Aero-engine thrust measuring device

Abstract

The utility model belongs to the field of optical-mechanical-electrical integrated precision measurement, and particularly relates to an aero-engine thrust measuring device which comprises a bottom plate, a sliding rail is fixedly connected to the surface of the bottom plate, a limiting strip is slidably installed on the inner side of the sliding rail, and a frame is fixedly connected to the inner side of the limiting strip. A mounting plate is fixedly connected to the top of the frame, and a bolt is fixedly mounted on the surface of the mounting plate in a threaded manner; the engine main body is fixed through the supporting block and the clamping block, the pressing column abuts against the surface of the pressure gauge to align the thrust of the device for measurement, the stability of the device during measurement is improved, through the design of the clamping block fixedly connected through a bolt, clamping blocks of different sizes can be replaced conveniently, and the adaptability of the device is improved; and secondly, the engine main body is fixed through the clamping blocks, and the moving range of the frame is limited through the sealing plate, so that the possibility that the frame possibly slides forwards under the counter-acting force when the engine main body is closed is reduced, and the stability of the device is improved.

Description

Technical Field

[0001] The utility model relates to the field of optical, mechanical and electrical integration precision measurement, in particular to an aero-engine thrust measurement device. Background Art

[0002] Opto-mechanical integration technology is the intersection and integration of microelectronics, computer technology, control technology, optical technology, and mechanical technology. It is the foundation of many high-tech industries and high-tech equipment. It includes two aspects: products and technologies. Opto-mechanical integration products are high-tech products that integrate optics, mechanics, microelectronics, automatic control, and communication technologies, with rich functions and high added value.

[0003] When measuring the thrust of an aircraft engine, an optomechanical and electrical integrated precision measuring device is required.

[0004] Existing aircraft engine thrust measurement devices are not easy to achieve the effect of stably and conveniently clamping engine bodies of different sizes, which may lead to reduced adaptability and stability of the device. Existing aircraft engine thrust measurement devices are not easy to achieve an effective restriction effect on the device, which may lead to reduced stability of the device.

[0005] Therefore, in order to solve the above problems, an aero-engine thrust measuring device is proposed. Utility Model Content

[0006] In order to remedy the problems in the prior art, the utility model proposes an aero-engine thrust measuring device.

[0007] The technical solution adopted by the present invention to solve its technical problems is: an aircraft engine thrust measuring device described in the present invention includes a base plate, the surface of the base plate is fixedly connected to a slide rail, the inner side of the slide rail is slidably installed with a limit strip, the inner side of the limit strip is fixedly connected to a frame, the top of the frame is fixedly connected to a mounting plate, the surface of the mounting plate is fixedly threaded with bolts, the surface of the mounting plate is fixedly connected to one of the clamping blocks by bolts, the inner wall of the clamping block is engaged with the engine body, the surface of the mounting plate is fixedly connected to the support frame, the top of the support frame is fixedly connected to a hydraulic press, the output end of the hydraulic press is fixedly connected to a cross plate, the rear side of the engine body is engaged with the support block, the rear side of the mounting plate is fixedly connected to a pressure column, and the surface of the base plate is fixedly connected to a pressure gauge.

[0008] Preferably, the surface of the transverse plate is fixedly connected to another clamping block by bolts, and the side surface of the transverse plate is slidably connected to the inner wall of the support frame.

[0009] Preferably, the surface of the bottom plate is fixedly connected to the sealing plate by bolts, and the rear side of the sealing plate is pressed against one end of the slide rail.

[0010] Preferably, pulleys are rotatably connected to positions near the four corners of the bottom surface of the frame.

[0011] Preferably, a plurality of mounting holes are provided on the surface of the mounting plate at equal distances, and the mounting holes are fixedly connected to the support blocks by bolts.

[0012] Preferably, the installation position of the pressure gauge corresponds to the setting position of the pressure column.

[0013] The utility model is beneficial in that:

[0014] 1. The utility model fixes the engine body by means of a support block and a clamping block. The pressure column is pressed against the surface of the pressure gauge to measure the thrust of the device, which improves the stability of the device during measurement. The design of the clamping block fixed by bolts facilitates the replacement of clamping blocks of different sizes, thus improving the adaptability of the device.

[0015] 2. The utility model fixes the engine body by the clamping block and limits the movement range of the frame by the sealing plate, thereby reducing the possibility that the frame may slide forward due to the reaction force when the engine body is closed, thereby improving the stability of the device. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. 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 these drawings without paying any creative work.

[0017] Figure 1 This is a schematic diagram of the main structure of the utility model;

[0018] Figure 2 This is a schematic diagram of the clamping block structure of the utility model;

[0019] Figure 3 This is a schematic diagram of the limit bar structure of the utility model;

[0020] Figure 4 This is a schematic diagram of the support block structure of the present utility model.

[0021] In the figure: 1. Base plate; 2. Slide rail; 3. Closing plate; 4. Bolt; 5. Pulley; 6. Frame; 7. Mounting plate; 8. Clamping block; 9. Support frame; 10. Hydraulic press; 11. Cross plate; 12. Engine body; 13. Support block; 14. Mounting hole; 15. Pressure column; 16. Pressure gauge; 17. Limit strip. DETAILED DESCRIPTION

[0022] The following will be combined with the accompanying 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 embodiments described 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 making creative efforts are within the scope of protection of the present invention.

[0023] See also Figure 1-Figure 4 As shown, an aircraft engine thrust measuring device includes a base plate 1, a slide rail 2 is fixedly connected to the surface of the base plate 1, a limit strip 17 is slidably installed on the inner side of the slide rail 2, a frame 6 is fixedly connected to the inner side of the limit strip 17, a mounting plate 7 is fixedly connected to the top of the frame 6, a bolt 4 is fixedly threaded on the surface of the mounting plate 7, a clamping block 8 is fixedly connected to the surface of the mounting plate 7 by the bolt 4, an engine body 12 is mounted on the inner wall of the clamping block 8, a support frame 9 is fixedly connected to the surface of the mounting plate 7, a hydraulic press 10 is fixedly connected to the top of the support frame 9, a cross plate 11 is fixedly connected to the output end of the hydraulic press 10, a support block 13 is snap-connected to the rear side of the engine body 12, a pressure column 15 is fixedly connected to the rear side of the mounting plate 7, and a pressure gauge 16 is fixedly connected to the surface of the base plate 1;

[0024] Furthermore, the surface of the horizontal plate 11 is fixedly connected to another clamping block 8 by means of bolts 4, and the side surface of the horizontal plate 11 is slidably connected to the inner wall of the support frame 9;

[0025] During operation, the structural design of fixing another clamping block 8 to the surface of the transverse plate 11 by bolts 4 facilitates the device to clamp the upper and lower sides of the engine body 12, thereby improving the stability of the device during installation.

[0026] Furthermore, the surface of the bottom plate 1 is fixedly connected to the sealing plate 3 by means of bolts 4, and the rear side of the sealing plate 3 is pressed against one end of the slide rail 2;

[0027] During operation, the rear side of the sealing plate 3 is pressed against one end of the slide rail 2 , so that the sealing plate 3 limits the movement range of the frame 6 , thereby improving the stability of the device during operation.

[0028] Furthermore, the bottom surface of the frame 6 near the four corners is rotatably connected to pulleys 5;

[0029] During operation, the bottom surface of the frame 6 near the four corners is rotatably connected to the pulleys 5 , which facilitates the frame 6 to slide on the surface of the bottom plate 1 and provides a stable support effect for the frame 6 .

[0030] Furthermore, a plurality of mounting holes 14 are formed at equal distances on the surface of the mounting plate 7, and the mounting holes 14 are fixedly connected to the support block 13 by bolts 4;

[0031] During operation, the surface of the mounting plate 7 is provided with a plurality of mounting holes 14 at equal intervals, which facilitates adjustment of the mounting position of the support block 13 and improves the adaptability of the device.

[0032] Furthermore, the installation position of the pressure gauge 16 corresponds to the setting position of the pressure column 15;

[0033] During operation, the structural design in which the installation position of the pressure gauge 16 corresponds to the setting position of the pressure column 15 facilitates the device to measure the thrust generated by the engine body 12 .

[0034] Working principle: First, fix the clamping block 8 of appropriate shape to the surface of the mounting plate 7 through the bolt 4, and hoist the engine body 12 above the clamping block 8, and at the same time start the hydraulic press 10 through the external power supply. The output end of the hydraulic press 10 enables another clamping block 8 to clamp the top surface of the engine body 12 through the cross plate 11. The sliding connection design of the cross plate 11 and the support frame 9 improves the stability of the device. At the same time, slide the support block 13 to the appropriate position on the surface of the mounting plate 7. The rear end of the engine body 12 is engaged with the internal part of the support block 13, and the support block 13 is fixedly installed above the mounting hole 14 through the bolt 4. Start the engine body 12 through the external oil supply device same as that of the aircraft. At this time, the frame 6 is subjected to the thrust of the engine body 12 and slides to the position of the pressure gauge 16. The pressure column 15 presses against the surface of the pressure gauge 16 to measure the thrust of the alignment device;

[0035] The pulley 5 design at the bottom of the frame 6 reduces the friction when the device moves. The design of the clamping block 8 fixed by the bolt 4 makes it easy to replace the clamping blocks 8 of different sizes. The sealing plate 3 limits the moving range of the frame 6, reducing the possibility that the frame 6 may slide to the front side due to the reaction force when the engine body 12 is closed.

[0036] The above shows and describes the basic principles, main features and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The above embodiments and descriptions are merely illustrative of the principles of the present invention. Various changes and improvements may be made to the present invention without departing from the spirit and scope of the present invention, and such changes and improvements fall within the scope of the present invention as claimed.

Claims

1. An aero-engine thrust measuring device, comprising a base plate (1), characterized in that: The surface of the base plate (1) is fixedly connected to a slide rail (2), the inner side of the slide rail (2) is slidably mounted with a limit strip (17), the inner side of the limit strip (17) is fixedly connected to a frame (6), the top of the frame (6) is fixedly connected to a mounting plate (7), the surface of the mounting plate (7) is fixedly threaded with a bolt (4), the surface of the mounting plate (7) is fixedly connected to one of the clamping blocks (8) through the bolt (4), the inner wall of the clamping block (8) is engaged with the engine body (12), the surface of the mounting plate (7) is fixedly connected to a support frame (9), the top of the support frame (9) is fixedly connected to a hydraulic press (10), the output end of the hydraulic press (10) is fixedly connected to a transverse plate (11), the rear side of the engine body (12) is engaged with the support block (13), the rear side of the mounting plate (7) is fixedly connected to a pressure column (15), and the surface of the base plate (1) is fixedly connected to a pressure gauge (16).

2. The aircraft engine thrust measurement device according to claim 1, characterized in that: The surface of the transverse plate (11) is fixedly connected to another clamping block (8) via bolts (4), and the side surface of the transverse plate (11) is slidably connected to the inner wall of the support frame (9).

3. The aircraft engine thrust measurement device according to claim 1, characterized in that: The surface of the bottom plate (1) is fixedly connected to the sealing plate (3) via bolts (4), and the rear side of the sealing plate (3) is pressed against one end of the slide rail (2).

4. The aircraft engine thrust measurement device according to claim 1, characterized in that: The bottom surface of the frame (6) is rotatably connected to pulleys (5) near the four corners.

5. The aircraft engine thrust measurement device according to claim 1, characterized in that: A plurality of mounting holes (14) are provided at equal intervals on the surface of the mounting plate (7), and the mounting holes (14) are fixedly connected to the support block (13) via bolts (4).

6. The aircraft engine thrust measurement device according to claim 1, characterized in that: The installation position of the pressure gauge (16) corresponds to the setting position of the pressure column (15).

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