CN217687868U

CN217687868U - Aeroengine test run rack

Info

Publication number: CN217687868U
Application number: CN202221416641.1U
Authority: CN
Inventors: 夏晓虎; 邢博
Original assignee: Individual
Current assignee: Individual
Priority date: 2022-06-08
Filing date: 2022-06-08
Publication date: 2022-10-28
Anticipated expiration: 2032-06-08

Abstract

The utility model belongs to the technical field of the rack of taking a trial run, an aeroengine platform of taking a trial run is disclosed, including bottom plate and activity set up in the test piece at bottom plate top, the top activity of bottom plate is provided with first fly leaf and second fly leaf, the top fixed mounting of first fly leaf has the first supporting block of symmetry, the top fixed mounting of first supporting block has first loading board, the top fixed mounting of first loading board has the first stopper of symmetry, the test piece is arched door shape structure, the test piece activity set up in the top of first stopper, one side fixed mounting of first loading board has the fixed block. This device possesses the pressure test structure, can test out the pressure that the aeroengine during operation vibration produced the test body on the rack of taking a trial run fast to can conveniently carry out quick adjustment and fix to the position of pressure test structure, thereby conveniently carry out the quick test to the vibrating pressure of aeroengine its outer wall when the rack of taking a trial run.

Description

Aeroengine test run rack

Technical Field

The application relates to the technical field of test run racks, in particular to an aero-engine test run rack.

Background

An aircraft engine is a highly complex and precise thermal machine, and in order to ensure the normal operation of the aircraft engine and the stable flight of an aircraft, the characteristics of the engine need to be tested in a testing stage, and the aircraft engine is usually placed on a test stand for testing at present.

However, the existing test bed for the aero-engine is usually lack of a pressure testing structure, so that the pressure generated by vibration to a testing body when the aero-engine works on the test bed is difficult to test quickly, the position of the pressure testing structure is difficult to adjust and fix quickly, and further improvement is needed.

SUMMERY OF THE UTILITY MODEL

In order to solve the problem, the application provides an aeroengine test bed frame.

The application provides an aeroengine platform frame of taking a trial run adopts following technical scheme:

aeroengine platform frame of taking a trial run, including bottom plate and activity set up in the test block at bottom plate top, the top activity of bottom plate is provided with first fly leaf and second fly leaf, the top fixed mounting of first fly leaf has the first supporting block of symmetry, the top fixed mounting of first supporting block has first loading board, the top fixed mounting of first loading board has the first stopper of symmetry, the test block is arched door shape structure, the test block activity set up in the top of first stopper, one side fixed mounting of first loading board has the fixed block, the top and the bottom of fixed block run through and have seted up first cell body, the inner wall activity of first cell body is provided with first movable block, the top fixed mounting of first movable block has fixed frame, the inner wall activity of fixed frame is provided with the second movable block, the fixed second cell body that has seted up in one side of test block, the inner wall fixed mounting of second cell body has first pressure sensor, one side fixed mounting of first pressure sensor's test head has first rubber body.

Through above-mentioned technical scheme, place aeroengine on the top of first loading board, place the test block in the suitable position on first stopper top, make aeroengine's outer wall laminate mutually with the outer wall of the first rubber body, aeroengine when opening, the shake on its surface can be detected by first pressure sensor to but the quick test of the pressure that produces the test body of aeroengine during operation vibration on the platform frame of taking a trial run.

Furthermore, the top end of the bottom plate is fixedly provided with symmetrical first limiting grooves, the bottom end of the first movable plate is fixedly provided with symmetrical second limiting blocks, and the second limiting blocks are matched with the first limiting grooves.

Through above-mentioned technical scheme, the inner wall removal of first spacing groove can be followed to the second stopper to make things convenient for first fly leaf to stably remove on the top of bottom plate.

Further, the top fixed mounting of second fly leaf has the second supporting shoe of symmetry, the top fixed mounting of second supporting shoe has the second loading board, the second spacing groove has been seted up in the both ends of first loading board run through, the one end fixed mounting of second loading board has the limiting plate, the outer wall of limiting plate and the inner wall in second spacing groove laminate mutually.

Through above-mentioned technical scheme, the limiting plate removes along the inner wall of second spacing groove to can realize the stable removal of second loading board.

Further, the both sides of fixed block are run through and are seted up first thread groove, the bolt is installed to the inner wall screw thread of first thread groove, the both sides of first movable block run through and are seted up evenly distributed's second thread groove, bolt and second thread groove looks adaptation.

Through above-mentioned technical scheme, pass first thread groove with the bolt and install the inner wall at the second thread groove of suitable height, can realize carrying out quick adjustment and fixed to the height of second movable block.

Furthermore, the top and the bottom of second movable block run through the third thread groove of seting up evenly distributed, the top and the bottom of fixed frame run through and have seted up the fourth thread groove, the internal thread of fourth thread groove installs the screw thread post, screw thread post and third thread groove looks adaptation.

Through above-mentioned technical scheme, pass the inner wall at the third thread groove of suitable position with the screw thread post, can carry out quick adjustment and fixed to the position of second movable block.

Furthermore, a third groove body is fixedly formed in the inner wall of the other side of the test block, and a magnet block is fixedly mounted on the inner wall of the third groove body.

Through above-mentioned technical scheme, the magnetite piece can adsorb the outer wall at the first stopper of iron to do benefit to the stable of testing the piece and place.

Furthermore, a fourth groove body is fixedly formed in one side, close to the center of the top of the first bearing plate, of the second movable block, a second pressure sensor is fixedly mounted on the inner wall of the fourth groove body, and a second rubber body is fixedly mounted on a test head of the second pressure sensor.

Through above-mentioned technical scheme, adjust the position of second movable block, make the second rubber body laminate mutually with aeroengine's outer wall, aeroengine when the test operation, the vibrational force accessible second rubber body of its outer wall is transmitted and is surveyed pressure by second pressure sensor on to the second pressure sensor.

In summary, the present application includes at least one of the following advantageous technical effects:

(1) According to the device, the testing block, the first pressure sensor and the first rubber body are arranged, the testing block is placed at the top end of the first limiting block at a proper position, the outer wall of the first rubber body is attached to the outer wall of the aero-engine, and when the aero-engine runs, vibration pressure can be transmitted to the first pressure sensor through the first rubber body, and the first pressure sensor can rapidly measure pressure;

(2) The device can realize the quick adjustment and fixation of the height of the second movable block by arranging the fixed block, the first movable block, the first screw groove, the second screw groove and the bolt and arranging the bolt to penetrate through the first screw groove and be arranged on the inner wall of the second screw groove with proper height;

(3) This device is through setting up second pressure sensor and the second rubber body, adjusts the position of second movable block and makes the outer wall of the second rubber body laminate mutually with aeroengine's outer wall, and aeroengine is when moving, and the vibration pressure accessible second rubber body on its outer wall transmits to second pressure sensor and is surveyed pressure by last second pressure sensor to accessible pressure numerical value judges aeroengine's stability.

Drawings

FIG. 1 is a schematic perspective view of an aircraft engine test bed;

fig. 2 is a schematic perspective view of a fixing block of the present application;

FIG. 3 is a cross-sectional view of a test block of the present application;

fig. 4 is a cross-sectional view of a second movable block in the present application.

The reference numbers in the figures illustrate: 1. a base plate; 2. a first movable plate; 3. a first support block; 4. a first bearing plate; 5. a first stopper; 6. a test block; 7. a second movable plate; 8. a second support block; 9. a second carrier plate; 10. a first limit groove; 11. a second limiting block; 12. a second limit groove; 13. a limiting plate; 14. a first rubber body; 15. a fixed block; 16. a first tank body; 17. a first screw groove; 18. a bolt; 19. a first movable block; 20. a second screw groove; 21. a fixing frame; 22. a second movable block; 23. a third screw groove; 24. a fourth screw groove; 25. a threaded post; 26. a second rubber body; 27. a second tank body; 28. a first pressure sensor; 29. a third tank body; 30. a magnet block; 31. a fourth tank body; 32. a second pressure sensor.

Detailed Description

The technical solution in the embodiment of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiment of the present invention; obviously, the described embodiments are only a part of the embodiments of the present invention, and not all embodiments, and all other embodiments obtained by those skilled in the art without any inventive work are within the scope of the present invention based on the embodiments of the present invention.

In the description of the present invention, it should be noted that the terms "upper", "lower", "inner", "outer", "top/bottom", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted", "provided", "sleeved/connected", "connected", and the like are to be understood in a broad sense, such as "connected", which may be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood as a specific case by those skilled in the art.

The present application is described in further detail below with reference to figures 1-4.

The embodiment of the application discloses an aeroengine test bench, which comprises a bottom plate 1 and a test block 6 movably arranged at the top of the bottom plate 1, wherein the top end of the bottom plate 1 is movably provided with a first movable plate 2 and a second movable plate 7, the top end of the first movable plate 2 is fixedly provided with symmetrical first supporting blocks 3, the top end of the first supporting blocks 3 is fixedly provided with a first bearing plate 4, the top end of the first bearing plate 4 is fixedly provided with symmetrical first limiting blocks 5, the test block 6 is in an arched door-shaped structure, the test block 6 is movably arranged at the top end of the first limiting blocks 5, one side of the first bearing plate 4 is fixedly provided with a fixed block 15, the top end and the bottom end of the fixed block 15 are provided with a first groove body 16 in a penetrating way, and the inner wall of the first groove body 16 is movably provided with a first movable block 19, the top fixed mounting of first movable block 19 has fixed frame 21, the inner wall activity of fixed frame 21 is provided with second movable block 22, second cell body 27 has been seted up to one side of test block 6 is fixed, the inner wall fixed mounting of second cell body 27 has first pressure sensor 28, one side fixed mounting of first pressure sensor 28's test head has first rubber body 14, the top fixed mounting of second fly leaf 7 has the second supporting shoe 8 of symmetry, the top fixed mounting of second supporting shoe 8 has second loading board 9, the second spacing groove 12 has been seted up in running through at the both ends of first loading board 4, the one end fixed mounting of second loading board 9 has limiting plate 13, the outer wall of limiting plate 13 is laminated with the inner wall of second spacing groove 12 mutually.

Referring to fig. 1, in order to realize stable movement of the first movable plate 2, symmetrical first limiting grooves 10 are fixedly formed at the top end of the bottom plate 1, symmetrical second limiting blocks 11 are fixedly mounted at the bottom end of the first movable plate 2, and the second limiting blocks 11 are matched with the first limiting grooves 10. When the first movable plate 2 moves at the top end of the base plate 1, the second stopper 11 moves along the inner wall of the first stopper groove 10, so that the stable movement of the first movable plate 2 can be realized.

Referring to fig. 2, in order to quickly adjust and fix the height and the horizontal position of the second movable block 22, the first screw grooves 17 are formed in the two sides of the fixed block 15, the bolts 18 are installed on the inner wall threads of the first screw grooves 17, the second screw grooves 20 which are uniformly distributed are formed in the two sides of the first movable block 19, the bolts 18 are matched with the second screw grooves 20, the third screw grooves 23 which are uniformly distributed are formed in the top and the bottom of the second movable block 22, the fourth screw grooves 24 are formed in the top and the bottom of the fixed frame 21, the threaded columns 25 are installed on the internal threads of the fourth screw grooves 24, and the threaded columns 25 are matched with the third screw grooves 23. The bolt 18 passes through the first thread groove 17 and is installed on the inner wall of the second thread groove 20 with a proper height, so that the height of the second movable block 22 can be quickly adjusted and fixed, and the threaded column 25 passes through the inner wall of the fourth thread groove 24 and is installed on the third thread groove 23 with a proper position in a threaded manner, so that the position of the second movable block 22 in the horizontal direction can be quickly adjusted and fixed.

Referring to fig. 3, in order to improve the stability of the test block 6 during placement, a third groove 29 is fixedly formed on the inner wall of the other side of the test block 6, and a magnet block 30 is fixedly mounted on the inner wall of the third groove 29. The magnet block 30 can be placed on the outer wall of the first stopper 5 made of iron in an adsorptive manner, so that the stability of the test block 6 during placement can be realized.

Referring to fig. 4, in order to implement multiple-group tests on the outer wall vibration pressure during the operation of the aircraft engine, a fourth groove 31 is fixedly formed in one side of the second movable block 22 close to the center of the top of the first bearing plate 4, a second pressure sensor 32 is fixedly mounted on the inner wall of the fourth groove 31, and a second rubber body 26 is fixedly mounted on a test head of the second pressure sensor 32. The second rubber body 26 is attached to different positions on the outer wall of the aircraft engine by adjusting the position of the second movable block 22, and the pressure of the vibration action of the outer wall of the aircraft engine on the second pressure sensor 32 can be tested by using the second pressure sensor 32 when the aircraft engine vibrates.

The implementation principle of aeroengine test run rack of the embodiment of this application does: the aero-engine is placed at the top end of the first bearing plate 4, the outer wall of the aero-engine is attached to the inner walls of the two sides of the first limiting block 5, the testing block 6 is placed at a proper position at the top end of the first limiting block 5, the outer wall of the aero-engine is attached to the outer wall of the first rubber body 14, when the aero-engine is started, surface vibration of the aero-engine can be detected by the first pressure sensor 28, pressure generated by vibration of the aero-engine on a test bed when the aero-engine works can be rapidly tested, the bolt 18 penetrates through the first screw groove 17 and is installed on the inner wall of the second screw groove 20 at a proper height, rapid adjustment and fixation of the height of the second movable block 22 can be achieved, the threaded column 25 penetrates through the inner wall of the third screw groove 23 at a proper position in a threaded mode through the fourth screw groove 24, the position of the second movable block 22 in the horizontal direction can be rapidly adjusted and fixed, the position of the second movable block 22 is adjusted, the second rubber body 26 is attached to different positions on the outer wall of the aero-engine outer wall when the second pressure sensor 32 is used for vibration testing, and accuracy of the vibration pressure of the aero-engine can be tested.

The above embodiments are preferred embodiments of the present application, and the protection scope of the present application is not limited by the above embodiments, so: all equivalent changes made according to the structure, shape and principle of the present application shall be covered by the protection scope of the present application.

Claims

1. Aeroengine test run rack, including bottom plate (1) with the activity set up in test block (6) at bottom plate (1) top, its characterized in that: the utility model discloses a pressure sensor testing device, including bottom plate (1), bottom plate, first loading board, first cell body (16), first movable block (27), first supporting block (3) of symmetry, the top fixed mounting of first supporting block (3), first loading board (4) of top fixed mounting of first loading board (4), test block (6) are arched door shape structure, test block (6) activity set up in the top of first stopper (5), one side fixed mounting of first loading board (4) has fixed block (15), first cell body (16) have been run through to the top and the bottom of fixed block (15), the inner wall activity of first cell body (16) is provided with first movable block (19), the top fixed mounting of first movable block (19) has fixed frame (21), the inner wall activity of fixed frame (21) is provided with second movable block (22), second cell body (27) have been seted up to one side fixed of fixed block (6), the inner wall fixed mounting of second cell body (27) has first movable block (28), the pressure sensor (28) is installed to one side fixed sensor (14) of first fixed sensor.

2. The aircraft engine test run stand of claim 1, wherein: the top of bottom plate (1) is fixed and is seted up first spacing groove (10) of symmetry, the bottom fixed mounting of first fly leaf (2) has second stopper (11) of symmetry, second stopper (11) and first spacing groove (10) looks adaptation.

3. The aircraft engine test stand of claim 1, wherein: the utility model discloses a portable loading device, including second fly leaf (7), second supporting shoe (8), second loading board (9), second spacing groove (12), limiting plate (13), the outer wall of limiting plate (13) and the inner wall of second spacing groove (12) laminate mutually, the top fixed mounting of second fly leaf (7) has second supporting shoe (8) of symmetry, the top fixed mounting of second supporting shoe (8) has second loading board (9), run through at the both ends of first loading board (4) and seted up second spacing groove (12), the one end fixed mounting of second loading board (9) has limiting plate (13).

4. The aircraft engine test stand of claim 1, wherein: the both sides of fixed block (15) are run through and are seted up first thread groove (17), bolt (18) are installed to the inner wall screw thread of first thread groove (17), evenly distributed's second thread groove (20) are run through to the both sides of first movable block (19), bolt (18) and second thread groove (20) looks adaptation.

5. The aircraft engine test run stand of claim 1, wherein: the top and the bottom of second movable block (22) run through and seted up evenly distributed's third thread groove (23), the top and the bottom of fixed frame (21) run through and seted up fourth thread groove (24), the internal thread of fourth thread groove (24) is installed screw thread post (25), screw thread post (25) and third thread groove (23) looks adaptation.

6. The aircraft engine test run stand of claim 1, wherein: a third groove body (29) is fixedly formed in the inner wall of the other side of the test block (6), and a magnet block (30) is fixedly mounted on the inner wall of the third groove body (29).

7. The aircraft engine test run stand of claim 1, wherein: the second movable block (22) is close to one side of the center of the top of the first bearing plate (4) and is fixedly provided with a fourth groove body (31), the inner wall of the fourth groove body (31) is fixedly provided with a second pressure sensor (32), and a test head of the second pressure sensor (32) is fixedly provided with a second rubber body (26).