CN116818340A - Aeroengine hole detection test simulation tester - Google Patents

Abstract

The invention discloses an aerospace engine borehole testing simulation tester, which includes a drive motor, a motor bracket, a nylon coupling, a test module, a test bracket and a base; the test module includes a casing, a rotating shaft, a flange, and a compressor blade. Disc, compressor stator blisk, compressor stator bearing, turbine blisk, turbine stator blisk and turbine stator bearing. The invention can meet the needs of aeroengine internal damage prefabrication and borehole simulation testing, is beneficial to the development, testing and secondary development of borehole testing equipment, and provides test data for automatic defect identification based on borehole images.

Description

An aerospace engine borehole testing simulation tester

Technical field

The invention relates to aeroengine borescope testing, realizes aeroengine borescope testing, and comprehensively develops and improves existing aeroengine borescope measurement technology.

Background technique

Aviation engines are the main source of power for aircraft flight. Because they work in high temperature, high pressure, and high vibration working environments for a long time, and high bypass ratio turbofan engines are easily sucked into the vicinity of runways and taxiways during takeoff, landing, and taxiing. Foreign objects such as stones, leftover aircraft parts, and birds make aircraft engines prone to failure. Serious engine failure will cause engine surge or stop in the air, posing a great threat to flight safety. Regular engine inspections or condition-specific maintenance after emergencies can ensure the continued airworthiness of the aircraft, improve the daily utilization of the aircraft, save maintenance costs, and increase the economic benefits of the airline. Damage to internal components and structures is an important cause of aircraft engine failure. Internal damage to engines is usually detected using non-destructive testing methods. Commonly used non-destructive testing methods include magnetic particle testing, penetrant testing, eddy current testing, ultrasonic testing, radiographic testing and borehole testing (endoscopic testing). microscopic examination). Because of its rapidity and convenience, borehole exploration is currently the most widely used non-destructive testing method in aircraft engine maintenance. Domestic and foreign scholars have also conducted in-depth research on borehole exploration technology, but the research results are difficult to apply to engineering practice. One of the important reasons is the lack of corresponding aerospace engine borehole test verification. Real aeroengines are extremely expensive and the internal core machine is difficult to disassemble and customize. Therefore, an aerospace engine simulation tester that can meet the needs of borehole test research is designed and manufactured. Extremely important. However, the existing aero-engine borehole testing and research devices generally have the following shortcomings: they do not have a casing, only the engine rotor part or no stator blade part; they do not have the basic structure of a real aero-engine core machine and only have blades. Simple structures such as discs; the blades and blisks are integrated, and the blades cannot be replaced and defects prefabricated well; the position between the casing and the rotor is limited, making it inconvenient for borehole exploration equipment to carry out borehole photography and testing.

Contents of the invention

The technical problem to be solved by the present invention is to provide an aerospace engine borehole testing simulation tester in view of the defects involved in the background technology, which can perform borehole testing for internal damage of the aeroengine at low speeds or in a hand-cranked rotation state. simulation.

The present invention adopts the following technical solutions to solve the above technical problems:

An aerospace engine borehole testing simulation tester, including a drive motor, a motor bracket, a nylon coupling, a test module, a test bracket and a base;

The test module includes a casing, a rotating shaft, a flange, a compressor blisk, a compressor stator blisk, a compressor stator bearing, a turbine blisk, a turbine stator blisk and a turbine stator bearing;

The casing is an axially symmetrical hollow variable-section cylinder with openings at both ends;

The compressor blisk includes a compressor turntable and a number of compressor blades; the center of the compressor turntable is provided with a first mounting hole that matches the rotating shaft; the compressor turntable passes through its first mounting hole and the rotating shaft Coaxially fixed; the plurality of compressor blades are evenly arranged on the outer wall of the compressor turntable in the circumferential direction, and their roots are detachably fixed to the outer wall of the compressor turntable;

The compressor stator blisk includes a compressor stator turntable and a plurality of compressor stator blades; the center of the compressor stator turntable is provided with a second mounting hole that matches the compressor stator bearing; the compressor stator turntable passes through its third Two mounting holes are coaxially connected to the outer ring of the compressor stator bearing, and the inner ring of the compressor stator bearing is coaxially connected to the rotating shaft; the plurality of compressor blades are evenly arranged on the compressor stator circumferentially. On the outer wall of the turntable, its roots are detachably fixed to the outer wall of the compressor stator turntable, and its tips are detachably fixed to the inner wall of the casing, so that the casing and the compressor stator turntable are coaxial;

The turbine blisk includes a turbine rotor and a plurality of turbine blades; the center of the turbine rotor is provided with a first mounting hole that matches the rotating shaft; the turbine rotor is coaxially connected to the rotating shaft through its first mounting hole; The plurality of turbine blades are evenly arranged on the outer wall of the turbine turntable in the circumferential direction, and their roots are detachably fixed to the outer wall of the turbine turntable;

The turbine stator blisk includes 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 that matches the turbine stator bearing; the turbine stator rotating disc passes through its second mounting hole and the The outer ring of the turbine stator bearing is coaxially connected, and the inner ring of the turbine stator bearing is coaxially connected to the rotating shaft; the plurality of turbine blades are evenly arranged on the outer wall of the turbine stator turntable in the circumferential direction, and their roots are evenly connected with the turbine stator. The outer wall of the stator turntable is removably fixed, and the tip is detachably fixed to the inner wall of the casing, so that the casing and the turbine stator turntable are coaxial;

The casing is provided with at least one peephole for an endoscope to extend a probe into at corresponding locations of the compressor blisk, compressor stator blisk, turbine blisk, and turbine stator blisk;

The flange is coaxially connected to one end of the rotating shaft;

The casing is fixed on the base through a test bracket;

The drive motor is fixed on the base through a motor bracket, and its output shaft is coaxially connected to the flange through the nylon coupling.

As a further optimization solution of the aeroengine borehole testing simulation tester of the present invention, the casing is evenly provided with circumferentially spaced holes at corresponding locations of the compressor blisk, compressor stator blisk, turbine blisk, and turbine stator blisk. Four peep holes for the endoscope to insert its probe.

Compared with the existing technology, the present invention adopts the above technical solution and has the following technical effects:

The invention constructs an aerospace engine borehole testing simulation tester with a similar structure to an aeroengine core machine. It has a casing, a compressor blisk, a compressor stator blisk, a turbine blisk, and a turbine stator blisk. It can be easily Convenient for borehole testing, the blades in the compressor blisk, compressor stator blisk, turbine blisk, and turbine stator blisk are all detachably matched with the turntable, making it easy to replace the blades and detect defects. Prefabricated. The invention can meet the needs of aeroengine internal damage prefabrication and borehole simulation testing, is beneficial to the development, testing and secondary development of borehole testing equipment, and provides test data for automatic defect identification based on borehole images.

Description of the drawings

Figure 1 is a schematic structural diagram of the present invention;

Figure 2 is a schematic cross-sectional structural diagram of the present invention;

Figure 3 is a schematic structural diagram of the cooperation between the test module and the probe of the endoscope in the present invention.

In the picture, 1-drive motor, 2-motor bracket, 3-nylon coupling, 4-test module, 5-test bracket, 6-base, 7-casing, 8-rotating shaft, 9-compressor turntable, 10 -Compressor blades, 11-Compressor stator blades, 12-Compressor stator blades, 13-Compressor stator bearings, 14-Turbine rotor blades, 15-Turbine blades, 16-Turbine stator blisks, 17-Turbine stator blades, 18 -Turbine stator bearing, 19-flange plate, 20-endoscope probe.

Implementation

The technical solution of the present invention will be further described in detail below in conjunction with the accompanying drawings:

The invention may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.

As shown in Figure 1, the present invention discloses an aerospace engine borehole testing simulation tester, which includes a drive motor, a motor bracket, a nylon coupling, a test module, a test bracket and a base;

As shown in Figure 2, the test module includes a casing, a rotating shaft, a flange, a compressor blisk, a compressor stator blisk, a compressor stator bearing, a turbine blisk, a turbine stator blisk and a turbine stator bearing;

The casing is an axially symmetrical hollow variable-section cylinder with openings at both ends;

The compressor blisk includes a compressor turntable and a number of compressor blades; the center of the compressor turntable is provided with a first mounting hole that matches the rotating shaft; the compressor turntable passes through its first mounting hole and the rotating shaft Coaxially fixed; the plurality of compressor blades are evenly arranged on the outer wall of the compressor turntable in the circumferential direction, and their roots are detachably fixed to the outer wall of the compressor turntable;

The compressor stator blisk includes a compressor stator turntable and a plurality of compressor stator blades; the center of the compressor stator turntable is provided with a second mounting hole that matches the compressor stator bearing; the compressor stator turntable passes through its third Two mounting holes are coaxially connected to the outer ring of the compressor stator bearing, and the inner ring of the compressor stator bearing is coaxially connected to the rotating shaft; the plurality of compressor blades are evenly arranged on the compressor stator circumferentially. On the outer wall of the turntable, its roots are detachably fixed to the outer wall of the compressor stator turntable, and its tips are detachably fixed to the inner wall of the casing, so that the casing and the compressor stator turntable are coaxial;

The turbine blisk includes a turbine rotor and a plurality of turbine blades; the center of the turbine rotor is provided with a first mounting hole that matches the rotating shaft; the turbine rotor is coaxially connected to the rotating shaft through its first mounting hole; The plurality of turbine blades are evenly arranged on the outer wall of the turbine turntable in the circumferential direction, and their roots are detachably fixed to the outer wall of the turbine turntable;

The turbine stator blisk includes 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 that matches the turbine stator bearing; the turbine stator rotating disc passes through its second mounting hole and the The outer ring of the turbine stator bearing is coaxially connected, and the inner ring of the turbine stator bearing is coaxially connected to the rotating shaft; the plurality of turbine blades are evenly arranged on the outer wall of the turbine stator turntable in the circumferential direction, and their roots are evenly connected with the turbine stator. The outer wall of the stator turntable is removably fixed, and the tip is detachably fixed to the inner wall of the casing, so that the casing and the turbine stator turntable are coaxial;

The casing is provided with at least one peephole for the endoscope to extend the probe into at the corresponding locations of the compressor blisk, compressor stator blisk, turbine blisk, and turbine stator blisk, as shown in Figure 3 ;

The flange is coaxially connected to one end of the rotating shaft;

The casing is fixed on the base through a test bracket;

The drive motor is fixed on the base through a motor bracket, and its output shaft is coaxially connected to the flange through the nylon coupling.

The casing is preferably provided with four peepholes for the endoscope to extend the probe into at the corresponding locations of the compressor blisk, compressor stator blisk, turbine blisk, and turbine stator blisk.

It can be understood by one of ordinary skill in the art 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 invention belongs. It should also be understood that terms such as those defined in general dictionaries are to be understood to have meanings consistent with their meaning in the context of the prior art, and are not to be taken in an idealized or overly formal sense unless defined as herein. explain.

The above-mentioned specific embodiments further describe the objectives, technical solutions and beneficial effects of the present invention in detail. It should be understood that the above-mentioned are only specific embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention shall be included in the protection scope of the present invention.

Claims (2)

1. The aeroengine hole detection test simulation tester is characterized by comprising a driving motor, a motor bracket, a nylon coupling, a test module, a test bracket and a base;

the test module comprises a casing, a rotating shaft, a flange plate, a compressor blade plate, a compressor stator bearing, a turbine blade plate, a turbine stator blade plate and a turbine stator bearing;

the casing is a hollow variable cross-section cylinder body with two open ends and axisymmetric;

the compressor blade disc comprises a compressor rotating disc and a plurality of compressor blades; the center of the compressor turntable is provided with a first mounting hole matched with the rotating shaft; the compressor turntable is coaxially and fixedly connected with the rotating shaft through a first mounting hole of the compressor turntable; the plurality of compressor blades are circumferentially and uniformly arranged on the outer wall of the compressor turntable, and the roots of the compressor blades are detachably and fixedly connected with the outer wall of the compressor turntable;

the compressor stator blade disc comprises a compressor stator rotating disc and a plurality of compressor stator blades; the center of the compressor stator turntable is provided with a second mounting hole matched with the compressor stator bearing; the compressor turntable is coaxially and fixedly connected with the outer ring of the compressor stator bearing through a second mounting hole of the compressor turntable, and the inner ring of the compressor stator bearing is coaxially and fixedly connected with the rotating shaft; the plurality of compressor blades are circumferentially and uniformly arranged on the outer wall of the compressor stator turntable, the root parts of the plurality of compressor blades are detachably fixedly connected with the outer wall of the compressor stator turntable, and the tip parts of the plurality of compressor blades are detachably fixedly connected with the inner wall of the casing, so that the casing and the compressor stator turntable are coaxial;

the turbine impeller comprises a turbine turntable and a plurality of turbine blades; the center of the turbine turntable is provided with a first mounting hole matched with the rotating shaft; the turbine turntable is coaxially and fixedly connected with the rotating shaft through a first mounting hole of the turbine turntable; the plurality of turbine blades are circumferentially and uniformly arranged on the outer wall of the turbine rotary table, and the roots of the plurality of turbine blades are detachably and fixedly connected with the outer wall of the turbine rotary table;

the turbine stator vane disk comprises a turbine stator rotary disk and a plurality of turbine stator blades; the center of the turbine stator turntable is provided with a second mounting hole matched with the turbine stator bearing; the turbine turntable is coaxially and fixedly connected with the outer ring of the turbine stator bearing through a second mounting hole of the turbine turntable, and the inner ring of the turbine stator bearing is coaxially and fixedly connected with the rotating shaft; the plurality of turbine blades are circumferentially and uniformly arranged on the outer wall of the turbine stator turntable, the root parts of the plurality of turbine blades are detachably and fixedly connected with the outer wall of the turbine stator turntable, and the tip parts of the plurality of turbine blades are detachably and fixedly connected with the inner wall of the casing, so that the casing and the turbine stator turntable are coaxial;

the casing is provided with at least one peeping hole for an endoscope to extend a probe into at least one corresponding position of the compressor blade disc, the compressor stator blade disc, the turbine blade disc and the turbine stator blade disc;

the flange plate is coaxially and fixedly connected with one end of the rotating shaft;

the casing is fixed on the base through a test bracket;

the driving motor is fixed on the base through a motor bracket, and an output shaft of the driving motor is coaxially and fixedly connected with the flange plate through the nylon coupling.

2. The aeroengine hole detection test simulation tester according to claim 1, wherein four peepholes for an endoscope to extend a probe into are uniformly arranged at corresponding positions of a compressor blade disc, a compressor stator blade disc, a turbine blade disc and a turbine stator blade disc in the circumferential direction.