Universal aero-engine test bed

Abstract

According to the universal test bed for the aero-engine, the radial sliding device and the axial sliding device are arranged on the fixed platform, the position can be adjusted in the axial direction and the radial direction of the aero-engine, and therefore it is guaranteed that various types of aero-engines of different sizes are fixed, and the universality of the test bed is high. The test bed is provided with the force measuring platform which can test the thrust of the aero-engine, and is provided with the weighing sensor for the oil drum, so that the fuel consumption of the aero-engine is tested.

Description

Technical Field

[0001] The utility model belongs to the technical field of aero-engine test stands, and particularly relates to a general-purpose aero-engine test stand. Background Art

[0002] An aero-engine is a highly complex and precise thermal machine. To ensure the normal operation of the aero-engine and the stable flight of the aircraft, it is necessary to test the characteristics of the engine during the test phase. Currently, the aero-engine is usually placed on a test stand for testing.

[0003] Relevant technicians engaged in aero-engine testing have found during actual work that a single test frame is only applicable to engines with specific size specifications and does not have universality. Moreover, there is usually a lack of a pressure test structure, making it difficult to quickly test the pressure generated by the aero-engine on the test object when working on the test stand. Summary of the Invention

[0004] In view of this, the purpose of the utility model is to provide a general-purpose aero-engine test stand to at least solve one of the problems existing in the background art.

[0005] The present application provides a general-purpose aero-engine test stand, including:

[0006] A support frame, which is used to be fixed on the ground;

[0007] A force-measuring platform, which is arranged on the support frame and is used for thrust testing when the aero-engine is tested;

[0008] A fixed platform, which is arranged on the force-measuring platform;

[0009] A display screen, which is arranged on the support frame and is used for displaying thrust test data;

[0010] Wherein, the fixed platform includes:

[0011] A supporting plate, which is arranged on the force-measuring platform;

[0012] A radial sliding device, which is arranged on the supporting plate and can slide on the supporting plate, and its sliding direction is perpendicular to the axial direction of the aero-engine;

[0013] An axial sliding device, which is arranged on the radial sliding device and can slide along the axial direction of the aero-engine, and the axial sliding device is used to fix the aero-engine.

[0014] Further, the support frame includes:

[0015] The first structural frame, which includes four vertical rods and several cross rods connecting the four vertical rods, is used to support the aeroengine;

[0016] The second structural frame is connected to one side of the first structural frame axially relative to the aeroengine. The second structural frame includes at least two vertical rods, several cross rods and several reinforcing beams. The two vertical rods are connected to the first structural frame through each cross rod, and several of the reinforcing beams are arranged between the cross rods of the second structural frame.

[0017] Further, a floor socket is provided at the bottom end of each vertical rod, and each floor socket is used to be connected to the ground.

[0018] Further, corner brackets are installed at the joints of each vertical rod, cross rod and reinforcing beam.

[0019] Further, the force measuring platform includes:

[0020] A support plate, which is arranged on the support frame;

[0021] Four positioning seats, with two of the positioning seats as a group. The two positioning seats in each group are arranged axially along the aeroengine on the support plate;

[0022] Guide rails, with two of the guide rails respectively arranged on the two positioning seats in each group;

[0023] Moving seats, with two of the moving seats both slidingly arranged on each guide rail;

[0024] A pressure sensor, which is arranged on the support plate, is used to measure the thrust in the axial direction of the aeroengine and is electrically connected to the display screen.

[0025] Further, the radial sliding device includes:

[0026] Four limiting seats, with two of the limiting seats as a group. The two limiting seats in each group are arranged radially along the aeroengine on the supporting plate;

[0027] Limiting shafts, with two of the limiting shafts respectively arranged on the two limiting seats in each group;

[0028] Moving seats, with two of the moving seats both slidingly arranged on each limiting shaft.

[0029] Further, the axial sliding device includes:

[0030] Four fixed seats, with two of the fixed seats as a group. The two fixed seats in each group are arranged axially;

[0031] Slide rails, two of the slide rails are respectively arranged on two of the fixing seats of each group;

[0032] Sliders, two of the sliders are both slidably arranged on the slide rails of each group;

[0033] Adapter plates, one of the adapter plates is arranged on each of the sliders, and the adapter plates are used to connect the mounting lugs and the hoops of the aeroengine.

[0034] Further, it further includes:

[0035] A weighing sensor, which is arranged on the support frame and is electrically connected to the display screen;

[0036] An oil barrel, which is arranged on the weighing sensor and is used to provide energy for the aeroengine.

[0037] Further, it further includes:

[0038] A triangular plate, which connects the moving seat of the adjacent radial sliding device and the slider of the axial sliding device.

[0039] The beneficial effects of the present application:

[0040] The general-purpose aeroengine test stand provided by the present application is provided with a radial sliding device and an axial sliding device on the fixed platform, which can adjust the position in the axial and radial directions of the aeroengine, so as to ensure the fixation of various types of aeroengines with different sizes, making the test stand highly versatile. A force measuring platform is arranged on the test stand to test the thrust of the aeroengine, and a weighing sensor for the oil barrel is arranged, so as to realize the test of the fuel consumption of the aeroengine. Description of the Drawings

[0041] Through the following description of the embodiments of the present invention with reference to the drawings, the above and other objects, features and advantages of the present invention will become clearer.

[0042] Figure 1 is a three-dimensional structural schematic diagram of a general-purpose aeroengine test stand equipped with an aeroengine according to an embodiment of the present invention;

[0043] Figure 2 is according to an embodiment of the present invention Figure 1 Another perspective three-dimensional structural schematic diagram;

[0044] Figure 3 is a structural schematic diagram of the aeroengine to be tested according to an embodiment of the present invention;

[0045] Figure 4 is a three-dimensional structural schematic diagram of a general-purpose aeroengine test stand according to an embodiment of the present invention;

[0046] Figure 5 It is a partial three-dimensional structural schematic diagram of a general aviation engine test stand provided according to an embodiment of the present invention.

[0047] Among them,

[0048] 1. Aviation engine; 2. Hoop; 3. Mounting section; 4. Adapter plate; 5. Slide block; 6. Slide rail; 7. Fixed seat; 8. Moving seat; 9. Triangular plate; 10. Limit shaft; 11. Limit seat; 12. Support plate; 13. Movable seat; 14. Guide rail; 15. Positioning seat; 16. Support board; 17. Pressure sensor; 18. Support frame; 19. Floor seat; 20. Angle code; 21. First structural frame; 22. Partition board; 23. Display screen; 24. Weighing sensor; 25. Oil barrel; 26. Cross bar; 27. Second structural frame; 28. Reinforcing beam. Specific embodiments

[0049] The various embodiments of the present invention will be described in more detail below with reference to the accompanying drawings. In each of the drawings, the same elements are denoted by the same or similar reference numerals. For the sake of clarity, the various parts in the drawings are not drawn to scale.

[0050] Referring to Figures 1 to 5 , the present application provides a general aviation engine test stand, including: a support frame 18, which is used to be fixed on the ground and support the aviation engine 1; a force measuring platform, which is arranged on the support frame 18 and is used for thrust testing when the aviation engine 1 is tested; a fixed platform, which is arranged on the force measuring platform; a display screen 23, which is arranged on the support frame 18 and is used for displaying thrust test data; among them, the fixed platform includes: a support plate 12, which is arranged on the force measuring platform; a radial sliding device, which is arranged on the support plate 12 and can slide on the support plate 12, and its sliding direction is perpendicular to the axial direction of the aviation engine 1; an axial sliding device, which is arranged on the radial sliding device and can slide along the axial direction of the aviation engine 1, and the axial sliding device is used to fix the aviation engine 1.

[0051] Referring to Figure 4 and Figure 5, the support frame 18 includes: a first structural frame 21, which includes four vertical rods and several crossbars 26 connecting the four vertical rods, and is used to support the aero-engine 1; a second structural frame 27, which is connected to one side of the first structural frame 21 in the axial direction relative to the aero-engine 1. The second structural frame 27 includes at least two vertical rods, several crossbars 26 and several reinforcing beams 28. The two vertical rods are connected to the first structural frame 21 through the respective crossbars 26, and several of the reinforcing beams 28 are arranged between the respective crossbars 26 of the second structural frame 27. The first structural frame 21 is mainly used to support and install the aero-engine 1 and other related equipment, and the second structural frame 27 is arranged in the thrust action direction of the aero-engine 1, and is mainly used to improve the stability of the aero-engine 1 during the test run.

[0052] The bottom end of each of the vertical rods is provided with a floor socket 19, and each of the floor sockets 19 is used to be connected to the ground. Each of the floor sockets 19 can be bolted to the ground to ensure the stability during the test run.

[0053] In this embodiment, angle codes 20 are installed at the joints of each of the vertical rods, crossbars 26 and reinforcing beams 28. The angle codes 20 can enhance the structural strength of each joint of the support frame 18 and ensure the connection stability.

[0054] In this embodiment, referring to Figure 5 , the force measuring platform includes: a support plate 16, which is arranged on the support frame 18; four positioning seats 15, with two of the positioning seats 15 as a group, and the two positioning seats 15 of each group are arranged on the support plate 16 along the axial direction of the aero-engine 1; guide rails 14, with the two guide rails 14 respectively arranged on the two positioning seats 15 of each group; movable seats 13, with the two movable seats 13 both slidingly arranged on each of the guide rails 14; a pressure sensor 17, which is arranged on the support plate 16, is used to measure the thrust in the axial direction of the aero-engine 1, and is electrically connected to the display screen 23.

[0055] The pressure sensor 17 is installed in the pressure sensing component, and further includes a fixing component and a moving force receiving component. The pressure sensor 17 is arranged between the fixing component and the moving force receiving component. The fixing component is fixed on the force measuring platform, and the moving force receiving component is connected to the fixed platform. During the test run, the fixed platform moves along the axial direction of the aero-engine 1 under the action of the aero-engine 1, and then drives the moving force receiving component to move by the fixed platform, so that the thrust acts on the pressure sensor 17, realizing the test of the test run thrust of the aero-engine 1.

[0056] The oil barrel 26, the weighing sensor 24, the display screen 23, etc. can all be installed on the partition plate 22 arranged on the support frame 18.

[0057] In this embodiment, Figures 1 to 4, the radial sliding device includes: four limit seats 11, with two of the limit seats 11 as a group, and the two limit seats 11 in each group are arranged along the radial direction of the aeroengine 1 on the supporting plate 12; limit shafts 10, with two of the limit shafts 10 respectively arranged on the two limit seats 11 in each group; moving seats 8, with two of the moving seats 8 both slidably arranged on the respective limit shafts 10.

[0058] The axial sliding device includes: four fixed seats 7, with two of the fixed seats 7 as a group, and the two fixed seats 7 in each group are arranged along the axial direction of the aeroengine 1, and each fixed seat 7 is respectively arranged on a corresponding limit seat 11; slide rails 6, with two of the slide rails 6 respectively arranged on the two fixed seats 7 in each group; sliders 5, with two of the sliders 5 both slidably arranged on the slide rails 6 in each group; adapter plates 4, with one of the adapter plates 4 arranged on each of the sliders 5, and the adapter plates 4 are used to connect the mounting lugs 3 and the hoop 2 of the aeroengine 1.

[0059] In an alternative embodiment, the limit seats 11 are fixed to the supporting plate 12 by bolts, and the fixed seats 7 are fixed to the moving seats 8 by bolts.

[0060] The general-purpose aeroengine test bench further includes: a load cell 24, which is arranged on the support frame 18 and electrically connected to the display screen 23; an oil barrel 26, which is arranged on the load cell 24 and used to provide energy for the aeroengine 1. It can be understood that the oil barrel 26 stores the fuel required by the aeroengine 1, and the fuel consumption can be known through the load cell 24. The fuel consumption is related to the test time, the test thrust magnitude, etc., which will not be elaborated here.

[0061] The general-purpose aeroengine test bench further includes: a triangular plate 9, which connects the moving seat 8 of the adjacent radial sliding device and the slider 5 of the axial sliding device. As those skilled in the art should understand, the triangular plate 9 is for facilitating the operator to adjust the distance between the limit seats 11 in each group, and also to adjust the distance between the sliders 5 in different groups, that is, by adjusting the spacing, the installation and fixation of aeroengines 1 with different diameters can be achieved. By adjusting the spacing between the sliders 5 in the same group, the installation and fixation of aeroengines 1 with different lengths can be achieved.

[0062] For the general-purpose aeroengine test bench provided by the present application, a radial sliding device and an axial sliding device are arranged on the fixed platform, which can adjust the position in the axial and radial directions of the aeroengine 1, thus ensuring the fixation of various types of aeroengines 1 with different sizes, making the test bench highly versatile. A force measuring platform is arranged on the test bench to test the thrust of the aeroengine 1, and a load cell 24 for the oil barrel 26 is arranged, thereby realizing the test of the fuel consumption of the aeroengine 1.

[0063] It should be noted that in this text, relational terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the term "comprising", "including" or any other variant thereof is intended to cover non-exclusive inclusion, so that a process, method, article or device comprising a series of elements not only includes those elements, but also includes other elements not expressly listed, or also includes elements inherent to such process, method, article or device. Without further limitation, an element defined by the statement "comprising an..." does not exclude the presence of additional identical elements in the process, method, article or device comprising the said element.

[0064] Finally, it should be noted that: Obviously, the above embodiments are only examples given for clearly illustrating the present utility model, rather than limitations on the implementation manners. For those of ordinary skill in the art, other different forms of changes or modifications can be made based on the above description. It is not necessary and impossible to list all the implementation manners here. And the obvious changes or modifications derived therefrom are still within the protection scope of the present utility model.

Claims

1. A general-purpose aircraft engine test bench, characterized in that: include: A support frame, which is used to be fixed on the ground and support the aircraft engine; A force measuring platform, which is arranged on the support frame and is used for thrust testing of the aircraft engine during test run; A fixed platform, which is arranged on the force measuring platform; A display screen, which is arranged on the support frame and is used to display thrust test data; Among them, the fixed platform includes: A supporting plate, which is arranged on the force measuring platform; A radial sliding device, which is arranged on the supporting plate and can slide on the supporting plate, and its sliding direction is perpendicular to the axial direction of the aircraft engine; An axial sliding device is arranged on the radial sliding device and can slide along the axial direction of the aircraft engine. The axial sliding device is used to fix the aircraft engine.

2. The universal aircraft engine test bench according to claim 1, characterized in that: The support frame comprises: A first structural frame, comprising four vertical poles and a plurality of horizontal poles connecting the four vertical poles, for supporting the aircraft engine; The second structural frame is connected to one side of the first structural frame relative to the axial direction of the aircraft engine. The second structural frame includes at least two vertical poles, a plurality of cross bars and a plurality of reinforcing beams. The two vertical poles are connected to the first structural frame via the cross bars. The plurality of reinforcing beams are arranged between the cross bars of the second structural frame.

3. The universal aircraft engine test bench according to claim 2, characterized in that: The bottom end of each upright pole is provided with a ground anchor, and each ground anchor is used for connecting to the ground.

4. The universal aircraft engine test bench according to claim 2, characterized in that: Angle brackets are installed at the connection points of each of the vertical poles, horizontal poles and reinforcing beams.

5. The universal aircraft engine test bench according to claim 1, characterized in that: The force measuring platform comprises: A support plate, which is arranged on the support frame; Four positioning seats, two of which form a group, and the two positioning seats in each group are distributed on the support plate along the axial direction of the aircraft engine; Guide rails, two of the guide rails are respectively arranged on the two positioning seats of each group; A movable seat, wherein two movable seats are slidably disposed on each of the guide rails; The pressure sensor is arranged on the support plate, is used to measure the thrust of the aircraft engine in the axial direction, and is electrically connected to the display screen.

6. The universal aircraft engine test bench according to claim 1, characterized in that: The radial sliding device comprises: Four limit seats, two of which form a group, and two of which in each group are distributed on the support plate along the radial direction of the aircraft engine; A limiting shaft, wherein two limiting shafts are respectively arranged on the two limiting seats of each group; The two movable seats are slidably arranged on the respective limiting shafts.

7. The universal aircraft engine test bench according to claim 1, characterized in that: The axial sliding device comprises: Four fixing seats, two of which form a group, and two of which in each group are distributed along the axial direction of the aircraft engine; Slide rails, two of the slide rails are respectively arranged on the two fixed seats of each group; Slide blocks, two of which are slidably disposed on the slide rails of each group; An adapter plate is provided on each of the slide blocks, and the adapter plate is used to connect the mounting section and the clamp of the aircraft engine.

8. The universal aircraft engine test bench according to claim 1, characterized in that: Also includes: A weighing sensor, which is arranged on the supporting frame and electrically connected to the display screen; The oil drum is arranged on the weighing sensor and is used to provide energy for the aircraft engine.

9. The universal aircraft engine test bench according to claim 1, characterized in that: Also includes: A triangular plate connects the adjacent moving seats of the radial sliding device and the sliding blocks of the axial sliding device.

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