was manually ground before assembly, and the graphite ring, being a replacement part, was directly replaced with a new one. However, even after the rotating ring was repaired to meet the specifications, a certain leakage rate still existed, severely impacting the quality and efficiency of in-plant testing. Simultaneously, due to dimensional and positional tolerances during machining (parallelism tolerances and parallelism of rotating parts), the sealing surface where the rotating ring and graphite ring contact always exhibits end-face runout along the axis. This ultimately leads to a small amount of oil seeping between the repaired rotating ring and the new graphite ring, seriously affecting the operational safety of the aircraft engine. Summary of the Invention

[0005] The purpose of this application is to provide a method for eliminating oil leakage faults in the sealing device of an aero-engine afterburner pump, in order to solve the problem that in the prior art, after the sealing device of the afterburner pump is repaired to meet the standards according to the current process, there is still a certain oil leakage rate between the dynamic ring and the graphite ring during use, which causes frequent oil leakage faults in the sealing device of the engine afterburner pump in the field.

[0006] To achieve the above objectives, embodiments of this application provide a method for troubleshooting oil leakage in the sealing device of an aero-engine afterburner pump.

[0007] The method includes setting up a break-in device, which comprises: a mounting plate, a product support, a splined shaft connector, a diaphragm-type flexible coupling, and a servo motor.

[0008] The product support is located at the right end of the mounting plate and is used to fix the booster pump bearing housing and sealing device to be repaired.

[0009] The first connector on the splined shaft connector is connected to the splined shaft extending from the left end of the booster pump bearing housing to be repaired via a sleeve tooth connection.

[0010] The right end of the diaphragm-type flexible coupling is connected to the splined shaft connector.

[0011] The rotating shaft of the servo motor is connected to the left end of the diaphragm-type flexible coupling;

[0012] The method for troubleshooting oil leakage in the afterburner pump sealing device of an aircraft engine using the aforementioned break-in device includes:

[0013] Step 1) Place the booster pump bearing housing and sealing device assembly to be repaired on the product support. The splined shaft at one end of the booster pump bearing housing is connected to the diaphragm type flexible coupling through the first connector of the splined shaft connector.

[0014] Step 2) By quantitatively controlling the speed, speed uniformity, and circumferential running-in stroke of the servo motor, the sealing device components can be automatically and precisely repaired.

[0015] Optionally, the method includes:

[0016] A first support plate and a second support plate are provided on the product support, and the two ends of the booster pump bearing housing and the sealing device assembly to be repaired are placed on the first support plate and the second support plate respectively.

[0017] The first and second support plates each have a semi-circular notch at their upper ends that couples with the outer ring of the booster pump bearing housing, and the second support plate has a pin hole.

[0018] Optionally, the method includes:

[0019] A pin assembly is provided to connect the first bushing at the right end of the diaphragm-type flexible coupling to the spline shaft connector via the pin assembly.

[0020] Optionally, the method includes:

[0021] The rotating shaft of the servo motor is connected to the second bushing located at the left end of the diaphragm-type flexible coupling.

[0022] Optionally, the method includes:

[0023] A servo motor base is provided, and the lower end of the servo motor base is fixed to the left end of the mounting plate. A vertically installed fixing plate is provided on the right end of the servo motor base.

[0024] The lower end of the servo motor housing is fixed to the upper end of the servo motor base, and the right end of the servo motor housing is fixed to the fixing plate.

[0025] Optionally, the method includes:

[0026] A simulated pressure sleeve is installed, which is fitted onto the drive shaft extending from the right end of the booster pump bearing housing to be repaired.

[0027] Optionally, the method includes:

[0028] A baffle support is provided, which is located on one side of the diaphragm type flexible coupling. The lower end of the baffle support is connected to the mounting plate, and the upper end of the baffle support is provided with a baffle pin. Both the left and right ends of the baffle pin are rotatably connected to the upper end of the baffle support, and a baffle clamp is provided in the middle of the baffle pin.

[0029] A baffle is provided, the upper end of which is connected to the baffle clamp.

[0030] A baffle bracket is provided, the lower end of which is connected to the mounting plate, and the upper end of which is connected to the lower end of the baffle.

[0031] Optionally, the method includes:

[0032] A first pin is provided, which passes through the pin hole and the through hole opened on the sealing housing of the sealing device to fix the sealing device to the second support plate.

[0033] Optionally, the method includes:

[0034] The mounting plate is provided with handles, two of which are located at opposite ends of the mounting plate.

[0035] Optionally, the method includes:

[0036] A switch holder is provided, and the switch in the switch holder is electrically connected to the servo motor for controlling the start and stop of the servo motor;

[0037] A power switch indicator light is provided, which is electrically connected to the switch provided in the switch socket, and is used to indicate whether the switch is open or closed.

[0038] The embodiments of this application have the following advantages:

[0039] Compared with existing technologies, the above-mentioned technical solution can effectively improve the running-in degree of the contact sealing surfaces of the dynamic ring and graphite ring without affecting the assembly of the sealing device. It reduces dimensional and positional tolerances caused by machining and perpendicularity errors between the dynamic ring plane and the theoretical axis caused during operation, thereby improving the sealing performance of the sealing device. Simultaneously, by quantitatively controlling the servo motor's speed, speed uniformity, and circumferential running-in stroke, it achieves automated and precise repair of the sealing device components, ensuring the running-in degree between the dynamic ring and graphite ring, reducing maintenance costs, improving the repair efficiency of the sealing device, and thus enhancing the repair quality of the sealing device and preventing oil leakage during the use of the booster pump. By using the running-in device designed to eliminate oil leakage in the sealing device of the aero-engine booster pump, the mutual running-in action of the two contact sealing surfaces can be used to improve the fit at the sealing surface under simulated actual relative movement of the dynamic ring and graphite ring, and to inspect the running-in marks and sealing performance of the dynamic ring base. Furthermore, this method also includes the development of running-in tools and the improvement of running-in methods to ensure running-in efficiency and improve the repair quality of the sealing device. This method can eliminate oil leakage from the sealing device during the use of booster pumps, solve the problem of booster connection failure caused by oil leakage from the sealing device of a certain type of aero-engine, improve production efficiency and product quality, and ultimately achieve the effect of improving quality and efficiency. Attached Figure Description

[0040] To more clearly illustrate the embodiments of this application or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are merely exemplary, and those skilled in the art can derive other embodiments based on the provided drawings without creative effort.

[0041] Figure 1 A perspective view of a break-in device used in a method for troubleshooting oil leakage in an afterburner pump sealing device of an aircraft engine, provided in at least one embodiment of this application;

[0042] Figure 2 A front view of a break-in device used in a method for troubleshooting oil leakage in an afterburner pump sealing device of an aircraft engine, provided in at least one embodiment of this application;

[0043] Figure 3 A top view of a break-in device used in a method for troubleshooting oil leakage in an afterburner pump sealing device of an aircraft engine, provided in at least one embodiment of this application;

[0044] Figure 4 A cross-sectional view of the splined shaft connector of a break-in device used in a method for troubleshooting oil leakage in an afterburner pump sealing device of an aircraft engine, provided in at least one embodiment of this application;

[0045] Figure 5 A partial cross-sectional view of the pin assembly of the break-in device used in a method for troubleshooting oil leakage in an afterburner pump sealing device of an aircraft engine, provided in at least one embodiment of this application.

[0046] Figure 6 A front view of the pin assembly of a break-in device used in a method for troubleshooting oil leakage in an afterburner pump sealing device of an aircraft engine, provided in at least one embodiment of this application;

[0047] Figure 7 A schematic diagram showing the connection between the servo motor rotating shaft, diaphragm type flexible coupling, pin shaft assembly, and spline shaft connector of the break-in device used in a method for troubleshooting oil leakage in the sealing device of an aero-engine afterburner pump provided in at least one embodiment of this application.

[0048] Figure 8 A simulated pressure sleeve cross-sectional view of a break-in device used in a method for troubleshooting oil leakage in an afterburner pump sealing device of an aircraft engine, provided in at least one embodiment of this application.

[0049] Meaning of the reference numerals in the attached figures:

[0050] 1-Servo motor, 2-Screw, 3-Diaphragm type flexible coupling, 4-Pin assembly, 5-Splined shaft connector, 6-First pin, 7-Simulation pressure sleeve, 8-Product support, 9-Baffle bracket, 10-Handle, 11-Servo motor base, 12-Mounting plate, 13-First support piece, 14-Second support piece, 15-Positioning hole, 16-First connector, 17-Switch base, 18-Power switch indicator light, 19-Hex head bolt, 20-Baffle support, 21-Baffle, 22-Baffle clamp, 23-Baffle pin, 24-Pin body, 25-Spring, 26-Steel ball, 27-Second connector, 28-Rotating shaft, 29-First bushing, 30-Power pump bearing housing and sealing device assembly, 31-Second bushing. Detailed Implementation

[0051] The following specific embodiments illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0052] In the description of this application, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicating orientation or positional relationships based on the orientation or positional relationships shown in the accompanying drawings, are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on this application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. Unless otherwise expressly specified and limited, the terms "set," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections or electrical connections; they can refer to direct connections or indirect connections through an intermediate medium; and they can refer to the internal communication of two elements. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0053] It should also be noted that the terms “step 1),” “step 2),” “step 3),” etc. in the claims and description of this application are used to distinguish different steps, rather than to describe a specific order or sequence. It should be understood that these steps may be performed substantially in parallel or in reverse order, depending on the function involved.

[0054] Furthermore, the technical features involved in the different embodiments of this application described below can be combined with each other as long as they do not conflict with each other.

[0055] The existing repair method only involves manually grinding the sealing contact surface of the rotating ring before assembly, ensuring that the flatness meets the process requirements. The graphite ring is a replacement part and is directly replaced with a new one. This repair method has certain drawbacks. Manual grinding is prone to human error, which leads to poor grinding quality of the rotating ring contact sealing surface. In addition, grinding the rotating ring contact sealing surface alone cannot simulate the perpendicularity error between the rotating ring plane and the theoretical axis that may be caused by the relative movement of the two, thus forming uneven circumferential running-in marks.

[0056] The embodiments of this application propose a repair method for an afterburner pump sealing device to troubleshoot oil leakage faults, the method comprising the following aspects:

[0057] First, the break-in repair should be conducted under simulated actual relative motion between the rotating ring and the graphite ring to reduce the perpendicularity error between the rotating ring plane and the theoretical axis caused by the high speed of the booster pump. Second, the running-in of the rotating ring base sealing surface should be uniform, and the running-in stroke and rotational torque should be precisely controlled to ensure a tight fit between the rotating ring and the graphite ring, preventing oil leakage due to dimensional and positional tolerances caused by machining (parallelism tolerances of rotating parts, etc.). Specific implementation plans include:

[0058] This application embodiment designs a break-in device automatically controlled by a servo motor for troubleshooting oil leakage faults in the sealing device of an aero-engine booster pump. By using this break-in device, the speed, speed uniformity, and circumferential break-in stroke of the servo motor are quantitatively controlled to achieve automated and precise repair of the sealing device components, thereby ensuring the break-in degree between the dynamic ring and the graphite ring and improving the repair efficiency of the sealing device.

[0059] This application provides a method for troubleshooting oil leakage in the sealing device of an aero-engine afterburner pump. The method includes setting up a break-in device. Using the break-in device, 1. the afterburner pump bearing housing and sealing device assembly 30 to be repaired are placed on the product support 8 of the break-in device. The splined shaft at one end of the afterburner pump bearing housing is connected to the diaphragm-type flexible coupling 3 of the break-in device through the first connector 16 of the splined shaft connector 5 of the break-in device; 2. the automatic and precise repair of the sealing device assembly is achieved by quantitatively controlling the speed, speed uniformity, and circumferential break-in stroke of the servo motor 1 of the break-in device.

[0060] refer to Figures 1 to 3 The break-in device includes:

[0061] Mounting plate 12.

[0062] Product support 8, which is located at the right end of the mounting plate 12, is used to fix the booster pump bearing housing and sealing device to be repaired.

[0063] In some embodiments, the product support 8 includes a first support plate 13 and a second support plate 14. The upper ends of the first support plate 13 and the second support plate 14 are provided with semi-circular notches that are coupled to the outer ring of the booster pump bearing housing. The second support plate 14 is provided with pin holes.

[0064] Splined shaft connector 5, wherein the first connector 16 provided on the splined shaft connector 5 is connected to the splined shaft extending from the left end of the booster pump bearing housing to be repaired via a sleeve tooth connection.

[0065] Specifically, refer to Figure 4 The spline shaft connector 5 includes a first connector 16 and a second connector 27 that are connected to each other. The first connector 16 is machined with inner teeth for connecting with the spline shaft at the left end of the booster pump bearing housing to be repaired, thereby transmitting the torque of the servo motor 1. The spline shaft connector 5 connects the dynamic ring and the graphite ring through the spline shaft, ensuring precise positioning without offset and serving a fixing and positioning function.

[0066] A diaphragm-type flexible coupling 3 is provided, the right end of which is connected to a splined shaft connector 5.

[0067] Specifically, a diaphragm-type flexible coupling 3 is adopted, as referenced. Figure 7 The left end of the diaphragm-type flexible coupling 3 is directly connected to the bushing on the servo motor 1, and the right end is connected to the spline shaft connector 5. This can effectively reduce axial deviation and vibration, and reduce the perpendicularity error between the dynamic ring plane and the theoretical axis.

[0068] In some embodiments, the device further includes a pin assembly 4, wherein the first bushing 29 disposed at the right end of the diaphragm-type flexible coupling 3 is connected to the spline shaft connector 5 via the pin assembly 4.

[0069] Specifically, refer to Figure 5 and Figure 6 The pin assembly 4 includes a pin body 24, a spring 25, and a steel ball 26. (Reference) Figure 7 The right end of the diaphragm-type flexible coupling 3 is locked to the first bushing 29 of the pin assembly 4 by a second pin. The left end of the pin assembly 4 is inserted into the first bushing 29 of the diaphragm-type flexible coupling 3, and the right end of the pin assembly 4 is connected to the second connector 27 provided on the splined shaft connector 5. Specifically, the connection between the right end of the pin assembly 4 and the second connector 27 is achieved by inserting the steel ball 26 of the pin assembly 4 into the positioning hole 15 of the second connector 27.

[0070] Servo motor 1, the rotating shaft 28 of which is connected to the left end of diaphragm type flexible coupling 3.

[0071] refer to Figure 7 In some embodiments, the rotating shaft 28 of the servo motor 1 is connected to the second bushing 31 disposed at the left end of the diaphragm elastic coupling 3.

[0072] Specifically, the servo motor 1 is an adjustable digital display motor. The motor speed and rotation time can be quantitatively controlled via a speed knob, precisely controlling the rotation torque to adapt to the break-in requirements of the booster pump sealing device under different conditions. Compared to manual rocker arm rotation, this greatly ensures the uniformity of the break-in speed and circumferential break-in stroke. When the rotating shaft 28 of the servo motor 1 is connected to the second bushing 31 on the diaphragm-type flexible coupling 3, the diaphragm-type flexible coupling 3 is inserted into the rotating shaft 28 of the servo motor 1, and the upper and lower halves of the second bushing 31 of the diaphragm-type flexible coupling 3 are locked onto the rotating shaft 28 via a third pin.

[0073] In some embodiments, the system further includes: a servo motor base 11, the lower end of which is fixed to the left end of the mounting plate 12, and a vertically arranged fixing plate at the right end of the servo motor base 11.

[0074] The lower end of the servo motor 1 housing is connected to the upper end of the servo motor base 11, and the right end of the servo motor 1 housing is connected to the fixing plate.

[0075] Specifically, the right end of the servo motor 1 housing is fixed to the mounting plate by multiple screws 2 (e.g., hex socket head cap screws 2).

[0076] In some embodiments, it further includes: a simulated pressure sleeve 7, which is sleeved on the drive shaft extending from the right end of the booster pump bearing housing to be repaired.

[0077] Specifically, refer to Figure 8 The main function of the simulated pressure sleeve 7 is to protect the drive shaft exposed outside the bearing housing of the booster pump. The simulated pressure sleeve 7 is directly fitted onto the drive shaft of the booster pump to prevent the drive shaft from being damaged during rotation.

[0078] In some embodiments, it also includes:

[0079] A baffle support 20 is provided on one side of the diaphragm type flexible coupling 3. The lower end of the baffle support 20 is connected to the mounting plate 12. The upper end of the baffle support 20 is provided with a baffle pin 23. Both the left and right ends of the baffle pin 23 are rotatably connected to the upper end of the baffle support 20. A baffle clamp 22 is provided in the middle of the baffle pin 23.

[0080] Baffle 21, the upper end of which is connected to baffle clamp 22, is used to protect the safe operation of the diaphragm type flexible coupling 3, pin shaft assembly 4, and spline shaft connector 5 that are covered by baffle 21.

[0081] The lower end of the baffle bracket 9 is connected to the mounting plate 12, and the upper end of the baffle bracket 9 is connected to the lower end of the baffle 21.

[0082] Specifically, the lower end of the baffle support 20 is connected to the mounting plate 12 by a hexagonal head bolt 19.

[0083] In some embodiments, the device further includes a first pin 6, which passes through the pin hole and a through hole in the sealing housing of the sealing device to fix the sealing device to the second support piece 14.

[0084] In some embodiments, the mounting plate 12 is further comprising: handles 10, wherein there are two handles 10, which are respectively disposed at both ends of the mounting plate 12.

[0085] In some embodiments, the system further includes a switch base 17, wherein a switch disposed in the switch base 17 is electrically connected to the servo motor 1 and is used to control the start and stop of the servo motor 1.

[0086] In some embodiments, the system further includes a power switch indicator light 18, which is electrically connected to a switch disposed in the switch holder 17 and is used to indicate the opening and closing of the switch.

[0087] In summary, compared with existing technologies, the method provided by the above technical solution can effectively improve the running-in degree of the contact sealing surfaces of the dynamic ring and graphite ring without affecting the assembly of the sealing device. It reduces dimensional and positional tolerances caused by machining and the perpendicularity error between the dynamic ring plane and the theoretical axis caused during operation, thereby improving the sealing performance of the sealing device. Simultaneously, by quantitatively controlling the speed, speed uniformity, and circumferential running-in stroke of the servo motor 1, automated and precise repair of the sealing device components is achieved, ensuring the running-in degree between the dynamic ring and graphite ring, reducing maintenance costs, improving the repair efficiency of the sealing device, and thus enhancing the repair quality of the sealing device and preventing oil leakage during the use of the booster pump. By using the running-in device designed to eliminate oil leakage in the sealing device of the aero-engine booster pump, the mutual running-in action of the two contact sealing surfaces can be used to improve the fit at the sealing surface under simulated actual relative movement of the dynamic ring and graphite ring, and to inspect the running-in marks and sealing performance of the dynamic ring base. Furthermore, this method also includes the development of running-in tools and the improvement of running-in methods to ensure running-in efficiency and improve the repair quality of the sealing device. This method can eliminate oil leakage from the sealing device during the use of booster pumps, solve the problem of booster connection failure caused by oil leakage from the sealing device of a certain type of aero-engine, improve production efficiency and product quality, and ultimately achieve the effect of improving quality and efficiency.

[0088] Note that, unless otherwise explicitly stated, all features disclosed in this specification (including any appended claims, abstract, and drawings) may be replaced by alternative features for achieving the same, equivalent, or similar purpose. Therefore, unless explicitly stated otherwise, each disclosed feature is merely one example of a set of equivalent or similar features. Where used, "further," "preferably," "even further," and "more preferably" are simply starting points for describing another embodiment based on the foregoing embodiments, the combination of which with the foregoing embodiments constitutes the complete configuration of another embodiment. Any combination of several "further," "preferably," "even further," or "more preferably" settings following the same embodiment constitutes yet another embodiment.

[0089] In the implementation of functions and steps, the corresponding functions and steps in the various embodiments may occur in a different order than those shown. For example, two consecutive functions and steps may actually be executed or implemented substantially in parallel, and they may sometimes be executed or implemented in reverse order, depending on the functions involved.

[0090] Although this application has been described in detail above with general descriptions and specific embodiments, some modifications or improvements can be made to it, which will be obvious to those skilled in the art. Therefore, all such modifications or improvements made without departing from the spirit of this application fall within the scope of protection claimed in this application.

Claims

1. A method for troubleshooting oil leakage in the sealing device of an aero-engine afterburner pump, characterized in that, The method includes setting up a break-in device, which comprises: a mounting plate, a product support, a splined shaft connector, a diaphragm-type flexible coupling, and a servo motor. The product support is located at the right end of the mounting plate and is used to fix the booster pump bearing housing and sealing device to be repaired. The first connector on the splined shaft connector is connected to the splined shaft extending from the left end of the booster pump bearing housing to be repaired via a sleeve tooth connection. The right end of the diaphragm-type flexible coupling is connected to the splined shaft connector. The rotating shaft of the servo motor is connected to the left end of the diaphragm-type flexible coupling; The method for troubleshooting oil leakage in the afterburner pump sealing device of an aircraft engine using the aforementioned break-in device includes: Step 1) Place the booster pump bearing housing and sealing device assembly to be repaired on the product support. The splined shaft at one end of the booster pump bearing housing is connected to the diaphragm type flexible coupling through the first connector of the splined shaft connector. Step 2) By quantitatively controlling the speed, speed uniformity, and circumferential running-in stroke of the servo motor, the sealing device components can be automatically and precisely repaired.

2. The method for troubleshooting oil leakage in the afterburner pump sealing device of an aircraft engine according to claim 1, characterized in that, The method includes: A first support plate and a second support plate are provided on the product support, and the two ends of the booster pump bearing housing and the sealing device assembly to be repaired are placed on the first support plate and the second support plate respectively. The first and second support plates each have a semi-circular notch at their upper ends that couples with the outer ring of the booster pump bearing housing, and the second support plate has a pin hole.

3. The method for troubleshooting oil leakage in the afterburner pump sealing device of an aircraft engine according to claim 1, characterized in that, The method includes: A pin assembly is provided to connect the first bushing at the right end of the diaphragm-type flexible coupling to the spline shaft connector via the pin assembly.

4. The method for troubleshooting oil leakage in the afterburner pump sealing device of an aircraft engine according to claim 1, characterized in that, The method includes: The rotating shaft of the servo motor is connected to the second bushing located at the left end of the diaphragm-type flexible coupling.

5. The method for troubleshooting oil leakage in the afterburner pump sealing device of an aircraft engine according to claim 1, characterized in that, The method includes: A servo motor base is provided, and the lower end of the servo motor base is fixed to the left end of the mounting plate. A vertically installed fixing plate is provided on the right end of the servo motor base. The lower end of the servo motor housing is fixed to the upper end of the servo motor base, and the right end of the servo motor housing is fixed to the fixing plate.

6. The method for troubleshooting oil leakage in the afterburner pump sealing device of an aircraft engine according to claim 1, characterized in that, The method includes: A simulated pressure sleeve is installed, which is fitted onto the drive shaft extending from the right end of the booster pump bearing housing to be repaired.

7. The method for troubleshooting oil leakage in the afterburner pump sealing device of an aircraft engine according to claim 1, characterized in that, The method includes: A baffle support is provided, which is located on one side of the diaphragm type flexible coupling. The lower end of the baffle support is connected to the mounting plate, and the upper end of the baffle support is provided with a baffle pin. Both the left and right ends of the baffle pin are rotatably connected to the upper end of the baffle support, and a baffle clamp is provided in the middle of the baffle pin. A baffle is provided, the upper end of which is connected to the baffle clamp. A baffle bracket is provided, the lower end of which is connected to the mounting plate, and the upper end of which is connected to the lower end of the baffle.

8. The method for troubleshooting oil leakage in the afterburner pump sealing device of an aircraft engine according to claim 1, characterized in that, The method includes: A first pin is provided, which passes through the pin hole and the through hole opened on the sealing housing of the sealing device to fix the sealing device to the second support plate.

9. The method for troubleshooting oil leakage in the afterburner pump sealing device of an aircraft engine according to claim 1, characterized in that, The method includes: The mounting plate is provided with handles, two of which are located at opposite ends of the mounting plate.

10. The method for troubleshooting oil leakage in the afterburner pump sealing device of an aircraft engine according to claim 1, characterized in that, The method includes: A switch holder is provided, and the switch in the switch holder is electrically connected to the servo motor for controlling the start and stop of the servo motor; A power switch indicator light is provided, which is electrically connected to the switch provided in the switch socket, and is used to indicate whether the switch is open or closed.

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