Aero-engine borescope detection training platform and detection method

Abstract

The invention relates to the technical field of aviation simulation teaching, and discloses an aero-engine borescope detection training platform and a detection method.The platform comprises an operation platform and an operation underframe which are connected with each other, the operation platform is provided with a plurality of borescope detection ports, and a plurality of operation areas are arranged in the operation platform; the plurality of operation areas at least comprise an operation area I, an operation area II and an operation area III, and the borescope detection ports are respectively communicated with the corresponding operation areas; a bulkhead assembly is arranged in the second operation area and is used for simulating defects in the aero-engine; an aero-engine compressor blade assembly is arranged in the first operation area and used for simulating blade defects; a combustion chamber assembly is arranged in the third operation area and used for simulating defects in the combustion chamber. According to the technical scheme provided by the invention, real operation is carried out on defects in an aero-engine, defects of blades and defects in a combustion chamber through the borescope detection port, and the real operation requirement is met in multiple detection areas.

Description

Technical Field

[0001] The invention relates to the technical field of aviation simulation teaching, and in particular to an aviation engine borescope detection training platform and a detection method. Background Art

[0002] An aircraft engine is a highly complex and sophisticated thermal machine. As the heart of an aircraft, it is not only the driving force for the aircraft to fly, but also an important driving force for the development of the aviation industry. Every important change in human aviation history is closely related to the technological progress of aircraft engines.

[0003] The development of aviation engines is accelerating, which will bring new and significant changes to the human aviation field. Traditional aviation engines are developing towards geared engines, variable cycle engines, multi-electric engines, intercooled regenerative engines and open rotor engines. Non-traditional pulse detonation engines, scramjet engines, turbine-based combined engines, as well as solar power and fuel cell power are also maturing. The development of these engines will make future aircraft faster, higher, farther, more economical, more reliable, and able to meet more stringent environmental protection requirements. It will also make hypersonic aircraft, trans-atmospheric aircraft and reusable earth-to-space round-trip transportation a reality.

[0004] Aircraft engine borescope inspection training usually adopts two training methods: actual carrier training and simulated operation platform training. Actual carrier training requires maintenance personnel to operate and practice various subjects on real aircraft; simulated operation platform training only requires maintenance personnel to operate and practice on simulated operation platform. Real aviation equipment requires high precision, and due to the special location during operation, different detection methods need to be implemented on different aircraft engines. The current training operation is relatively simple, mainly simulating the operation of some existing replaced engines. This operation platform cannot meet the requirements of real operation training and cannot truly simulate the detection methods of various detection areas on different aircraft engines. Summary of the invention

[0005] The main purpose of the present invention is to provide an aircraft engine borescope detection training platform and detection method, aiming to solve the problem that the existing simulation operation platform cannot meet the actual practical operation needs.

[0006] To achieve the above purpose, the technical solution proposed by the present invention is:

[0007] An aircraft engine borescope inspection training platform comprises an operating platform and an operating chassis connected to each other, wherein the operating platform is provided with a plurality of borescope inspection ports, and a plurality of operating areas are arranged in the operating platform, wherein the plurality of operating areas at least comprise an operating area 1, an operating area 2 and an operating area 3, and each of the borescope inspection ports is respectively connected to a corresponding operating area; a bulkhead assembly is arranged in the operating area 2, and the bulkhead assembly is used to simulate defects in the aircraft engine; an aircraft engine compressor blade assembly is arranged in the operating area 1, and the aircraft engine compressor blade assembly is used to simulate blade defects; a combustion chamber assembly is arranged in the operating area 3, and the combustion chamber assembly is used to simulate defects in the combustion chamber.

[0008] Preferably, the operating platform includes a barrel outer frame, the operating zone one, the operating zone two and the operating zone three are all arranged in the barrel outer frame, the operating zone one, the operating zone two and the operating zone three are arranged in sequence along the axial direction of the barrel outer frame, the aircraft engine compressor blade assembly is arranged in the operating zone one, the bulkhead assembly is arranged in the operating zone two, and the combustion chamber assembly is arranged in the operating zone three.

[0009] Preferably, the bulkhead assembly includes a plurality of baffles which are sequentially arranged axially along the inner frame of the cylinder body, the baffles are staggered, and each baffle has a detection channel; each baffle is respectively provided with a first trace layer; the first trace layer includes at least one of an oil leakage layer, a crack layer and a corrosion layer.

[0010] Preferably, the aircraft engine compressor blade assembly includes a fairing, a rotating shaft, a bearing seat and at least one blade group, the fairing and the bearing seat are both arranged at one end of the cylinder outer frame close to the operating area, and the bearing seat is arranged in the fairing; the rotating shaft drives and connects each blade group respectively, one end of the rotating shaft passes through the cylinder outer frame and the fairing in sequence, and the bearing seat is sleeved on the rotating shaft.

[0011] Preferably, a reducer is arranged between the rotating shaft and each of the blade groups; the blade group includes blades and a hollow drum, the blades are connected to the hollow drum, and the rotating shaft is connected to each of the hollow drums through a reducer drive; the blades include at least one of a compressor blade, a turbine blade and a guide blade.

[0012] Preferably, the combustion chamber assembly includes a fixing frame and a plurality of flame tubes, each of the flame tubes is fixed in the third operation zone by the fixing frame, and a fuel nozzle is arranged on a side of each of the flame tubes facing the second operation zone.

[0013] Preferably, at least one second trace layer is provided on the outer wall surface of the flame tube and the outer wall surface of the fuel nozzle, and the second trace layer includes at least one of an ablation layer, a coating peeling layer, a crack layer and a carbon deposition layer.

[0014] Preferably, each of the borescope detection ports is provided with a detachable observation window.

[0015] An aircraft engine borescope detection method, the detection method using any of the above-mentioned aircraft engine borescope detection training platforms, the detection method comprising:

[0016] Obtain the operation area to be operated, and remove the observation window connected to the operation area to be operated;

[0017] Obtain a preset probe and preset brightness, and drive the preset probe at a preset speed through the borescope detection port with the observation window removed into the operation area to be operated;

[0018] When the operation area to be operated is the second operation area, the bending angles of the preset probes are adjusted in sequence according to the positions of the baffles, so that the preset probes can detect the first trace layers through the detection channels;

[0019] When the operation area to be operated is the first operation area, the bending angle of the preset probe is adjusted in sequence according to the arrangement direction of each blade, so that the preset probe can detect each blade; the single blade inspection process includes: moving the preset probe so that the current leaf in the blade enters the shooting range of the preset probe for detection; after the current leaf in the blade is detected, the preset probe is withdrawn from the first operation area, and then the blade is rotated by the rotating shaft so that the next leaf in the blade enters the shooting range of the preset probe, and the preset probe is moved into the first operation area to detect the next leaf in the blade that enters the shooting range, until the detection of each leaf in the blade is completed;

[0020] When the operation area to be operated is the first operation area, the bending angle of the preset probe is adjusted according to the position of the current blade, so that any leaf of the current blade is located within the shooting range of the preset probe, and then the current blade is driven to rotate through the rotating shaft to send each leaf of the blade into the shooting range in turn;

[0021] When the operation area to be operated is the first operation area, the guide tube is inserted and fixed according to the position of the current blade, and the preset probe adjusts the bending angle according to the guide tube so that any leaf of the current blade is located within the shooting range of the preset probe, and then the current blade is driven to rotate through the rotating shaft to drill each leaf of the blade into the shooting range in turn;

[0022] When the operation area to be operated is the third operation area, the bending angle of the preset probe is adjusted in sequence according to the position of each flame tube, so that the preset probe first detects the fuel nozzle of the flame tube according to the preset scanning width, and then checks the outer wall surface of the flame tube.

[0023] Compared with the prior art, the present invention has at least the following beneficial effects:

[0024] Through the borescope inspection port, practical operations are carried out on the defects in the aircraft engine simulated by the bulkhead assembly, the blade defects simulated by the aircraft engine compressor blade assembly, and the defects in the combustion chamber simulated by the combustion chamber assembly, achieving multiple inspection areas and meeting practical operation needs. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying creative work.

[0026] Figure 1 It is a structural schematic diagram of an embodiment of an aircraft engine borescope inspection training platform of the present invention;

[0027] Figure 2 It is a schematic diagram of the structure inside the operating platform;

[0028] Figure 3 This is a schematic diagram of the structure inside the operation zone 1;

[0029] Figure 4 This is a schematic diagram of the structure inside the second operation area;

[0030] Figure 5 It is a structural schematic diagram of the 3D perspective effect of the aviation engine borescope detection training platform of the present invention.

[0031] Description of Figure Numbers:

[0032] 1-operation platform; 11-operation chassis; 12-operation area 1; 13-operation area 2; 14-operation area 3; 15-borescope detection port; 16-observation window; 17-cylinder outer frame;

[0033] 2- bulkhead assembly; 21- baffle;

[0034] 3-aircraft engine compressor blade assembly; 31-rotating shaft; 32-fairing; 33-bearing seat; 34-blade; 35-hollow drum;

[0035] 4-combustion chamber assembly; 41-fixed frame; 42-flame tube; 43-fuel nozzle;

[0036] The realization of the purpose, functional features and advantages of the present invention will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0037] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0038] It should be noted that all directional indications in the embodiments of the present invention (such as up, down, left, right, front, back, etc.) are only used to explain the relative position relationship, movement status, etc. between the components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0039] In addition, in the present invention, descriptions such as "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" or "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0040] In the present invention, unless otherwise clearly specified and limited, the terms "connection", "fixation", etc. should be understood in a broad sense. For example, "fixation" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0041] In addition, the technical solutions between the various embodiments of the present invention can be combined with each other, but it must be based on the fact that ordinary technicians in the field can implement it. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0042] The present invention provides an aviation engine borescope detection training platform.

[0043] like Figures 1 to 5 The aircraft engine borescope inspection training platform shown in the figure includes an operation platform 1 and an operation chassis 11 connected to each other. The operation platform 1 is provided with a plurality of borescope inspection ports 15. A plurality of operation areas are arranged in the operation platform 1. The plurality of operation areas include at least an operation area 12, an operation area 2 13 and an operation area 3 14 ( Figure 2In the figure, the operation zone 12, the operation zone 2 13 and the operation zone 3 14 are outlined with corresponding wireframes, and each borescope detection port 15 is connected to the corresponding operation zone respectively; a bulkhead assembly 2 is arranged in the operation zone 2 13, and the bulkhead assembly 2 is used to simulate defects in an aircraft engine; an aircraft engine compressor blade assembly 3 is arranged in the operation zone 12, and the aircraft engine compressor blade assembly 3 is used to simulate blade 34 defects; a combustion chamber assembly 4 is arranged in the operation zone 3 14, and the combustion chamber assembly 4 is used to simulate defects in the combustion chamber.

[0044] Through the borescope inspection port 15, practical operations are carried out on the defects in the aircraft engine simulated by the bulkhead assembly 2, the defects in the blades 34 simulated by the aircraft engine compressor blade assembly 3, and the defects in the combustion chamber simulated by the combustion chamber assembly 4, respectively, to achieve multi-detection area simulation and meet the practical needs of training operations.

[0045] The operating platform 1 includes a barrel outer frame 17, and the operating zone 12, the operating zone 2, and the operating zone 3, 14 are all arranged in the barrel outer frame 17, and the axial direction of the barrel outer frame 17 is arranged along a set direction; the operating zone 12, the operating zone 2, and the operating zone 3, 14 are arranged in sequence along the axial direction of the barrel outer frame 17, the aircraft engine compressor blade assembly 3 is arranged in the operating zone 12, the bulkhead assembly 2 is arranged in the operating zone 2, 13, and the combustion chamber assembly 4 is arranged in the operating zone 3, 14.

[0046] The bulkhead assembly 2 includes a plurality of baffles 21 arranged in sequence along the axial direction of the outer frame 17 of the cylinder. The baffles 21 are arranged in a staggered manner, and each baffle 21 has a detection channel. Each baffle 21 has a first trace layer. The first trace layer includes at least one of an oil leakage layer, a crack layer, and a corrosion layer. The staggered arrangement of the baffles 21, combined with the detection channels opened on the baffles 21, is sufficient to simulate the complex environment inside the engine. Various types of first trace layers simulate the internal conditions of the engine to the greatest extent possible, improving the practical effect.

[0047] Specifically, a portion of the baffles 21 is perpendicular to the axial direction of the cylinder outer frame 17 , and another portion of the baffles 21 is parallel to the axial direction of the cylinder outer frame 17 .

[0048] Specifically, the inspection channel is a circular channel.

[0049] The aircraft engine compressor blade assembly 3 includes a fairing 32, a rotating shaft 31, a bearing seat 33 and at least one blade group. The fairing 32 and the bearing seat 33 are both arranged at one end of the cylinder outer frame 17 close to the operating area 12, and the bearing seat 33 is arranged in the fairing 32; the rotating shaft 31 drives and connects each blade group respectively, one end of the rotating shaft 31 passes through the cylinder outer frame 17 and the fairing 32 in sequence, and the bearing seat 33 is sleeved on the rotating shaft 31.

[0050] Specifically, a handle (not shown in the figure) is provided at one end of the rotating shaft 31 extending out of the outer frame 17 of the cylinder, and the trainee can adjust the rotation of the blade 34 by simply turning the handle.

[0051] A reducer (not shown in the figure) is arranged between the rotating shaft 31 and each blade group; the blade group includes blades 34 and hollow drums 35, the blades 34 are connected to the hollow drums 35, and the rotating shaft 31 is connected to each hollow drum 35 through the reducer drive; the blades 34 include at least one of compressor blades, turbine blades and guide blades. The coordination of the reducer and the hollow drum ensures that the blades 34 can be adjusted by a preset number of circles per rotation (for example, the blades 34 rotate half a circle for each rotation of the rotating shaft 31), which can not only facilitate the operation of the trainees, but also protect the blade group through standardized operation.

[0052] Specifically, the rotating shaft 31 is connected to the reduction assembly and each hollow drum 35 through a sleeve gear.

[0053] Specifically, two compressor blades, two turbine blades, three guide vanes and seven hollow drums 35 are arranged in the first operating zone 11 .

[0054] The combustion chamber assembly 4 includes a fixing frame 41 and a plurality of flame tubes 42 . Each flame tube 42 is fixed in the third operation zone 14 through the fixing frame 41 . A fuel nozzle 43 is arranged on a side of each flame tube 42 facing the second operation zone 13 .

[0055] At least one second trace layer is provided on the outer wall of the flame tube 42 and the outer wall of the fuel nozzle 43, and the second trace layer includes at least one of an ablation layer, a coating peeling layer, a crack layer and a carbon deposition layer. Different types of second trace layers can further simulate the real environment of the combustion chamber and improve the practical effect.

[0056] Each borehole detection port 15 is provided with a detachable observation window 16. The detachable observation window 16 can not only facilitate the trainees to observe the actual situation inside the barrel outer frame 17, but also play a sealing effect.

[0057] Specifically, the observation window 16 and the borescope detection port 15 are fixed by bolts.

[0058] The present invention also provides an aircraft engine borescope detection method, the detection method uses any of the above-mentioned aircraft engine borescope detection training platforms, and the detection method includes:

[0059] Obtain the operation area to be operated, and remove the observation window 16 connected to the operation area to be operated;

[0060] Specifically, select a disassembly tool (i.e., a screwdriver or other tool of the corresponding size of the fixing screw) to unscrew the fixing screw of the observation window 16 and remove the observation window 16. After checking the overall integrity of the operating platform 1 and ensuring that it is correct, use a flashlight to observe the inside of the barrel outer frame 17 through the borescope detection port 15 where the observation window 16 is removed to prevent the presence of excess objects.

[0061] Get the preset probe, drive the preset probe at the preset speed to maintain the preset brightness, and enter the operation area to be operated by removing the borescope detection port 15 of the observation window 16;

[0062] Maintain the preset brightness so that the preset probe can obtain a clear field of view, and adjust the joystick to make the preset probe in a straight state before controlling the preset probe to pass through the borescope detection port 15 with the observation window 16 removed to enter the operation area to be operated.

[0063] Specifically, the preset speed is a preset probe movement speed less than or equal to 10 mm / s.

[0064] When the operation area to be operated is the second operation area 13, the bending angle of the preset probe is adjusted in sequence according to the position of each baffle 21, so that the preset probe can detect each first trace layer through each detection channel;

[0065] When the operation area to be operated is the first operation area 12, the bending angle of the preset probe is adjusted in sequence according to the arrangement direction of each blade 34, so that the preset probe can detect each blade 34; wherein, the inspection process of a single blade 34 includes: moving the preset probe so that the current blade of the blade 34 enters the shooting range of the preset probe for detection; after the detection of the current blade of the blade 34 is completed, the preset probe is withdrawn from the first operation area 12, and then the blade 34 is rotated by the rotating shaft 31 so that the next blade of the blade 34 enters the shooting range of the preset probe, and the preset probe is moved into the first operation area 12 to detect the next blade of the blade 34 that enters the shooting range, until the detection of each blade of the blade 34 is completed;

[0066] When the operation area to be operated is the first operation area 12, the bending angle of the preset probe is adjusted according to the position of the current blade 34, so that any leaf of the current blade 34 is located within the shooting range of the preset probe, and then the current blade 34 is driven to rotate through the rotating shaft 31, and each leaf of the blade 34 is sequentially sent into the shooting range;

[0067] When the operation area to be operated is the first operation area 12, the guide tube is inserted and fixed according to the position of the current blade 34, and the preset probe adjusts the bending angle according to the guide tube so that any leaf of the current blade 34 is located within the shooting range of the preset probe, and then the current blade 34 is driven to rotate through the rotating shaft 31, so that each leaf of the blade 34 is sequentially within the shooting range;

[0068] When the operation area to be operated is the third operation area 14, the bending angle of the preset probe is adjusted in sequence according to the position of each flame tube 42, so that the preset probe first detects the fuel nozzle 43 of the flame tube 42 according to the preset scanning width, and then checks the outer wall surface of the flame tube 42.

[0069] Specifically, the preset scanning width is 20 mm.

[0070] After the operation of the operation area to be operated is completed, the preset probe needs to be adjusted to a straight state and slowly withdrawn to the outside of the cylinder outer frame 17 through the borescope detection port 15. Then, the operation area 12, the operation area 2 13 and the operation area 3 14 are respectively checked through the borescope detection port 15 to see if there are any foreign objects left. After the inspection is completed, the observation window 16 is fixed to the corresponding borescope detection port 15 again through the fixing screws using the disassembly tool (i.e., a screwdriver with the corresponding fixing screw size).

[0071] Specifically, each preset probe is connected to the processing module for communication, so that the detection images captured by each preset probe are sent to the processing module for processing.

[0072] Furthermore, the processing module can also obtain the detection images taken by each preset probe at different time points during the detection process; calculate the positions of each preset probe at different time points in the detection process based on the detection images taken by the same preset probe at different time points in the detection process; establish the different positions of each preset probe at different time points in the detection process in the three-dimensional model of the training platform, so as to calculate the detection trajectory of the preset probe moving in the training platform; judge the standardization and proficiency of the operation in the test process according to the detection trajectory and the time point corresponding to each position point in the detection trajectory, so as to obtain the evaluation result of the detection training according to the change of the detection trajectory over time, so that the evaluation result of the entire training process can be obtained automatically.

[0073] Furthermore, the training platform may also be provided with a speed sensor for detecting the speed of the rotating shaft 31, and the speed sensor is communicatively connected with the processing module so that the processing module obtains the speed of the rotating shaft 31 at different time points;

[0074] Therefore, the processing module can also obtain the operation of the rotating shaft 31 during the detection training process according to the rotation speed of the rotating shaft 31 at different time points, so as to combine the detection trajectory and the time point corresponding to each position point in the detection trajectory to obtain the evaluation results during the detection training process.

[0075] The technical solution of the present invention realizes borescope detection of fault phenomena such as oil leakage, corrosion, ablation, coating shedding, cracks, carbon deposition, etc. in complex internal environments such as narrow and obstructed multi-detection areas; realizes a basic understanding of the operations of trainees, improves the actual teaching efficiency of the simulation training system, and achieves accuracy of simulation operations close to actual operations.

[0076] The above description is only a preferred embodiment of the present invention, and does not limit the patent scope of the present invention. All equivalent structural changes made by using the contents of the present invention specification and drawings under the inventive concept of the present invention, or directly / indirectly applied in other related technical fields are included in the patent protection scope of the present invention.

Claims

1. Aircraft engine borescope inspection training platform, characterized by: It comprises an operating platform and an operating chassis which are interconnected, wherein the operating platform is provided with a plurality of borescope inspection ports, and a plurality of operating areas are arranged in the operating platform, wherein the plurality of operating areas at least comprise a first operating area, a second operating area and a third operating area, and each of the borescope inspection ports is respectively connected to a corresponding operating area; a bulkhead assembly is arranged in the second operating area, and the bulkhead assembly is used to simulate defects in an aircraft engine; an aircraft engine compressor blade assembly is arranged in the first operating area, and the aircraft engine compressor blade assembly is used to simulate blade defects; a combustion chamber assembly is arranged in the third operating area, and the combustion chamber assembly is used to simulate defects in a combustion chamber.

2. The aircraft engine borescope inspection training platform according to claim 1, characterized in that: The operating platform includes a barrel outer frame, and the operating zone one, the operating zone two and the operating zone three are all arranged in the barrel outer frame. The operating zone one, the operating zone two and the operating zone three are arranged in sequence along the axial direction of the barrel outer frame. The aircraft engine compressor blade assembly is arranged in the operating zone one, the bulkhead assembly is arranged in the operating zone two, and the combustion chamber assembly is arranged in the operating zone three.

3. The aircraft engine borescope inspection training platform according to claim 2, characterized in that: The bulkhead assembly includes a plurality of baffles arranged in sequence along the axial direction inside the outer frame of the cylinder, the baffles are arranged in a staggered manner, and each baffle has a detection channel respectively; each baffle is provided with a first trace layer respectively; the first trace layer includes at least one of an oil leakage layer, a crack layer and a corrosion layer.

4. The aircraft engine borescope inspection training platform according to claim 2 or 3, characterized in that: The aircraft engine compressor blade assembly includes a fairing, a rotating shaft, a bearing seat and at least one blade group. The fairing and the bearing seat are both arranged at one end of the cylinder outer frame close to the operating area, and the bearing seat is arranged in the fairing; the rotating shaft drives and connects each blade group respectively, one end of the rotating shaft passes through the cylinder outer frame and the fairing in sequence, and the bearing seat is sleeved on the rotating shaft.

5. The aircraft engine borescope inspection training platform according to claim 4, characterized in that: A reducer is arranged between the rotating shaft and each of the blade groups; the blade group includes blades and a hollow drum, the blades are connected to the hollow drum, and the rotating shaft is connected to each of the hollow drums through a reducer drive; the blades include at least one of a compressor blade, a turbine blade and a guide blade.

6. The aircraft engine borescope inspection training platform according to claim 2 or 3, characterized in that: The combustion chamber assembly includes a fixing frame and a plurality of flame tubes. Each of the flame tubes is fixed in the third operation zone through the fixing frame. A fuel nozzle is arranged on a side of each of the flame tubes facing the second operation zone.

7. The aircraft engine borescope inspection training platform according to claim 6, characterized in that: At least one second trace layer is provided on the outer wall surface of the flame tube and the outer wall surface of the fuel nozzle, and the second trace layer includes at least one of an ablation layer, a coating peeling layer, a crack layer and a carbon deposition layer.

8. The aircraft engine borescope inspection training platform according to any one of claims 1 to 3, characterized in that: Each of the borescope detection ports is provided with a detachable observation window.

9. An aircraft engine borescope inspection method, the inspection method using the aircraft engine borescope inspection training platform described in any one of claims 1 to 8, characterized in that: The detection method comprises: Obtain the operation area to be operated, and remove the observation window connected to the operation area to be operated; Obtain a preset probe and preset brightness, and drive the preset probe at a preset speed through the borescope detection port with the observation window removed into the operation area to be operated; When the operation area to be operated is the second operation area, the bending angles of the preset probes are adjusted in sequence according to the positions of the baffles, so that the preset probes can detect the first trace layers through the detection channels; When the operation area to be operated is the first operation area, the bending angle of the preset probe is adjusted in sequence according to the arrangement direction of each blade, so that the preset probe can detect each blade; the single blade inspection process includes: moving the preset probe so that the current leaf in the blade enters the shooting range of the preset probe for detection; after the current leaf in the blade is detected, the preset probe is withdrawn from the first operation area, and then the blade is rotated by the rotating shaft so that the next leaf in the blade enters the shooting range of the preset probe, and the preset probe is moved into the first operation area to detect the next leaf in the blade that enters the shooting range, until the detection of each leaf in the blade is completed; When the operation area to be operated is the first operation area, the bending angle of the preset probe is adjusted according to the position of the current blade, so that any leaf of the current blade is located within the shooting range of the preset probe, and then the current blade is driven to rotate through the rotating shaft to send each leaf of the blade into the shooting range in turn; When the operation area to be operated is the first operation area, the guide tube is inserted and fixed according to the position of the current blade, and the preset probe adjusts the bending angle according to the guide tube so that any leaf of the current blade is located within the shooting range of the preset probe, and then the current blade is driven to rotate through the rotating shaft to drill each leaf of the blade into the shooting range in turn; When the operation area to be operated is the third operation area, the bending angle of the preset probe is adjusted in sequence according to the position of each flame tube, so that the preset probe first detects the fuel nozzle of the flame tube according to the preset scanning width, and then checks the outer wall surface of the flame tube.

Images