A bird impact test device simulating a real engine

Abstract

The application belongs to the field of bird impact test and is a bird impact test device simulating a real engine, comprising an air cannon, a first ejection plate, a second ejection plate, a first fixed support, an air intake casing and a second fixed support; the first ejection plate and the second ejection plate are arranged in front and back, and the first fixed support and the air intake casing are both located behind the second ejection plate; the air intake casing is installed on the first fixed support; the second fixed support is fixed with a fan casing; the first ejection plate, the second ejection plate, the first fixed support, the air intake casing and the second fixed support are arranged to simulate the impact of the bird on the fan casing and the component unit after the first simulated fan blade is impacted by the bird, to realize the ejection impact of the air intake on the bird body, to simulate the process of the bird body impacting the air intake support plate, to effectively simulate the change of the bird body motion trajectory and the cutting and deceleration of the air intake support plate on the bird body in the case of limited space, and to realize the accurate evaluation of the ability of the engine to withstand the bird body impact.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of bird impact test, and particularly relates to a bird impact test device simulating a real engine. BACKGROUND

[0002] An accident caused by a bird colliding with an aircraft in flight is called bird strike, and the bird strike can lead to a serious flight accident. With the continuous development of aviation technology, the bird strike events have shown an upward trend in the world in recent years, and the probability of bird strike accidents of military aircraft flying at low altitude and high speed is even greater.

[0003] The degree of the aircraft bird strike accident mainly depends on the position of the aircraft hit by the bird, the mass of the bird and the relative speed of the bird and the aircraft and other factors. According to the bird strike event data, the number of times of the bird strike on the engine blade is only less than that on the windshield, accounting for 18.0% of the total number of bird strikes. After the bird strike accident occurs, the deformation and fracture of the aircraft engine blade can cause the engine thrust to decrease, and the fractured blade can also injure other blades and cause them to break. Once the fractured blade flies out and penetrates the nacelle, it can damage the aircraft control system. The fractured blade can also cause the imbalance of the engine rotor, which can have extremely serious consequences, directly affecting the flight safety of the aircraft, causing huge economic losses, and also endangering the life safety of the passengers.

[0004] The bird impact resistance of the aircraft engine is an important condition to ensure the safety of the aircraft. The bird strike problem has always been one of the important special items considered in the airworthiness review of the engine. In the airworthiness specification, the aircraft engine must pass the strict bird strike test to evaluate its ability to withstand bird impact. The ability of the aircraft engine to resist bird impact is a necessary condition for the engine to obtain a certificate. The airworthiness standards are constantly updated at home and abroad to improve the level of bird strike prevention of the aircraft.

[0005] The engine fan rotor bird impact test piece adopts a fan rotor of a certain engine structure, which belongs to a large fan rotor. After dynamic balancing, the test piece is installed on the test support point of the horizontal rotor rotation tester in a simply supported manner, and is connected to the double support points of the equipment through a shaft coupling. The test equipment is composed of a horizontal rotor rotation tester and an air gun, and a test equipment schematic diagram is shown in Figure 1 When testing, the fan rotor reaches the target speed, the launching mechanism is started, the compressed air pushes the shell and the bird bullet to accelerate in the barrel, and the shell is separated and stopped after reaching the shell separation mechanism. The separated bird bullet collides with the specified position of the rotating fan rotor.

[0006] The existing bird impact test device has many deficiencies, mainly in the technical aspect:

[0007] 1. After the real aircraft swallows the bird, the bird body first collides with the air inlet at high speed and rebounds, especially for the aircraft engine with S-shaped air inlet, the existing test device cannot simulate it;

[0008] 2. After the bird body collides through the air inlet, it continues to hit the engine inlet casing support plate and guide vane, and the mass and speed of the bird body will be attenuated, and the existing test device cannot simulate it;

[0009] 3. Due to the lack of fan casing, the bird body hits the rotating fan rotor blade, and the damage to the fan casing caused by the blade drop is difficult to evaluate;

[0010] Based on the above three points, the existing test device is difficult to simulate the test results of the real engine hit by the bird on the tester, and the existing test device directly hits the fan blade with the bird, which is the most severe test method, and the evaluation of the ability of the engine to withstand bird impact is not accurate. SUMMARY

[0011] The purpose of the present application is to provide a bird impact test device for simulating a real engine, to solve the problem of inaccurate evaluation of the ability of the engine to withstand bird impact.

[0012] The technical scheme of the present application is: a bird impact test device for simulating a real engine, comprising a gas gun, a first ejection plate, a second ejection plate, a first fixed support, an inlet casing and a second fixed support; the outlet of the gas gun corresponds to the first ejection plate and the second ejection plate; the first ejection plate and the second ejection plate are arranged in front and back, the first fixed support and the inlet casing are located behind the second ejection plate, and are used to simulate the aircraft air inlet; and the inlet casing is installed on the first fixed support, and is used to simulate the process of bird body hitting the air inlet support plate; the second fixed support is fixed with a fan casing, the fan casing is internally provided with a fan rotor, and the fan casing, the inlet casing and the fan rotor jointly form a fan component unit body, which is used to simulate the influence of the fan blade hit by the bird on the fan casing and the component unit body.

[0013] Preferably, a front support is arranged in front of the inlet casing, and a rear support point is arranged behind the fan casing, and the front support point and the rear support point are in rotating cooperation with the fan rotor.

[0014] Preferably, a coupling joint and a device double support point are further arranged behind the rear support point, the coupling joint is fixedly connected to the end of the fan rotor, and the rear end of the coupling joint is connected with the device double support point.

[0015] Preferably, the air inlet casing and the fan casing are further provided with a positioning system, the positioning system comprising an air inlet fixing plate, a fan fixing plate, a vertical support assembly, an upper support assembly and a lower support assembly; the air inlet fixing plate is fixedly connected with the air inlet casing, and an air inlet support plate is arranged on the inner side of the air inlet fixing plate; the fan fixing plate is fixedly connected with the fan casing, and is used for further supporting the air inlet casing and the fan casing respectively; the vertical support assembly is coaxially arranged with the fan rotor; and the upper support assembly and the lower support assembly are arranged in a corresponding upper and lower manner.

[0016] Preferably, a front-end aluminum pad is arranged between the air inlet fixing plate and the fan rotor, and a rear-end aluminum pad is arranged between the vertical support assembly and the fan rotor.

[0017] Preferably, the corresponding test steps comprise:

[0018] Process 1: The bird body is launched by the air cannon and separated from the shell by the bullet separator at the end of the air cannon, at which time the initial launch speed V1 of the bird body can be measured;

[0019] Process 2: The bird body hits the first ejection plate to simulate the first impact of the real bird body on the inner wall of the aircraft inlet, which forms an angle with the flight direction of the aircraft, and the angle can be adjusted by adjusting the placement angle of the ejection plate A to simulate the angle, and after the first impact, the bird body continues to move along the tangent direction of the ejection plate A, and the speed is attenuated to V2;

[0020] Process 3: The bird body hits the second ejection plate to simulate the real bird body flying through the S-shaped inlet and hitting another inner wall, which is parallel to the engine axis direction, and after the second impact, the bird body enters the fan unit component along the engine axial direction, at which time the speed of the bird body is attenuated to V3;

[0021] Process 4: The bird body hits the air inlet support plate after passing through the C-shaped hole reserved in the air inlet casing, at which time the bird body is divided into different parts after hitting the air inlet support plate, and the main part is attenuated to V4;

[0022] Process 5: The main part of the bird body hits the fan rotor in a rotating state at a speed of V4, and causes the fan blade to be curled or even dropped, and the dropped part of the blade hits the fan casing along the tangent direction of the fan rotor to test the containment of the fan casing.

[0023] The bird impact test device simulating a real engine is provided in the application, and the first ejection plate, the second ejection plate, the first fixed support for simulating the influence of the bird impact on the fan case and the component unit body after the bird impact on the fan blade, the air inlet case and the second fixed support are arranged to realize the ejection impact of the air inlet on the bird body, simulate the process of the bird body impacting the air inlet support plate, effectively simulate the change of the bird body motion track and the cutting and deceleration effect of the air inlet support plate on the bird body in the case of limited space, and thus the accurate evaluation of the bird impact capacity of the engine can be realized. BRIEF DESCRIPTION OF DRAWINGS

[0024] In order to more clearly illustrate the technical solutions provided in the application, the drawings will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the application.

[0025] Figure 1 It is a schematic diagram of the existing bird impact test device;

[0026] Figure 2 It is a schematic diagram of the overall structure of the application;

[0027] Figure 3 It is a schematic diagram of the positioning system structure of the application;

[0028] Figure 4 It is a schematic diagram of the vertical support assembly structure of the application;

[0029] Figure 5 It is a schematic diagram of the fan fixed plate structure of the application;

[0030] Figure 6 It is a schematic diagram of the air inlet fixed plate structure of the application;

[0031] Figure 7 It is a front view of the bird impact test device of the application.

[0032] 1, air cannon; 2, first ejection plate; 3, second ejection plate; 4, rear support plate; 5, first fixed support; 6, air inlet case; 7, fan case; 8, second fixed support; 9, fan rotor; 10, front support point; 11, coupling; 12, equipment double support point; 13, front end aluminum pad; 14, air inlet fixed plate; 15, first bolt; 16, upper support assembly; 17, fan fixed plate; 18, second bolt; 19, vertical support assembly; 20, screw; 21, rear end aluminum pad; 22, lower support assembly; 23, air inlet support plate. DETAILED DESCRIPTION

[0033] Clearly, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative efforts belong to the protection scope of the present application.

[0034] A bird impact test device for simulating a real engine, comprising a gas gun 1, a first ejection plate 2, a second ejection plate 3, a first fixed support 5, an air inlet casing 6 and a second fixed support 8. Figure 2 The outlet of the gas gun 1 corresponds to the first ejection plate 2 and the second ejection plate 3; the first ejection plate 2 and the second ejection plate 3 are arranged in front of and behind each other; the first fixed support 5 and the air inlet casing 6 are both located behind the second ejection plate 3, for simulating an aircraft air inlet; and the air inlet casing 6 is installed on the first fixed support 5, for simulating the process of a bird body impacting the air inlet support plate 23; the second fixed support 8 is fixed with a fan casing 7, the inside of the fan casing 7 is a fan rotor 9, and the fan casing 7, together with the air inlet casing 6 and the fan rotor 9, constitutes a fan component unit body, for simulating the influence of a bird impacting a fan blade on the fan casing 7 and the component unit body; the bird body impacting the fan blade is easy to cause the blade to drop and impact the fan casing 7, for testing the containment requirement of the fan casing 7; because the double support point structure is different from the real engine, the coaxiality requirement between the fan casing 7 and the fan rotor 9 needs to be ensured.

[0035] Because the real S-shaped air inlet of an aircraft is about 8-10 meters long and is expensive to manufacture, it is impossible to use the real air inlet for bird impact test under the condition of a test device, so two ejection plates with material, thickness and surface roughness as consistent as possible with the real air inlet are arranged in the limited space, for simulating the ejection impact of the S-shaped air inlet on the bird body, so that the running track of the bird body changes obviously and finally enters the fan component along the engine axial direction.

[0036] The bird body impacts the air inlet support plate 23 after passing through the air inlet, for testing that the strength of the air inlet support plate 23 can meet the structural integrity requirement after the bird body impacting, and for testing that the air inlet support plate 23 has a cutting and deceleration effect on the bird body, so that the bird body after passing through the air inlet support plate 23 is obviously reduced in mass and speed.

[0037] Preferably, a front support is arranged in front of the air inlet casing 6, and a rear support point is arranged behind the fan casing 7; the front support point 10 and the rear support point are both in rotational cooperation with the fan rotor 9, for supporting the fan rotor 9.

[0038] A coupling 11 and a device double support point 12 are further arranged behind the rear support point; the coupling is fixedly connected to the end of the fan rotor 9; the rear end of the coupling 11 is connected with the device double support point 12, for further fixing the fan rotor 9.

[0039] Preferably, the installation and fixation of the inlet casing 6 and fan casing 7 assembly, and the coaxiality of the casing components and the fan rotor 9 components should be considered, so the positioning system is also provided for the inlet casing 6 and fan casing 7, such as Figure 3 The positioning system includes the inlet fixing plate 14, the fan fixing plate 17, the vertical support assembly 19, the upper support assembly 16 and the lower support assembly 22. The inlet fixing plate 14 is fixedly connected with the inlet casing 6, and the inner side of the inlet fixing plate 14 is provided with an inlet support plate 23. The fan fixing plate 17 is fixedly connected with the fan casing 7, and is used for further supporting the inlet casing 6 and the fan casing 7 respectively. The vertical support assembly 19 is coaxially arranged with the fan rotor 9, and the vertical support assembly 19 is connected with the fan fixing plate 17 through the second bolt 18. The upper support assembly 16 and the lower support assembly 22 are arranged in correspondence with each other in up and down directions, and both support and fix the inlet fixing plate 14 and the fan fixing plate 17.

[0040] Preferably, the inlet fixing plate 14 is connected with the upper support assembly 16 and the lower support assembly 22 through bolts.

[0041] Preferably, due to the limited space in the vacuum cabin, the assembly of the fan component unit body should be completed outside the vacuum cabin, so the front end aluminum pad 13 is arranged between the inlet fixing plate 14 and the fan rotor 9, and the rear end aluminum pad 21 is arranged between the vertical support assembly 19 and the fan rotor 9, so as to adjust the coaxiality of the inlet casing 6, the fan casing 7 and the fan rotor 9, and then to install and fix the unit body. After the bolt fixation of the support point and the ground rail is completed, the front end aluminum pad 13 and the rear end aluminum pad 21 are removed, and the installation of the test device is completed.

[0042] Preferably, the rear end aluminum pad 21 is connected with the vertical support assembly 19 through the screw 20.

[0043] Different from the real structure of the engine, the support bearing structure of the casing assembly and the fan rotor 9 assembly cannot be simulated under the condition of the test device, so it is necessary to ensure that the casing assembly has sufficient rigid support to prevent additional impact on the casing structure caused by bird impact. The vertical support assembly 19 is designed at the rear end of the fan rotor 9, as shown in Figure 4 The bottom is connected and fixed with the ground rail in the vacuum cabin through bolts, and the installation side is connected with the fan fixing plate 17 to support the fan casing 7 assembly, as shown in Figure 5 .

[0044] Because the front end of the fan rotor 9 is difficult to place a bracket due to space position limitation, the upper bracket assembly 16 and the lower bracket assembly 22 are designed. The lower bracket assembly 22 is fixed on the cabin ground rail through anchor bolts, and the upper bracket assembly 16 is fixed with the lower bracket assembly 22 in a split way through the flange edge. The front end is fixed with the inlet duct 6 through the inlet fixing plate 14. One side of the inlet fixing plate 14 is provided with a C-shaped hole for the bird to pass through, as shown in Figure 6 The front view of the test device is shown in Figure 7

[0045] By setting the first ejection plate 2, the second ejection plate 3, the first fixed bracket for simulating the influence of the bird hitting the fan casing 7 and the component unit body after the fan blade, the inlet duct 6 and the second fixed bracket 8, the ejection and impact of the simulated inlet duct on the bird body and the process of the bird body hitting the inlet support plate 23 are realized. In the case of limited space, the change of the bird body motion trajectory and the cutting and deceleration effect of the inlet support plate 23 on the bird body are effectively simulated, so as to realize the accurate evaluation of the bird impact resistance of the engine.

[0046] As a specific embodiment, a bird impact test step for simulating a real engine is further included, which comprises the following processes:

[0047] Process 2: The bird body hits the first ejection plate 2 to simulate the first impact of the real bird body on the inner wall of the aircraft inlet duct, which forms an angle with the flight direction of the aircraft. The angle can be simulated by adjusting the placement angle of the ejection plate A. After the first impact, the bird body continues to move along the tangent direction of the ejection plate A, and the speed is attenuated to V2.

[0048] Process 3: The bird body hits the second ejection plate 3 to simulate the flight of the real bird body through the S-shaped inlet duct and hits another inner wall parallel to the engine axis direction. After the second impact, the bird body enters the fan unit component along the engine axis direction, and the speed is attenuated to V3.

[0049] Process 4: The bird body hits the inlet support plate 23 after passing through the C-shaped hole reserved in the inlet duct 6. At this time, the bird body is divided into different parts after hitting the inlet support plate 23, and the main part is attenuated to V4.

[0050] Process 5: The main part of the bird body hits the fan rotor 9 in a rotating state at a speed of V4, and causes the fan blade to be curled or even dropped. The dropped part of the blade hits the fan casing 7 along the tangent direction of the fan rotor 9 to test the containment of the fan casing 7.

[0051] ​Through the above analysis, it can be seen that the bird impact test device effectively simulates the influence of the air inlet on the bird impact under the test device condition, the influence of the air inlet casing and the air inlet support plate on the bird impact, and the influence of the bird impact on the fan casing after the fan blade is impacted, and the like. The real fan blade bird impact resistance is more accurately evaluated on the bird mass and the bird speed, and compared with the whole machine bird swallowing test, the test cost is greatly saved.

[0052] Finally, it should be noted that: the present application discloses the embodiment in the drawing, only relates to the structure involved in the present application, other structures can refer to the usual design, in the case of no conflict, the same embodiment and different embodiments of the present application can be combined with each other;

[0053] Finally: the above only for the preferred embodiment of the present application, and not for limiting the present application, any modification, equivalent replacement, improvement, etc. within the spirit and principles of the present application, should be included in the protection scope of the present application.

Claims

1. A bird impact test apparatus simulating a real engine, characterized by: The application relates to a bird impact test device, which comprises an air cannon (1), a first ejection plate (2), a second ejection plate (3), a first fixed support (5), an air inlet casing (6) and a second fixed support (8); the outlet of the air cannon (1) is provided with the first ejection plate (2) and the second ejection plate (3); the first ejection plate (2) and the second ejection plate (3) are arranged in front of and behind each other; the first fixed support (5) and the air inlet casing (6) are both located behind the second ejection plate (3) and are used for simulating an aircraft air inlet; the air inlet casing (6) is installed on the first fixed support (5) and is used for simulating the process that a bird body impacts an air inlet support plate (23); a fan casing (7) is fixed on the second fixed support (8); the fan casing (7) is internally provided with a fan rotor (9); the fan casing (7), the air inlet casing (6) and the fan rotor (9) jointly form a fan component unit body and are used for simulating the influence of a bird impacting a fan blade on the fan casing (7) and the component unit body; The air inlet casing (6) and the fan casing (7) are further provided with a positioning system; the positioning system comprises an air inlet fixed plate (14), a fan fixed plate (17), a vertical support assembly (19), an upper support assembly (16) and a lower support assembly (22); the air inlet fixed plate (14) is fixedly connected with the air inlet casing (6); the air inlet fixed plate (14) is internally provided with an air inlet support plate (23); the fan fixed plate (17) is fixedly connected with the fan casing (7) and is used for further supporting the air inlet casing (6) and the fan casing (7) respectively; the vertical support assembly (19) is coaxially arranged with the fan rotor (9); the upper support assembly (16) and the lower support assembly (22) are arranged in a corresponding manner.

2. The bird impact test apparatus simulating a real engine of claim 1, wherein: The air inlet casing (6) is provided with a front supporting point (10) in front; the fan casing (7) is provided with a rear supporting point in back; the front supporting point (10) and the rear supporting point are both rotationally matched with the fan rotor (9).

3. The bird impact test apparatus simulating a real engine of claim 2, wherein: The rear of the rear supporting point is further provided with a shaft coupling (11) and a device double supporting point (12); the shaft coupling (11) is fixedly connected with the end of the fan rotor (9); the rear end of the shaft coupling (11) is connected with the device double supporting point (12).

4. The bird impact test apparatus simulating a real engine of claim 1, wherein: A front end aluminum pad (13) is arranged between the air inlet fixed plate (14) and the fan rotor (9); a rear end aluminum pad (21) is arranged between the vertical support assembly (19) and the fan rotor (9).

5. A method for simulating a bird impact test of a real engine using the bird impact test device according to any one of claims 1 to 4, characterized in that: The corresponding test steps comprise the following steps: Process 1: a bird body is launched through the air cannon (1) and is separated from a shell by a shell separator at the end of the air cannon (1); at this time, the initial launching speed V1 of the bird body is measured; Process 2: the bird body impacts the first ejection plate (2) to simulate that a real bird body impacts an inner wall of an aircraft air inlet for the first time; the inner wall forms an included angle with the flying direction of the aircraft; the included angle is adjusted by adjusting the placing angle of the first ejection plate (2) to simulate; after the first impact, the bird body continues to move along the tangent direction of the first ejection plate (2) and the speed is attenuated to V2; Process 3: Bird hits the second ejection plate (3), simulating the real bird passing through the S-bend inlet duct and hitting another inner wall which is parallel to the engine axis direction, after the second impact, the bird enters the fan unit part along the engine axial direction, at this time the bird speed is attenuated to V3; Process 4: After the bird passes through the C-shaped hole reserved in the inlet casing (6), it hits the inlet support plate (23), at this time the bird is divided into different parts after hitting the inlet support plate (23), and the main part is attenuated to V4; Process 5: The main part of the bird hits the rotating fan rotor (9) at a speed of V4, and causes the fan blade to be curled or even to fall off, the fallen part of the blade hits the fan casing (7) along the tangent direction of the fan rotor (9) to test the containment of the fan casing (7).

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