Test bed for small gas turbine engine

Abstract

The invention relates to the technical field of aero-engine testing, and discloses a test bed for a small gas turbine engine. The test bed comprises a bottom table, a top table, a mounting table capable of horizontally moving away from or close to the top table, a semi-enclosed mounting joint used for mounting the small gas turbine engine, an air inlet pipe and an adapter pipe connected with the air outlet end of the air inlet pipe and the air inlet end of the small gas turbine engine. The pressure sensor and the force penetrating rod are used for detecting the thrust of the small gas turbine engine; through the semi-surrounded mounting frame and the three ejector rods capable of adjusting the positions, the mounting frame is arranged on the small gas turbine engine in a surrounding mode, the three ejector rods support and fix the small gas turbine engine in a three-point mode, and simulation of mounting of the engine on an aircraft can be achieved; the purpose of completely examining the engine can be achieved during test run; and small gas turbine engines of different specifications can be supported and fixed, and the beneficial effects of being high in practicability and universality are achieved.

Description

Technical Field

[0001] The present invention relates to the technical field of aeroengine testing, and particularly relates to a test stand for a small gas turbine engine. Background Technique

[0002] At present, small gas turbine engines are widely used in modern aircraft, such as auxiliary power units of large aircraft, missile power units, and UAV power. Due to their small structural size and short service life, etc., the overall structural design concept has unique features compared with large aero-turbine jet engines. For example, in the design of engine mounting lugs, small engines often use a three-point encircling mounting lug to be installed on the aircraft, while large engines often use front and rear mounting lugs to be suspended on the aircraft. Therefore, the test stand for large turbojet engines is not suitable for testing such small engines, and a test stand suitable for the structure of small engines needs to be designed for testing.

[0003] Most of the small engine test stands on the market at present are simple fixed brackets, with poor structural applicability, unable to be applicable to the testing of multiple engines, and the mounting method of the test stand cannot simulate the installation of the engine on the aircraft, so the purpose of fully evaluating the engine cannot be achieved during the test. Therefore, we propose a test stand for a small gas turbine engine. Summary of the Invention

[0004] The main purpose of the present invention is to provide a test stand for a small gas turbine engine. Through a semi-enclosed mounting frame and a push rod whose position can be adjusted, the installation of the engine on the aircraft can be simulated, and it has the advantages of high practicability and high versatility, and can effectively solve the problems in the background technique.

[0005] To achieve the above purpose, the technical solution adopted by the present invention is as follows:

[0006] A test stand for a small gas turbine engine, including a bottom platform, on the top end of the bottom platform, a sliding support structure and a top platform are fixedly installed. The sliding support structure is arranged on one side of the top platform, and there are two sliding support structures arranged in parallel. On the top ends of the two sliding support structures, an installation platform is commonly installed. On the top end of the installation platform, two parallel support plates are fixedly connected. On one ends of the two support plates facing the top platform, support frames are respectively fixedly connected. Between the two support frames, an installation ring is commonly fixedly connected. At one end of the installation ring, an air inlet pipe is fixedly connected. At the other end of the installation ring, a rotary connection pipe is fixedly connected. On one ends of the two support plates far from the top platform, a mounting lug is commonly installed. The rotary connection pipe is arranged between the mounting lug and the air inlet pipe, and the air outlet direction of the air inlet pipe points to the rotary connection pipe; on one end of the installation platform facing the top platform, a mounting seat is fixedly connected. At the end of the mounting seat far from the installation platform, a force transmission rod is fixedly connected. On one end of the top platform facing the installation platform, a pressure sensor is fixedly connected, and the pressure sensor cooperates with the force transmission rod.

[0007] Preferably, the sliding support structure includes a first support and a second support. The first support is arranged on one side of the second support and close to the top platform. A sliding rod is fixedly connected to both the first support and the second support. The sliding rod is perpendicular to the top platform. A first sliding platform and a second sliding platform are slidably sleeved on the sliding rod. Both the first sliding platform and the second sliding platform are arranged between the first support and the second support and are fixed to the bottom end of the installation platform.

[0008] Preferably, the installation section includes an installation frame and an adjustment plate. The installation frame is a semi-enclosed structure, and the inner side surface of the installation frame is an arc surface. A cushion block is fixedly connected to the inner side surface of the installation frame. A top rod is arranged on the cushion block. One end of the top rod penetrates through the end of the cushion block away from the installation frame, and the other end of the top rod penetrates through the cushion block and the installation frame and is fixedly connected to an adjustment rod. Two fixing plates are fixedly connected to the outer side surface of the installation frame, and the two fixing plates are respectively fixed to the two support plates; the adjustment plate is arranged outside the installation frame and is connected to the installation frame through bolts, and the adjustment plate cooperates with the adjustment rod.

[0009] Preferably, an adjustment groove is formed on the outer peripheral side surface of the adjustment rod. The adjustment groove is an annular groove and is arranged along the circumferential direction of the adjustment rod. A clamping groove is formed on the adjustment plate. The clamping groove cooperates with the adjustment groove and forms a clamping structure.

[0010] Preferably, a plurality of adjustment grooves are provided, and the plurality of adjustment grooves are equidistantly arranged at intervals along the axial direction of the adjustment rod.

[0011] Preferably, a limit seat is installed at the top end of the bottom platform, and the limit seat cooperates with the end of the installation platform away from the top platform.

[0012] Compared with the prior art, the present invention has the following beneficial effects:

[0013] 1. The installation and fixation of a small gas turbine engine are carried out through the cooperation of a semi-enclosed installation frame and three top rods. The installation frame surrounds the small gas turbine engine, and the three top rods form three-point support and fixation for the small gas turbine engine, realizing the simulation of the installation of the engine on the aircraft, so that the purpose of fully evaluating the engine can be achieved during the test run.

[0014] 2. By providing an adjustment rod and an adjustment plate, and arranging a plurality of adjustment grooves on the adjustment rod and a clamping groove cooperating with the adjustment grooves on the adjustment plate, the clamping groove can be inserted into the adjustment grooves at different positions. By inserting the clamping groove into different adjustment grooves, the distance from the end of the top rod connected to the small gas turbine engine to the inner side surface of the installation frame is adjusted, so that the top rod can support and fix small gas turbine engines of different specifications, increasing the practicability and versatility. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1This is the overall structure diagram of a test bench for a small gas turbine engine of the present invention;

[0016] Figure 2 This is the overall structure schematic diagram of a test bench for a small gas turbine engine of the present invention from another perspective;

[0017] Figure 3 This is the structure schematic diagram of the sliding support structure of a test bench for a small gas turbine engine of the present invention;

[0018] Figure 4 This is the structure schematic diagram of the mounting lug of a test bench for a small gas turbine engine of the present invention;

[0019] Figure 5 This is the structure schematic diagram of the adjusting rod of a test bench for a small gas turbine engine of the present invention;

[0020] Figure 6 This is the partial structure schematic diagram of the adjusting plate of a test bench for a small gas turbine engine of the present invention.

[0021] In the figure: 1, bottom platform; 2, sliding support structure; 3, top platform; 4, mounting platform; 5, support plate; 6, mounting lug; 7, support frame; 8, mounting ring; 9, adapter pipe; 10, intake pipe; 11, mounting seat; 12, force transmission rod; 13, pressure sensor; 14, limit seat; 21, first support; 22, second support; 23, sliding rod; 24, first sliding table; 25, second sliding table; 61, mounting frame; 62, spacer; 63, ejector rod; 64, adjusting rod; 641, adjusting groove; 65, adjusting plate; 651, clamping groove; 66, fixing plate. Detailed implementation manners

[0022] To make the technical means, creative features, achieved purposes and functions of the present invention easy to understand, the present invention will be further described below in conjunction with the detailed implementation manners.

[0023] In the description of the present invention, it should be noted that the orientation or positional relationship indicated by the terms "upper", "lower", "inner", "outer", "front end", "rear end", "both ends", "one end", "the other end", etc. is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present invention. In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance.

[0024] In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, terms such as "installation", "equipped with", "connection", etc. should be understood in a broad sense. For example, "connection" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0025] As Figure 1-6 shown, a test bench for a small gas turbine engine includes a bottom platform 1. A sliding support structure 2 and a top platform 3 are fixedly installed at the top of the bottom platform 1. The sliding support structure 2 is arranged on one side of the top platform 3. There are two sliding support structures 2 and they are arranged in parallel. An installation platform 4 is commonly installed at the tops of the two sliding support structures 2. The installation platform 4 can move horizontally away from or close to the top platform 3. Two parallel support plates 5 are fixedly connected to the top of the installation platform 4. At one end of the two support plates 5 facing the top platform 3, support frames 7 are respectively fixedly connected. An installation ring 8 is commonly fixedly connected between the two support frames 7. An air inlet pipe 10 is fixedly connected to one end of the installation ring 8. A transfer pipe 9 is fixedly connected to the other end of the installation ring 8. An installation joint 6 is commonly installed at one end of the two support plates 5 away from the top platform 3. The transfer pipe 9 is arranged between the installation joint 6 and the air inlet pipe 10. The air outlet direction of the air inlet pipe 10 points to the transfer pipe 9. An installation seat 11 is fixedly connected to one end of the installation platform 4 facing the top platform 3. A force transmission rod 12 is fixedly connected to the end of the installation seat 11 away from the installation platform 4. A pressure sensor 13 is fixedly connected to one end of the top platform 3 facing the installation platform 4. The pressure sensor 13 cooperates with the force transmission rod 12.

[0026] In the above technical solution, the installation joint 6 is used to fix the small gas turbine engine. The transfer pipe 9 cooperates with the air inlet of the small gas turbine engine. The air entering from the air inlet pipe 10 enters the small gas turbine engine through the transfer pipe 9. When conducting the test run operation of the small gas turbine engine, under the action of the reaction force formed by the jet of the small gas turbine engine, the installation platform 4 moves towards the top platform 3, causing the force transmission rod 12 to abut against the pressure detection end of the pressure sensor 13 to obtain a pressure value. And as the reaction force formed by the jet of the small gas turbine engine increases, the pressure value detected by the pressure sensor 13 increases synchronously. When the reaction force formed by the jet of the small gas turbine engine reaches the maximum value, the pressure value detected by the pressure sensor 13 reaches the maximum value. The thrust of the small gas turbine engine is reflected by the pressure value detected by the pressure sensor 13.

[0027] As a further illustration of the above technical solution, the sliding support structure 2 includes a first support 21 and a second support 22. Both the first support 21 and the second support 22 are fixed to the top end of the base 1. The first support 21 is arranged on one side of the second support 22 and close to the top platform 3. A sliding rod 23 is fixedly connected to both the first support 21 and the second support 22. The sliding rod 23 is perpendicular to the top platform 3. A first sliding platform 24 and a second sliding platform 25 are slidably sleeved on the sliding rod 23. Both the first sliding platform 24 and the second sliding platform 25 are arranged between the first support 21 and the second support 22 and are fixed to the bottom end of the mounting platform 4. The first sliding platform 24 and the second sliding platform 25 can both move linearly away from or towards the top platform 3 on the sliding rod 23, so that the mounting platform 4 can move away from or towards the top platform 3.

[0028] It should be noted that when the force transmission rod 12 contacts the pressure sensor 13, neither the first sliding platform 24 nor the second sliding platform 25 contacts the first support 21 or the second support 22, so as to ensure the accuracy of the pressure value detected by the pressure sensor 13.

[0029] The mounting section 6 includes a mounting frame 61 and an adjusting plate 65. The mounting frame 61 is a semi-enclosed structure, and the inner side surface of the mounting frame 61 is an arc surface. A cushion block 62 is fixedly connected to the inner side surface of the mounting frame 61. A jacking rod 63 is arranged on the cushion block 62. One end of the jacking rod 63 penetrates through the end of the cushion block 62 away from the mounting frame 61, and the other end of the jacking rod 63 penetrates through the cushion block 62 and the mounting frame 61 and is fixedly connected to an adjusting rod 64. The adjusting plate 65 is arranged outside the mounting frame 61 and is connected to the mounting frame 61 by bolts. The adjusting plate 65 cooperates with the adjusting rod 64. When the small gas turbine engine is fixed through the mounting section 6, the small gas turbine engine is arranged inside the mounting frame 61 and abuts against the jacking rod 63.

[0030] The adjusting plate 65, the cushion block 62, the jacking rod 63 and the adjusting rod 64 are provided in the same number and at least three are provided. When the number of them is three, the three cushion blocks 62 are distributed in a Y shape and arranged along the circumferential direction of the inner side surface of the mounting frame 61, and two of the cushion blocks 62 are respectively close to the two ends of the mounting frame 61. Through the above, the three jacking rods 63 form a Y-shaped three-point support for the small gas turbine engine, so as to ensure the stability of the support and fixation of the small gas turbine engine.

[0031] An adjustment groove 641 is formed on the outer peripheral side surface of the adjustment rod 64. The adjustment groove 641 is an annular groove and is arranged along the circumferential direction of the adjustment rod 64. There are a plurality of adjustment grooves 641, and the plurality of adjustment grooves 641 are equidistantly arranged at intervals along the axial direction of the adjustment rod 64. A clamping groove 651 is formed on the adjustment plate 65. The clamping groove 651 cooperates with the adjustment groove 641 to form a clamping structure. The clamping groove 651 can be inserted into the adjustment grooves 641 at different positions. Through the above, after removing the bolt connecting the adjustment plate 65 and the mounting bracket 61, the clamping groove 651 is inserted into the adjustment groove 641 at other positions, and the adjustment plate 65 is made to abut against the outer side surface of the mounting bracket 61 again. Since the relative positions of the adjustment plate 65 and the adjustment rod 64 change after the clamping groove 651 is inserted into another adjustment groove 641, the distance from the end of the ejector rod 63 connected to the small gas turbine engine to the inner side surface of the mounting bracket 61 also changes after the adjustment plate 65 contacts the outer side surface of the mounting bracket 61 again. After the adjustment plate 65 is fixed to the mounting bracket 61 by bolts again, this change remains unchanged. Therefore, by inserting the clamping groove 651 into different adjustment grooves 641, the ejector rod 63 can support and fix small gas turbine engines of different specifications, increasing the practicability.

[0032] Two fixing plates 66 are fixedly connected to the outer side surface of the mounting bracket 61, and the two fixing plates 66 are respectively fixed to the two support plates 5.

[0033] A limit seat 14 is installed at the top end of the base 1, and the limit seat 14 cooperates with the end of the mounting table 4 away from the top table 3.

[0034] 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 by the above embodiments. What is described in the above embodiments and the specification only illustrates the principles of the present invention. Without departing from the spirit and scope of the present invention, the present invention will have various changes and improvements, and these changes and improvements all fall within the scope of the present invention claimed. The scope of protection claimed by the present invention is defined by the appended claims and their equivalents.

Claims

1. A test bench for a small gas turbine engine, comprising a base table (1), characterized in that: A sliding support structure (2) and a top platform (3) are fixedly installed at the top end of the bottom platform (1). The sliding support structure (2) is arranged on one side of the top platform (3). There are two sliding support structures (2) which are arranged in parallel. An installation platform (4) is jointly installed at the top ends of the two sliding support structures (2). Two parallel support plates (5) are fixedly connected to the top end of the installation platform (4). Support frames (7) are respectively fixedly connected to one ends of the two support plates (5) facing the top platform (3). An installation ring (8) is jointly fixedly connected between the two support frames (7). An air inlet pipe (10) is fixedly connected to one end of the installation ring (8). A rotary connecting pipe (9) is fixedly connected to the other end of the installation ring (8). An installation joint (6) is jointly installed at the ends of the two support plates (5) far from the top platform (3). The rotary connecting pipe (9) is arranged between the installation joint (6) and the air inlet pipe (10). The air outlet direction of the air inlet pipe (10) points to the rotary connecting pipe (9). An installation seat (11) is fixedly connected to the end of the installation platform (4) facing the top platform (3). A force transmission rod (12) is fixedly connected to the end of the installation seat (11) far from the installation platform (4). A pressure sensor (13) is fixedly connected to the end of the top platform (3) facing the installation platform (4). The pressure sensor (13) cooperates with the force transmission rod (12).

2. The test bench for a small gas turbine engine according to claim 1, characterized in that: The sliding support structure (2) includes a first support (21) and a second support (22). The first support (21) is arranged on one side of the second support (22) and close to the top platform (3). A sliding rod (23) is jointly fixedly connected to the first support (21) and the second support (22). The sliding rod (23) is perpendicular to the top platform (3). A first sliding platform (24) and a second sliding platform (25) are slidably sleeved on the sliding rod (23). The first sliding platform (24) and the second sliding platform (25) are both arranged between the first support (21) and the second support (22) and are both fixed to the bottom end of the installation platform (4).

3. The test stand for a small gas turbine engine according to claim 1, characterized in that: The installation joint (6) includes an installation frame (61) and an adjustment plate (65). The installation frame (61) is a semi-enclosed structure. The inner side surface of the installation frame (61) is an arc surface. A cushion block (62) is fixedly connected to the inner side surface of the installation frame (61). A top rod (63) is arranged on the cushion block (62). One end of the top rod (63) penetrates through the end of the cushion block (62) far from the installation frame (61). The other end of the top rod (63) penetrates through the cushion block (62) and the installation frame (61) and is fixedly connected to an adjustment rod (64). Two fixing plates (66) are fixedly connected to the outer side surface of the installation frame (61). The two fixing plates (66) are respectively fixed to the two support plates (5). The adjustment plate (65) is arranged outside the installation frame (61) and is connected to the installation frame (61) by bolts. The adjustment plate (65) cooperates with the adjustment rod (64).

4. A test bench for a small gas turbine engine according to claim 3, characterized in that: An adjustment groove (641) is formed on the outer peripheral side of the adjustment rod (64). The adjustment groove (641) is an annular groove and is arranged along the circumferential direction of the adjustment rod (64). A clamping groove (651) is formed on the adjustment plate (65). The clamping groove (651) cooperates with the adjustment groove (641) to form a clamping structure.

5. A test bench for a small gas turbine engine according to claim 4, characterized in that: A plurality of the adjustment grooves (641) are provided, and the plurality of adjustment grooves (641) are arranged at equal intervals along the axial direction of the adjustment rod (64).

6. The test stand for a small gas turbine engine according to claim 1, characterized in that: A limit seat (14) is installed at the top end of the bottom table (1), and the limit seat (14) cooperates with one end of the installation table (4) far from the top table (3).

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