Aero-engine performance test board with dual-angle adjustment

Abstract

The utility model relates to an aero-engine performance test, and especially relates to a double-angle adjustable aero-engine performance test bench. Various attitudes of the engine can be accurately simulated when the unmanned aerial vehicle flies, so that the working performance of the engine is tested. Comprising a rack body, a turnover mechanism, a rotating mechanism and an engine fixing frame. The turnover mechanism is installed on the rack body through a left supporting frame and a right supporting frame, the turnover mechanism comprises a turnover shaft, the turnover shaft is rotationally connected to the tops of the two supporting frames and connected with the bearing platform, the left side and the right side of the bearing platform are each fixedly connected with a first supporting plate, and each first supporting plate is connected with a second supporting plate through a pin shaft; the bottom end of the second supporting plate is hinged to the supporting frame, and at least five pin holes are distributed in the second supporting plate and used for being matched with the corresponding pin holes in the first supporting plate, so that angle overturning is achieved, and the front-back inclination angle of the engine is adjusted. The rotating mechanism is fixed to the bearing platform of the turnover mechanism and used for adjusting the left-right inclination angle of the engine.

Description

TECHNICAL FIELD

[0001] The utility model relates to aero-engine performance test, especially a double angle adjustment's aero-engine performance test board. BACKGROUND

[0002] The fixed wing unmanned plane generates the thrust or pull force of the forward movement by the power device, and generates the lift by the fixed wing of the fuselage. The power of the heavy load fixed wing unmanned plane for cargo transportation is usually generated by the engine, and the engine performance is related to the dynamic performance, flight efficiency and other aspects of the whole unmanned plane. Therefore, it is of great significance to study the performance of the engine. The test bench of the engine is one of the important tools for testing the performance of the engine. The flight environment simulation experiment can be carried out by loading the engine and its gear box and other components, and then the performance of the engine is analyzed according to the obtained data, so as to provide a scientific basis for the overall research and improvement of the unmanned plane.

[0003] In the prior art, the patent for new type invention with publication number CN213456102U and the name of "a fuel cell engine testing device" proposes a method of connecting the lifting device and the driving transmission device, so that the performance of the fuel cell engine to be tested can be tested at different angles. However, since the engine generates a large torque and vibration during operation, the method of simultaneously adjusting the height and angle by connecting the lifting device and the bearing platform driving connection cannot accurately simulate the real working scene, and there will be a large deviation from the real data when testing the large engine.

[0004] The patent for new type invention with publication number CN215664037U and the name of "a small electric unmanned plane engine test bench" proposes a method of changing the height and angle of the engine by adjusting the four same lifting devices above the bearing platform, so that the performance of the engine can be tested at different angles. However, since the angle and height are adjusted at the same time every time, the angle obtained by adjusting needs to be further measured to determine, which is troublesome, and when measuring the performance of the large engine, the adjustment of the lifting device is more difficult, and it is not suitable for multi-angle performance test of the large engine. SUMMARY

[0005] The utility model is just in view of the defects existing in the prior art, provides a double angle adjustment's aero-engine performance test board. It can accurately simulate various postures of the engine during the flight of the unmanned plane, so as to test the working performance of the engine and confirm that each system can operate normally. The test bench has stable structure, simple operation and is easy to realize.

[0006] In order to achieve the above object, the utility model discloses the following technical scheme, a kind of dual-angle adjustment's aero-engine performance test bench, including rack main body, turnover mechanism, rotating mechanism, engine fixing frame.

[0007] The turnover mechanism is installed on the rack main body by left and right support frames, and the turnover mechanism includes a turnover shaft, which is rotatably connected to the top of the two support frames, and the turnover shaft is connected to the bearing platform, and the bearing platform has a first support plate fixed to each of its left and right sides, and each first support plate is connected to a second support plate by a pin shaft; the second support plate is hingedly connected to the support frame at its bottom end, and has at least five pin holes distributed on it for cooperating with the pin holes on the corresponding first support plates to achieve angle turnover and adjust the front and rear inclination angle of the engine.

[0008] The rotating mechanism is fixed to the bearing platform of the turnover mechanism to adjust the left and right inclination angle of the engine.

[0009] The engine fixing frame is connected to the rotating mechanism, and the front end of the engine fixing frame has four hole positions for fixing the measured engine.

[0010] Further, the dual-angle adjustment's aero-engine performance test bench also includes a parameter instrument table connected to the sensors by wires to display and record the engine performance data.

[0011] Further, the bottom of the rack main body is provided with two parallelly placed H-shaped steels, each of which has two vertical columns fixed thereto, and the two vertical columns are fixedly connected by an X-shaped support.

[0012] Further, the support frame adopts a triangular support structure, each triangular support structure corresponds to two vertical columns and is detachably connected to the corresponding vertical columns.

[0013] Further, the rotating mechanism includes a main shaft, a bearing, and a hollow cylindrical steel, the main shaft is located inside the hollow cylindrical steel, and the main shaft is rotatably connected to the hollow cylindrical steel by rolling bearings at both ends; the outer wall of the hollow cylindrical steel is connected to a strip-shaped connecting block, which is fixedly connected to the bearing platform by a pin hole; the engine fixing frame is connected to the main shaft of the rotating mechanism to adjust the left and right inclination angle of the engine.

[0014] Further, the engine fixing frame is connected to the main shaft of the rotating mechanism by a flange plate.

[0015] Further, a tension sensor is mounted at the rear end of the main shaft of the rotating mechanism, and the tension sensor is connected to the parameter instrument table by wires to measure the thrust generated by the engine.

[0016] Further, a torque sensor is mounted at the rear of the bearing platform for torque measurement; the torque sensor is connected to the parameter instrument table by wires to measure the torque of the engine.

[0017] Further, temperature sensors and pressure sensors are installed at the positions of the engine intake and exhaust manifolds respectively, and the temperature sensors and the pressure sensors are connected with the parameter instrument desk through wires, for measuring the intake and exhaust temperatures and air pressures.

[0018] Further, a speed sensor is arranged in front of the engine, and the speed sensor is connected with the parameter instrument desk through wires, for measuring the output speed of the engine.

[0019] Compared with the prior art, the utility model has the beneficial effects.

[0020] The utility model discloses the structure that overturning mechanism is associated with rotating mechanism makes overturning mechanism and rotating mechanism mutual cooperation adjustment measured engine left and right inclination angle and front and back inclination angle, to this to simulate the attitude when unmanned plane flies. When testing the performance of the measured aeroengine under different angles, only need to adjust overturning mechanism to carry out front and back inclination angle adjustment according to each direction deflection angle demand, then adjust rotating mechanism to carry out front and back inclination angle adjustment, utilize this adjustment mode to make the adjustment of engine inclination angle more accurate, more convenient. More accurately simulate the flight attitude of unmanned plane.

[0021] The utility model adopts the rack main body structure that four stands and support frame combination, make the main body more firm and stable, as far as possible reduce the influence that engine vibration and the pulling force produced by propeller rotation bring to experimental data accuracy, cooperate the flange disc connection mode of rotating mechanism front end, can be applicable to heavy load fixed wing unmanned plane's engine performance test. BRIEF DESCRIPTION OF DRAWINGS

[0022] The utility model makes further explanation in combination with the following drawings and specific embodiment. The utility model protection scope is not only limited to the following content's expression.

[0023] Figure 1 It is whole schematic diagram for test rack to load aeroengine.

[0024] Figure 2 It is test rack main body support schematic diagram.

[0025] Figure 3 It is overturning mechanism schematic diagram.

[0026] Figure 4 It is rotating mechanism schematic diagram.

[0027] Figure 5 It is rotating mechanism sectional view.

[0028] Figure 6 It is engine and other parts schematic diagram.

[0029] In the figure, 1 is a main body of the stand, 2 is an X-shaped support, 3 is a turnover mechanism, 4 is a rotating mechanism, 5 is an engine and its parts to be measured, and 6 is a parameter instrument table.

[0030] 7 is an I-shaped steel, and 8 is a support column.

[0031] 9 is a support beam, 10 is a cross beam, 11 is an engine fixing frame, 12 is a turnover shaft, 13 is a first support plate, 15 is a second support plate (used to adjust the front and rear inclination angles and fixed by different pin hole cooperation), 14 is a bearing platform of the turnover mechanism, 16 is a torque sensor, and 17 is a pull rod.

[0032] 18 is a rotating mechanism bearing platform, 19 is a tension sensor, 20 is a pull ring fixing support, 21 is a pull ring of the tension sensor, 22 is a flange plate, 23 is a fixed plate, 24 is a hollow cylindrical steel, and 25 is a strip-shaped connecting block.

[0033] 26 is a rolling bearing, 27 is a main shaft, and 36 is a main shaft bearing axial positioning plate.

[0034] 28 is an aero-engine to be measured, 29 is a rotating speed sensor, 30 is a temperature sensor, 31 is a pressure sensor (an air inlet temperature and pressure sensor are arranged at the same position on the left side of the engine), 32 is an engine exhaust manifold (an engine air inlet manifold is arranged at the same or position on the left side of the engine), 33 is an engine reduction gearbox, 34 is a propeller, and 35 is an overall support frame (four hole positions at the rear end thereof are used to cooperate with and install the engine fixing frame hole positions). DETAILED DESCRIPTION

[0035] In order to make the purpose, technical scheme and beneficial effects of the embodiments of the present application more clear, the technical scheme in the embodiments of the present application will be described clearly and completely in combination with the drawings in the embodiments of the present application. Obviously, the described embodiments are some embodiments of the present application, rather than all the embodiments of the present application.

[0036] As Figures 1-6The specific embodiment shown is a dual-angle-adjustable aero-engine performance test bench, which comprises a bench main body 1, a turnover mechanism 3, a rotating mechanism 4, an engine fixing frame 11 and a parameter instrument table 6. The turnover mechanism 3 is installed on the bench main body 1 through left and right support frames 9. The turnover mechanism 3 comprises a turnover shaft 12 which is rotatably connected to the top of the two support frames 9 and is connected with a bearing platform 14. The bearing platform 14 is a cross beam 10. The bearing platform 14 is fixed with a first support plate 13 on each of the left and right sides. Each first support plate 13 is connected with a second support plate 15 through a pin shaft. The bottom end of the second support plate 15 is hingedly connected to the support frame 9. The second support plate 15 is provided with at least five pin holes for cooperating with the pin holes on the corresponding first support plate 13 to realize angle turnover and adjust the front and rear inclination angle of the engine. The rotating mechanism 4 is fixed on the bearing platform 14 of the turnover mechanism 3 and is used for adjusting the left and right inclination angle of the engine. The engine fixing frame 11 is connected with the main shaft 27 of the rotating mechanism 4. The front end of the engine fixing frame 11 is provided with four hole positions for fixing the measured engine 28. The parameter instrument table 6 is connected with the sensor through a wire and is used for displaying and recording the engine performance data.

[0037] Preferably, the bottom of the bench main body 1 is provided with two parallel I-shaped steels 7. Each I-shaped steel 7 is fixed with two vertical columns 8. The two vertical columns 8 are auxiliary fixed through an X-shaped support.

[0038] Preferably, the support frame 9 adopts a triangular support structure, that is, the triangular support structure is composed of two oblique sides and a support beam 9 between the two oblique sides. Each triangular support structure corresponds to two vertical columns 8 and is detachably connected with the corresponding vertical column 8.

[0039] Preferably, the rotating mechanism 4 comprises a main shaft 27, a bearing 26 and a hollow cylindrical steel 24. The main shaft 27 is located in the hollow cylindrical steel 24 and is rotatably connected with the hollow cylindrical steel 24 through the rolling bearing 26 at both ends. The outer wall of the hollow cylindrical steel 24 is connected with a strip-shaped connecting block 25. The strip-shaped connecting block 25 is fixedly connected with the bearing platform 14 through a pin hole. The engine fixing frame 11 is connected with the main shaft 27 of the rotating mechanism 4 and is used for adjusting the left and right inclination angle of the engine.

[0040] Preferably, the engine fixing frame 11 is connected with the main shaft 27 of the rotating mechanism 4 through a flange plate 22.

[0041] Preferably, a tension sensor 19 is arranged at the rear end of the main shaft of the rotating mechanism. The tension sensor 19 is connected with the parameter instrument table 6 through a wire and is used for measuring the thrust generated by the engine.

[0042] Preferably, the torque sensor 16 is installed at the rear of the bearing platform 14 for torque measurement; the torque sensor 16 is connected to the parameter instrument table 6 through wires for measuring the torque of the engine. The temperature sensor 30 and the pressure sensor 31 are installed at the positions of the engine intake and exhaust manifolds respectively, and are connected to the parameter instrument table 6 through wires for measuring the intake and exhaust temperatures and air pressure. The speed sensor 29 is installed in front of the engine and is connected to the parameter instrument table 6 through wires for measuring the output speed of the engine.

[0043] Specifically, embodiment 1 includes a bench body, a fixed support, a turnover mechanism, a rotating mechanism, a fixed support, various sensors, a parameter instrument table, etc. The bench body and the fixed support are sufficient to bear the weight of the aircraft engine and its components to be tested, reducing the influence of the overall vibration and the pulling force generated by the propeller rotation on the accuracy of the experimental test data.

[0044] The lower end of the bench body is two parallel I-shaped steels, each of which is fixed with two columns, and the middle is fixed by a support frame, which is sufficient to bear a large weight and has very high stability.

[0045] The turnover mechanism is installed at the upper end of the bench body, and the upper end is connected with a bearing platform, and the two ends are connected with support plates, and the support plates are fixed with the turnover shaft through bearings, and the end of the support plate is provided with a pin hole. A strip-shaped support frame is arranged on the bench body perpendicular to the column direction, and 12 equidistant pin holes are arranged in the direction of the strip-shaped support frame. The 12 pin holes can cooperate with the pin holes at the ends of the support plates, representing 12 different deflection amounts (deflection range -30°-30°, and adjacent pin holes differ by 5°), to adjust the front and rear inclination angle of the engine.

[0046] The rotating mechanism comprises a main shaft, a bearing, a supporting cylindrical steel, a flange plate and a tension sensor. The rotating mechanism is fixed on the bearing platform of the overturning mechanism. When the overturning mechanism is adjusted to change the front and back inclination angle of the engine, the rotating mechanism will be driven to change the front and back inclination angle of the engine, so as to simulate the pitch angle of the unmanned aerial vehicle during take-off and landing. The bearing platform of the supporting cylindrical steel overturning mechanism has a rotating main shaft inside, which is matched with the external cylindrical steel through two end bearings. The rear end of the cylindrical steel has a square connecting block fixed on the main shaft, which is provided with a pin hole and fixed with the left end of the bearing platform of the overturning mechanism through the pin hole, and is used for adjusting and fixing the left and right inclination angle of the engine by the rotating mechanism, so as to simulate different flight attitudes of the unmanned aerial vehicle during flight. When the deflection angle of the measured engine is adjusted, the front and back inclination angle of the engine is first adjusted by the overturning mechanism, and then the left and right inclination angle of the engine is adjusted by the rotating mechanism after the front and back inclination angle of the engine is adjusted and fixed, so as to simulate different flight attitudes of the unmanned aerial vehicle during flight, especially the simulation of the pitch angle and the pitch angle flight attitude of the unmanned aerial vehicle during take-off and landing. Through accurate inclination angle simulation, the engine performance data under various states are obtained, and the working state of the engine is analyzed. The engine fixing frame is connected by a flange, which better adapts to the torque generated during deflection. Four hole positions are arranged at the front end of the flange, which are matched and fixed with the engine support to make the engine more fixed and reduce the influence of vibration on the measurement accuracy of the overall performance data.

[0047] Working process: simulate the airflow suffered in high altitude flight, then fix the measured engine 28 on the overall support frame 35, the engine transmission shaft cooperates with the reduction box 33, the propeller 34 is fixed on the output end of the reduction box, and the remaining parts are fixed on the engine. The overall support frame is fixed on the engine fixing frame 11 through four hole positions, the engine fixing frame is fixed with the rotating mechanism main shaft through the flange 22, rolling bearings are arranged at the two ends in the rotating mechanism, the deflection angle of the engine in the left-right direction is adjusted by adjusting the internal main shaft transmission, and the position is fixed through the strip-shaped connecting block 25 and the right end pull rod 17. The rotating mechanism is arranged on the turnover mechanism bearing platform 14, the turnover mechanism rotates with the main shaft, and drives the rotating mechanism and the measured engine fixed on the bearing platform to adjust the angle in the up-down direction, so that the flight attitude in the flight process of the unmanned aerial vehicle is simulated by cooperating and adjusting the deflection angles in the up-down and left-right directions, and then the engine performance data under different attitudes is measured. Four columns are supported below the crossbeam and are fixed through the support frame, the four columns are welded on the I-shaped steel, in order to avoid overturning, two columns are welded at the rear end and the middle position of the I-shaped steel. When the engine performance data is measured, the engine needs to be fixed on the engine fixing frame 11 first, then the pin hole of the turnover bracket 13 and 15 of the turnover mechanism is adjusted to cooperate with the hole position, the deflection angle in the up-down direction is adjusted, then the rotating mechanism connecting block 25 and the pull rod 17 are adjusted to adjust the deflection angle of the engine in the left-right direction, then the base is placed in a suitable position, and the engine is started to begin measurement.

[0048] The torque sensor 16 is arranged at the rear of the turnover mechanism bearing platform and is used for torque measurement, the tension sensor 19 is arranged at the rear of the rotating mechanism main shaft and is used for measuring the forward thrust generated by the engine, the temperature sensor 30 and the pressure sensor 31 are arranged at the positions of the engine intake and exhaust manifold respectively, and are used for measuring the intake and exhaust temperature and air pressure, and the speed sensor 29 in front of the engine is used for measuring the output speed of the engine. The other ends of the various sensors are connected with corresponding instrument panels on the parameter instrument table 6, so that various engine performance data can be observed and recorded.

[0049] If it is required to change the simulated unmanned aerial vehicle flight attitude and test the engine performance under different flight attitudes of the unmanned aerial vehicle, the turnover mechanism and the rotating mechanism need to be adjusted according to requirements to reach the required simulation angle for testing, and measurement data recording is well done.

[0050] In the description of the specification, the description of the terms "one embodiment", "some embodiments", "exemplary embodiment", "preferred embodiment", "specific implementation", or "preferred implementation" and the like means that the specific features, structures, materials or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the utility model. In the description, the exemplary description of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0051] The above embodiments are only used to illustrate the technical solutions of the utility model, not to limit them; although the utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that; it can still modify the technical solutions recorded in the foregoing embodiments, or make equivalent replacement to part or all of the technical features; thus, these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the range defined by the utility model claims.

Claims

1. A dual angle adjustable aeroengine performance test bench, characterized in that, The test bench comprises a bench body (1), a turnover mechanism (3), a rotating mechanism (4), and an engine fixing frame (11); The turnover mechanism (3) is installed on the bench body (1) through left and right support frames (9), and comprises a turnover shaft (12) which is rotatably connected to the top of the two support frames (9) and is connected with a bearing platform (14). The bearing platform (14) is fixedly connected with first support plates (13) on the left and right sides, and each first support plate (13) is connected with a second support plate (15) through a pin shaft. The bottom end of the second support plate (15) is hingedly connected to the support frame (9), and the second support plate (15) is provided with at least five pin holes for cooperating with the pin holes on the corresponding first support plate (13) to realize angle turnover and adjust the front and rear inclination angle of the engine. The rotating mechanism (4) is fixed on the bearing platform (14) of the turnover mechanism (3) and is used for adjusting the left and right inclination angle of the engine. The engine fixing frame (11) is connected with the rotating mechanism (4), and the front end of the engine fixing frame (11) is provided with four hole positions for fixing the measured engine (28).

2. The dual angle-adjustable aeroengine performance test bench according to claim 1, characterized in that, The double-angle-adjustable aero-engine performance test bench further comprises a parameter instrument table (6) connected with the sensors through wires and used for displaying and recording the engine performance data.

3. The dual angle-adjustable aeroengine performance test bench according to claim 1, characterized in that, The bottom of the bench body (1) is provided with two parallel I-shaped steels (7), and each I-shaped steel (7) is fixedly provided with two vertical columns (8) which are fixedly connected through an X-shaped support.

4. The dual angle-adjustable aeroengine performance test bench according to claim 3, characterized in that, The support frame (9) adopts a triangular support structure, each triangular support structure corresponds to two vertical columns (8) and is detachably connected with the corresponding vertical column (8).

5. The dual angle-adjustable aeroengine performance test bench of claim 1, wherein, The rotating mechanism (4) comprises a main shaft (27), a bearing (26), and a hollow cylindrical steel (24). The main shaft (27) is located in the hollow cylindrical steel (24), and the two ends of the main shaft (27) are rotatably connected with the hollow cylindrical steel (24) through rolling bearings (26). The outer wall of the hollow cylindrical steel (24) is connected with a strip-shaped connecting block (25), the strip-shaped connecting block (25) is fixedly connected with the bearing platform (14) through a pin hole. The engine fixing frame (11) is connected with the main shaft (27) of the rotating mechanism (4) and is used for adjusting the left and right inclination angle of the engine.

6. The dual angle-adjustable aeroengine performance test bench according to claim 5, characterized in that, The engine fixing frame (11) is connected with the main shaft (27) of the rotating mechanism (4) through a flange (22).

7. The dual angle-adjustable aeroengine performance test bench according to claim 6, characterized in that, A tension sensor (19) is arranged at the rear end of the main shaft of the rotating mechanism, and the tension sensor (19) is connected with the parameter instrument table (6) through wires and is used for measuring the thrust generated by the engine.

8. The dual angle-adjustable aeroengine performance test bench of claim 2, wherein, A torque sensor (16) is arranged at the rear of the bearing platform (14) and is used for torque measurement. The torque sensor (16) is connected with the parameter instrument table (6) through wires and is used for measuring the torque of the engine.

9. The dual angle-adjustable aeroengine performance test bench according to claim 2, characterized in that, Temperature sensors (30) and pressure sensors (31) are arranged at the positions of the engine intake and exhaust manifolds, respectively. The temperature sensors (30) and the pressure sensors (31) are connected with the parameter instrument table (6) through wires and are used for measuring the intake and exhaust temperatures and air pressures.

10. The dual angle adjustable aeroengine performance test bed of claim 2, wherein, The engine is provided with a speed sensor (29) in front of the engine, which is connected with the parameter instrument desk (6) through a wire, and is used for measuring the output speed of the engine.

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