Aeroengine bore probe test simulation tester

Abstract

The application discloses an aero-engine bore-scope test simulation tester, which comprises a driving motor, a motor support, a nylon shaft coupling, a test module, a test support and a base; the test module comprises a casing, a rotating shaft, a flange plate, a compressor blade disc, a compressor stator blade disc, a compressor stator bearing, a turbine blade disc, a turbine stator blade disc and a turbine stator bearing. The application can satisfy the internal damage pre-preparation and bore-scope simulation test of the aero-engine, is beneficial to the development and test of the bore-scope test equipment and secondary development, and provides test data for automatic identification of defects based on bore-scope images.

Description

TECHNICAL FIELD

[0001] The present application relates to aero-engine bore test, realizes aero-engine bore test experiment, and comprehensively develops and improves existing aero-engine bore test technology. BACKGROUND

[0002] An aero-engine is the main power source for a plane to fly. Since it works in a high-temperature, high-pressure and high-vibration environment for a long time, and a high-bypass-ratio turbofan engine is prone to sucking in stones, parts left by a plane, birds and other foreign objects near a runway and taxiway during the process of takeoff, landing and taxiing of the plane, the aero-engine is prone to failure. Severe engine failure will cause engine surge or parking in the air, which greatly threatens flight safety. Regular inspection of the engine or visual maintenance after an emergency can ensure the continuous airworthiness of the plane, improve the daily utilization rate of the plane, save maintenance costs, and increase the economic benefits of an airline. Internal component and structural damage is an important cause of failure of the aero-engine, and internal damage of the engine is usually detected by a non-destructive testing method. Common non-destructive testing methods include magnetic powder detection, penetration detection, eddy current detection, ultrasonic detection, ray detection and bore test (endoscopy). The bore test is the most widely used non-destructive testing method in the maintenance of the aero-engine at present due to its rapidity and convenience, and scholars at home and abroad have also conducted in-depth research on the bore test technology. However, the research results are difficult to apply to engineering practice. An important reason is the lack of corresponding aero-engine bore test verification. A real aero-engine is expensive and its core engine is difficult to disassemble and customize, so it is extremely important to design and manufacture an aero-engine simulation tester capable of meeting the bore test research. However, the existing aero-engine bore test research devices generally have one or several of the following deficiencies: no casing, only engine rotor part or no stator blade part; no real aero-engine core engine basic structure, only simple structure such as a blade disc; integration of the blade and the blade disc, which cannot replace and preform defects on the blade; position limitation between the casing and the rotor, which is not convenient for bore test equipment to take pictures for bore test, etc. SUMMARY

[0003] The technical problem to be solved by the present application is to provide an aero-engine bore test simulation tester for solving the defects in the background art, which can perform internal damage bore test simulation of the aero-engine at a low rotating speed or in a hand-rotating state.

[0004] The present application adopts the following technical solutions to solve the above technical problems:

[0005] An aero-engine bore test simulation tester, comprising a driving motor, a motor support, a nylon shaft coupling, a test module, a test support and a base.

[0006] The test module comprises a casing, a rotating shaft, a flange, a compressor blade disc, a compressor stator blade disc, a compressor stator bearing, a turbine blade disc, a turbine stator blade disc and a turbine stator bearing;

[0007] The casing is an axisymmetric hollow variable cross-section cylinder with both ends open;

[0008] The compressor blade disc comprises a compressor rotating disc and a plurality of compressor blades; the center of the compressor rotating disc is provided with a first mounting hole matched with the rotating shaft; the compressor rotating disc is coaxially fixed with the rotating shaft through the first mounting hole; the plurality of compressor blades are uniformly arranged on the outer wall of the compressor rotating disc in the circumferential direction, and the roots of the compressor blades are detachably fixed with the outer wall of the compressor rotating disc;

[0009] The compressor stator blade disc comprises a compressor stator rotating disc and a plurality of compressor stator blades; the center of the compressor stator rotating disc is provided with a second mounting hole matched with the compressor stator bearing; the compressor stator rotating disc is coaxially fixed with the outer ring of the compressor stator bearing through the second mounting hole, and the inner ring of the compressor stator bearing is coaxially fixed with the rotating shaft; the plurality of compressor stator blades are uniformly arranged on the outer wall of the compressor stator rotating disc in the circumferential direction, and the roots of the compressor stator blades are detachably fixed with the outer wall of the compressor stator rotating disc, and the tips of the compressor stator blades are detachably fixed with the inner wall of the casing, so that the casing and the compressor stator rotating disc are coaxial;

[0010] The turbine blade disc comprises a turbine rotating disc and a plurality of turbine blades; the center of the turbine rotating disc is provided with a first mounting hole matched with the rotating shaft; the turbine rotating disc is coaxially fixed with the rotating shaft through the first mounting hole; the plurality of turbine blades are uniformly arranged on the outer wall of the turbine rotating disc in the circumferential direction, and the roots of the turbine blades are detachably fixed with the outer wall of the turbine rotating disc;

[0011] The turbine stator blade disc comprises a turbine stator rotating disc and a plurality of turbine stator blades; the center of the turbine stator rotating disc is provided with a second mounting hole matched with the turbine stator bearing; the turbine stator rotating disc is coaxially fixed with the outer ring of the turbine stator bearing through the second mounting hole, and the inner ring of the turbine stator bearing is coaxially fixed with the rotating shaft; the plurality of turbine stator blades are uniformly arranged on the outer wall of the turbine stator rotating disc in the circumferential direction, and the roots of the turbine stator blades are detachably fixed with the outer wall of the turbine stator rotating disc, and the tips of the turbine stator blades are detachably fixed with the inner wall of the casing, so that the casing and the turbine stator rotating disc are coaxial;

[0012] The casing is provided with at least one viewing hole for the endoscope to insert the probe at the corresponding positions of the compressor blade disc, the compressor stator blade disc, the turbine blade disc and the turbine stator blade disc;

[0013] The flange is coaxially fixed with one end of the rotating shaft;

[0014] The test module is fixed on the base through the test support;

[0015] The driving motor is fixed on the base through the motor support, and the output shaft is coaxially connected with the flange plate through the nylon shaft coupling.

[0016] As a further optimization scheme of the aero-engine bore test simulation tester, the test module is provided with four bore holes for the endoscope to insert the probe into at the corresponding positions of the compressor disc, the compressor stator disc, the turbine disc and the turbine stator disc.

[0017] Compared with the prior art, the aero-engine bore test simulation tester has the following technical effects:

[0018] The aero-engine bore test simulation tester with a similar structure of an aero-engine core engine is constructed, and the test module, the compressor disc, the compressor stator disc, the turbine disc and the turbine stator disc are provided, so that the bore test can be conveniently performed. BRIEF DESCRIPTION OF DRAWINGS

[0019] Figure 1 is a structural schematic diagram of the present application;

[0020] Figure 2 is a sectional view of the present application;

[0021] Figure 3 is a structural schematic diagram of the test module and the probe of the endoscope in the present application.

[0022] In the figure, 1 is a driving motor, 2 is a motor support, 3 is a nylon shaft coupling, 4 is a test module, 5 is a test support, 6 is a base, 7 is a test module, 8 is a shaft, 9 is a compressor disc, 10 is a compressor blade, 11 is a compressor stator disc, 12 is a compressor stator blade, 13 is a compressor stator bearing, 14 is a turbine disc, 15 is a turbine blade, 16 is a turbine stator disc, 17 is a turbine stator blade, 18 is a turbine stator bearing, 19 is a flange plate, and 20 is a probe of an endoscope. DETAILED DESCRIPTION

[0023] The technical scheme of the present application will be further described in detail below with reference to the accompanying drawings:

[0024] The application can be implemented in many different forms and should not be considered limited to the embodiments described herein. Rather, these embodiments are provided so that the disclosure will be thorough and complete, and will fully convey the scope of the application to those skilled in the art.

[0025] As shown in Figure 1 The application discloses an aero-engine borescope test simulation tester, comprising a driving motor, a motor support, a nylon shaft coupling, a test module, a test support and a base;

[0026] As shown in Figure 2 The test module comprises a casing, a rotating shaft, a flange plate, a compressor blade disc, a compressor stator blade disc, a compressor stator bearing, a turbine blade disc, a turbine stator blade disc and a turbine stator bearing;

[0027] The casing is a hollow variable cross-section cylinder with open ends and axial symmetry;

[0028] The compressor blade disc comprises a compressor rotating disc and a plurality of compressor blades; the center of the compressor rotating disc is provided with a first mounting hole matched with the rotating shaft; the compressor rotating disc is coaxially fixed with the rotating shaft through the first mounting hole; the plurality of compressor blades are uniformly arranged on the outer wall of the compressor rotating disc in a circumferential direction, and the roots of the compressor blades are detachably fixed with the outer wall of the compressor rotating disc;

[0029] The compressor stator blade disc comprises a compressor stator rotating disc and a plurality of compressor stator blades; the center of the compressor stator rotating disc is provided with a second mounting hole matched with the compressor stator bearing; the compressor stator rotating disc is coaxially fixed with the outer ring of the compressor stator bearing through the second mounting hole, and the inner ring of the compressor stator bearing is coaxially fixed with the rotating shaft; the plurality of compressor stator blades are uniformly arranged on the outer wall of the compressor stator rotating disc in a circumferential direction, the roots of the compressor stator blades are detachably fixed with the outer wall of the compressor stator rotating disc, and the tips of the compressor stator blades are detachably fixed with the inner wall of the casing, so that the casing and the compressor stator rotating disc are coaxial;

[0030] The turbine blade disc comprises a turbine rotating disc and a plurality of turbine blades; the center of the turbine rotating disc is provided with a first mounting hole matched with the rotating shaft; the turbine rotating disc is coaxially fixed with the rotating shaft through the first mounting hole; the plurality of turbine blades are uniformly arranged on the outer wall of the turbine rotating disc in a circumferential direction, and the roots of the turbine blades are detachably fixed with the outer wall of the turbine rotating disc;

[0031] The turbine stator blade disc comprises a turbine stator rotating disc and a plurality of turbine stator blades; the center of the turbine stator rotating disc is provided with a second mounting hole matched with a turbine stator bearing; the turbine stator rotating disc is coaxially fixed with the outer ring of the turbine stator bearing through the second mounting hole thereof, and the inner ring of the turbine stator bearing is coaxially fixed with the rotating shaft; the plurality of turbine stator blades are circumferentially and uniformly arranged on the outer wall of the turbine stator rotating disc, the roots of the turbine stator blades are detachably fixed with the outer wall of the turbine stator rotating disc, and the tips of the turbine stator blades are detachably fixed with the inner wall of the casing, so that the casing and the turbine stator rotating disc are coaxial.

[0032] The casing is provided with at least one viewing hole for the endoscope to insert a probe at the corresponding position of the compressor blade disc, the compressor stator blade disc, the turbine blade disc and the turbine stator blade disc. Figure 3

[0033] The flange plate is coaxially fixed with one end of the rotating shaft.

[0034] The casing is fixed on the base through the test support.

[0035] The driving motor is fixed on the base through the motor support, and the output shaft thereof is coaxially fixed with the flange plate through the nylon coupling.

[0036] The casing is circumferentially and uniformly provided with four viewing holes for the endoscope to insert a probe at the corresponding position of the compressor blade disc, the compressor stator blade disc, the turbine blade disc and the turbine stator blade disc.

[0037] Those skilled in the art can understand that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. It should also be understood that terms such as those defined in general dictionaries should be understood to have meanings consistent with those in the context of the prior art, and should not be interpreted in an idealized or overly formal sense unless otherwise defined.

[0038] The above specific embodiments further illustrate the purposes, technical solutions and beneficial effects of the present application. It should be understood that the above description is only a specific embodiment of the present application and is not used to limit the present application. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the protection scope of the present application.​

Claims

1. An aeroengine bore-scope test simulator, characterised in that, It comprises a driving motor, a motor support, a nylon coupling, a test module, a test support and a base; The test module comprises a casing, a rotating shaft, a flange, a compressor disc, a compressor stator disc, a compressor stator bearing, a turbine disc, a turbine stator disc and a turbine stator bearing; The casing is an axisymmetric hollow variable cross-section cylinder with both ends open; The compressor disc comprises a compressor rotating disc and a plurality of compressor blades; the center of the compressor rotating disc is provided with a first mounting hole matched with the rotating shaft; the compressor rotating disc is coaxially fixed with the rotating shaft through the first mounting hole; the plurality of compressor blades are uniformly arranged on the outer wall of the compressor rotating disc in the circumferential direction, and the roots of the compressor blades are detachably fixed with the outer wall of the compressor rotating disc; The compressor stator disc comprises a compressor stator rotating disc and a plurality of compressor stator blades; the center of the compressor stator rotating disc is provided with a second mounting hole matched with the compressor stator bearing; the compressor stator rotating disc is coaxially fixed with the outer ring of the compressor stator bearing through the second mounting hole, and the inner ring of the compressor stator bearing is coaxially fixed with the rotating shaft; the plurality of compressor stator blades are uniformly arranged on the outer wall of the compressor stator rotating disc in the circumferential direction, and the roots of the compressor stator blades are detachably fixed with the outer wall of the compressor stator rotating disc, and the tips of the compressor stator blades are detachably fixed with the inner wall of the casing, so that the casing and the compressor stator rotating disc are coaxial; The turbine disc comprises a turbine rotating disc and a plurality of turbine blades; the center of the turbine rotating disc is provided with a first mounting hole matched with the rotating shaft; the turbine rotating disc is coaxially fixed with the rotating shaft through the first mounting hole; the plurality of turbine blades are uniformly arranged on the outer wall of the turbine rotating disc in the circumferential direction, and the roots of the turbine blades are detachably fixed with the outer wall of the turbine rotating disc; The turbine stator disc comprises a turbine stator rotating disc and a plurality of turbine stator blades; the center of the turbine stator rotating disc is provided with a second mounting hole matched with the turbine stator bearing; the turbine stator rotating disc is coaxially fixed with the outer ring of the turbine stator bearing through the second mounting hole, and the inner ring of the turbine stator bearing is coaxially fixed with the rotating shaft; the plurality of turbine stator blades are uniformly arranged on the outer wall of the turbine stator rotating disc in the circumferential direction, and the roots of the turbine stator blades are detachably fixed with the outer wall of the turbine stator rotating disc, and the tips of the turbine stator blades are detachably fixed with the inner wall of the casing, so that the casing and the turbine stator rotating disc are coaxial; The casing is provided with at least one viewing hole for the endoscope to insert the probe at the corresponding position of the compressor disc, the compressor stator disc, the turbine disc and the turbine stator disc; The flange is coaxially fixed with one end of the rotating shaft; The casing is fixed on the base through the test support; The driving motor is fixed on the base through the motor support, and the output shaft of the driving motor is coaxially fixed with the flange through the nylon coupling.

2. The aeroengine bore-seeing test analog tester of claim 1, wherein, The casing is provided with four viewing holes for the endoscope to insert the probe at the corresponding position of the compressor disc, the compressor stator disc, the turbine disc and the turbine stator disc.

Images