CN116818340A - Aeroengine hole detection test simulation tester - Google Patents
Aeroengine hole detection test simulation tester Download PDFInfo
- Publication number
- CN116818340A CN116818340A CN202310779410.XA CN202310779410A CN116818340A CN 116818340 A CN116818340 A CN 116818340A CN 202310779410 A CN202310779410 A CN 202310779410A CN 116818340 A CN116818340 A CN 116818340A
- Authority
- CN
- China
- Prior art keywords
- compressor
- turbine
- turntable
- stator
- fixedly connected
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000012360 testing method Methods 0.000 title claims abstract description 44
- 238000001514 detection method Methods 0.000 title claims abstract description 31
- 238000004088 simulation Methods 0.000 title claims abstract description 14
- 239000004677 Nylon Substances 0.000 claims abstract description 8
- 230000008878 coupling Effects 0.000 claims abstract description 8
- 238000010168 coupling process Methods 0.000 claims abstract description 8
- 238000005859 coupling reaction Methods 0.000 claims abstract description 8
- 229920001778 nylon Polymers 0.000 claims abstract description 8
- 239000000523 sample Substances 0.000 claims description 8
- 208000008918 voyeurism Diseases 0.000 claims description 4
- 230000007547 defect Effects 0.000 abstract description 6
- 238000000034 method Methods 0.000 abstract description 6
- 238000011161 development Methods 0.000 abstract description 4
- 238000009417 prefabrication Methods 0.000 abstract description 3
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 238000011160 research Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 238000007689 inspection Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 241001391944 Commicarpus scandens Species 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000001839 endoscopy Methods 0.000 description 1
- 239000006247 magnetic powder Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000009659 non-destructive testing Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses an aero-engine hole detection test simulation tester, which comprises a driving motor, a motor bracket, a nylon coupling, a test module, a test bracket and a base, wherein the driving motor is arranged on the motor bracket; 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 method can meet the requirements of the internal damage prefabrication and the hole detection simulation test of the aeroengine, is beneficial to the development and the test as well as the secondary development of Kong Tance test equipment, and provides test data for the automatic defect identification based on the hole detection image.
Description
Technical Field
The invention relates to an aeroengine hole detection test, which realizes aeroengine hole detection test, and comprehensively develops and improves the existing aeroengine hole detection quantity technology.
Background
The aeroengine is a main power source for the aircraft to fly, and because the aeroengine works in a working environment with high temperature, high pressure and high vibration for a long time and the turbofan engine with high bypass ratio easily sucks stones, aircraft missing parts, birds and other foreign objects near the runway and the taxiway in the processes of taking off, landing and ground taxiing of the aircraft, the aeroengine is easy to break down. Serious engine failure can cause engine surge or air stopping, and can pose a great threat to flight safety. The engine is regularly checked or the aircraft can be ensured to be continuously navigable by maintaining according to conditions after emergency, so that the daily utilization rate of the aircraft is improved, the maintenance cost is saved, and the economic benefit of an airline company is increased. Internal component and structural damage is an important cause of failure of an aeroengine, and the internal damage of the engine is usually detected by using a nondestructive inspection method, and common nondestructive inspection methods include magnetic powder detection, penetration detection, eddy current detection, ultrasonic detection, radiation detection and hole detection (endoscopy). Kong Tan is the most widely applied nondestructive testing method in the current aeroengine overhaul because of the rapidness and convenience, and students at home and abroad also conduct intensive research on the hole detection technology, but the research result is difficult to apply to engineering practice. One of the important reasons is the lack of corresponding aeroengine hole detection test verification, while the real aeroengine price and the high price thereof and the difficult disassembly and customization of the internal core machine, so the design and manufacture of the aeroengine simulation tester capable of meeting the hole detection test research is extremely important. However, the existing aeroengine hole detection test research device generally has one or several of the following defects: no casing, only the engine rotor portion or no stator vane portion; the engine core machine has no basic structure of a real aeroengine core machine and only has simple structures such as a blade disc and the like; the blades and the blade discs are integrated, so that the blades cannot be well replaced and the defects are prefabricated; the position between the casing and the rotor is limited, so that the hole detection equipment is inconvenient to carry out hole detection photographing test and the like.
Disclosure of Invention
Aiming at the defects related to the background technology, the invention provides an aeroengine hole detection test simulation tester which can be used for carrying out aeroengine internal damage hole detection test simulation at a low rotating speed or in a hand-operated rotating state.
The invention adopts the following technical scheme for solving the technical problems:
an aeroengine hole detection test simulation tester comprises 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.
As a further optimization scheme of the aeroengine hole detection test simulation tester, four peeping holes for an endoscope to extend a probe into are uniformly formed in the corresponding positions of the compressor blade disc, the compressor stator blade disc, the turbine blade disc and the turbine stator blade disc in the circumferential direction.
Compared with the prior art, the technical scheme provided by the invention has the following technical effects:
the invention constructs an aeroengine hole detection test simulation tester with a similar structure of an aeroengine core machine, which is provided with a casing, a compressor blade disc, a compressor stator blade disc, a turbine blade disc and a turbine stator blade disc, so that hole detection test can be conveniently carried out, and blades in the compressor blade disc, the compressor stator blade disc, the turbine blade disc and the turbine stator blade disc are matched with a turntable in a detachable mode, and replacement and defect prefabrication of the blades can be conveniently carried out. The method can meet the requirements of the internal damage prefabrication and the hole detection simulation test of the aeroengine, is beneficial to the development and the test as well as the secondary development of Kong Tance test equipment, and provides test data for the automatic defect identification based on the hole detection image.
Drawings
FIG. 1 is a schematic diagram of the structure of the present invention;
FIG. 2 is a schematic cross-sectional view of the present invention;
FIG. 3 is a schematic view of the configuration of the invention in which the test module is mated with the probe of the endoscope.
In the figure, the probe of the endoscope comprises a 1-driving motor, a 2-motor bracket, a 3-nylon coupling, a 4-test module, a 5-test bracket, a 6-base, a 7-casing, an 8-rotating shaft, a 9-compressor rotating disc, a 10-compressor blade, a 11-compressor stator rotating disc, a 12-compressor stator blade, a 13-compressor stator bearing, a 14-turbine rotating disc, a 15-turbine blade, a 16-turbine stator blade, a 17-turbine stator blade, a 18-turbine stator bearing, a 19-flange and a 20-endoscope.
Description of the embodiments
The technical scheme of the invention is further described in detail below with reference to the accompanying drawings:
this 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 fig. 1, the invention discloses an aero-engine hole detection test simulation tester, which comprises a driving motor, a motor bracket, a nylon coupling, a test module, a test bracket and a base;
as shown in fig. 2, 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, as shown in fig. 3;
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.
Four peepholes for an endoscope to extend a probe into are uniformly arranged at the corresponding positions of the compressor blade disc, the compressor stator blade disc, the turbine blade disc and the turbine stator blade disc in a circumferential direction preferentially and uniformly.
It will be understood by those skilled 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 will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the prior art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
While the foregoing is directed to embodiments of the present invention, other and further details of the invention may be had by the present invention, it should be understood that the foregoing description is merely illustrative of the present invention and that no limitations are intended to the scope of the invention, except insofar as modifications, equivalents, improvements or modifications are within the spirit and principles of the 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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310779410.XA CN116818340A (en) | 2023-06-29 | 2023-06-29 | Aeroengine hole detection test simulation tester |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310779410.XA CN116818340A (en) | 2023-06-29 | 2023-06-29 | Aeroengine hole detection test simulation tester |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116818340A true CN116818340A (en) | 2023-09-29 |
Family
ID=88114169
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310779410.XA Pending CN116818340A (en) | 2023-06-29 | 2023-06-29 | Aeroengine hole detection test simulation tester |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116818340A (en) |
-
2023
- 2023-06-29 CN CN202310779410.XA patent/CN116818340A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP3361229B1 (en) | System and method for blade health monitoring | |
| CN106996740B (en) | For the system and method being positioned in gas-turbine unit that will pop one's head in | |
| US7717666B2 (en) | Methods and apparatus for rotary machinery inspection | |
| US10197473B2 (en) | System and method for performing a visual inspection of a gas turbine engine | |
| CN110672055B (en) | System and method for measuring blade clearance in a turbine engine | |
| US20190383161A1 (en) | Inspection Tool and Method | |
| CN105738116B (en) | A kind of turbine test device | |
| CN203130170U (en) | Low-pressure rotor autorotation tool used for borescope inspection of engine of civil aircraft | |
| US10196922B2 (en) | System and method for locating a probe within a gas turbine engine | |
| EP4047191A1 (en) | Instrumented turbine exhaust duct | |
| CN116818340A (en) | Aeroengine hole detection test simulation tester | |
| Hubinka et al. | Design and construction of a two shaft test turbine for investigation of mid turbine frame flows | |
| CN102777410B (en) | Compressor for aerodynamic performance comprehensive test platform of no-tail rotor anti-torque system | |
| CN116380383A (en) | Aeroengine blade vibration testing device | |
| CN113252280B (en) | Nacelle test device capable of simulating air intake and exhaust simultaneously | |
| US20220003354A1 (en) | Gas turbine engine casing arrangement | |
| US20190061965A1 (en) | Turbine engine with single wall cantilevered architecture | |
| CN210953407U (en) | Rotary measuring device and test system of aero-engine test bed | |
| CN109443773A (en) | Turbine model is used in a kind of test of thermal barrier coating service Work condition analogue | |
| EP4400693A1 (en) | Computationally balancing a rotating structure | |
| CN112985822B (en) | Air inlet channel test device for simulating coupling effect of air inlet channel and fan | |
| RU2013149549A (en) | METHOD OF SERIAL PRODUCTION OF A GAS TURBINE ENGINE AND A GAS TURBINE ENGINE EXECUTED BY THIS METHOD | |
| EP4450770A2 (en) | Propulsor blade imaging assembly for an aircraft propulsion system | |
| CN118408749B (en) | Fan casing inclusion test device and use method | |
| CN116558831A (en) | Civil turboshaft engine simulation windmill test tool |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |