Blade high-temperature impact test device

Abstract

The utility model relates to the technical field of aero-engine test equipment, and discloses a blade high-temperature impact test device which comprises a test chamber, a plurality of high-pressure combustors fixedly connected to the outer side of the test chamber, an air inlet chamber fixedly connected to the rear side of the test chamber, and a fuel pipe fixedly connected to the outer side of the air inlet chamber. A plurality of extension parts on the outer side of the fuel pipe are respectively connected with the corresponding high-pressure combustors, and a transmission shaft is rotationally connected in the test cabin and the air inlet cabin. The actual operation environment of the high-pressure turbine blade can be simulated, energy is supplied through the fuel pipe to enable the high-pressure combustor to generate high temperature, the high-pressure combustor is matched with the transmission shaft to drive the compression turbine to supercharge, the blade on the power turbine fixing clamp bears high-temperature and high-speed rotation stress, and the actual stress state is restored. A motor drives a gear, a gear ring and other parts, a sealing plate switch can be adjusted, and an impact object can be put from the plugging mechanism by combining the impact pipe and the negative pressure of the test chamber, so that the impact object accurately impacts the blade.

Description

TECHNICAL FIELD

[0001] The utility model relates to aero -engine test equipment technical field especially relates to a blade high temperature impact test device. BACKGROUND

[0002] The high pressure turbine blade of aero -engine is turbine core component, directly receives the high temperature combustion gas that combustion chamber discharged, can convert the heat energy of gas into mechanical energy, drives the compressor to continue operation;

[0003] The high pressure turbine of aero -engine needs to bear the huge stress that high pressure, high -speed rotation brings when working, the performance requirement is extremely high, therefore, the high pressure turbine needs to carry out impact test when designing and producing and processing, obtains each operating parameter of high pressure turbine, such as the existing announcement number for CN216208272U disclosed in Chinese utility model patent: a aero -engine blade impact test simulation device, the application will be through the two second telescopic cylinders in the clamping device of aero -engine blade and be clamped in the clamping groove of clamping arm, and through the first telescopic cylinder and the second telescopic cylinder mutually cooperate and adjust appropriate height, through the positive and negative motor adjusts the appropriate angle, then starts the cylinder, carries out the collision, and thus realizes the impact test to turbine blade, but this kind of impact test cannot simulate the actual operating environment of high pressure turbine, can only carry out the impact test to turbine blade under static condition, and in actual operation, turbine blade wants to bear the huge centrifugal force of high -speed rotation, the thermal stress of high temperature combustion gas scouring, also has complex aerodynamic force, these stresses will form special stress state inside the blade, and static test lacks these loads, cannot restore the stress distribution under real working condition, the deviation of the impact resistance performance measured and actual performance is big, also difficult to find the potential crack or weak point of blade under complex stress. CONTENT OF UTILITY MODEL

[0004] The utility model aims at providing a kind of blade high temperature impact test device, can effectively solve the problems in background art.

[0005] To achieve the above-mentioned purpose, the technical scheme adopted by the utility model is:

[0006] The utility model provides a kind of blade high temperature impact test device, including test cabin, several high-pressure combustors are fixedly connected outside the test cabin, air inlet cabin is fixedly connected to the rear side of the test cabin, fuel pipe is fixedly connected outside the air inlet cabin, and the fuel pipe multiple extensions are respectively connected with corresponding high-pressure combustor, transmission shaft is rotatably connected in the test cabin and the air inlet cabin, transmission shaft is fixedly connected with pressure turbine in the air inlet cabin, impact pipe is fixedly connected outside the test cabin, fixed flange is fixedly connected to the end of impact pipe away from test cabin, the fixed flange one side is fixedly connected with plugging mechanism, the plugging mechanism includes gear ring seat, motor is fixedly connected on the one side of gear ring seat, rotation groove is opened in the gear ring seat, fixed wheel is fixedly connected on the one side of gear ring seat close to the inner diameter of rotation groove, gear ring is rotatably connected in rotation groove, the one side of gear ring is fixedly connected with link ring frame, adjusting wheel is fixedly connected on the one side of link ring frame, several sealing plates are movably connected between fixed wheel and adjusting wheel.

[0007] As a further preferred embodiment of the utility model, the inside of the test cabin is fixedly connected with several spacers, thereby improving the impact resistance of the test cabin and preventing the test cabin structure from being damaged when the high-pressure turbine blade is broken during high-temperature impact testing.

[0008] As a further preferred embodiment of the utility model, the transmission shaft inside the test cabin is fixedly connected with a power turbine fixing clamp, which can fix the tested high-pressure turbine on the transmission shaft, so that the high-pressure turbine can be impacted and rotated to generate high temperature after the fuel pipe is started. At the same time, the high-pressure turbine drives the pressure turbine to rotate through the transmission shaft to increase the pressure in the test cabin and improve the rotational speed of the high-pressure turbine.

[0009] As a further preferred embodiment of the utility model, the motor is electrically connected to an external main control unit through a cable, and the output end of the motor is fixedly connected with a gear, which is engaged with the rotation groove to provide power source for the rotating adjusting wheel.

[0010] As a further preferred embodiment of the utility model, a plurality of arc-shaped guide slides are formed in the fixed wheel to cooperate with the adjusting wheel to realize the guided rotation of the sealing plates, thereby closing or opening the passage at the center of the fixed wheel and the adjusting wheel.

[0011] As a further preferred embodiment of the utility model, a plurality of connecting blocks are fixedly connected to the outside of the adjusting wheel, and a plurality of linear guide slides are formed on one side of the adjusting wheel, the connecting blocks are fixedly connected to one side of the link ring frame, the gear drives the rotation of the rotation groove, and the rotation groove drives the rotation of the adjusting wheel through the cooperation of the link ring frame and the connecting blocks.

[0012] As a further preferred embodiment of this utility model, a slider is fixedly connected to the sealing plate on one side relative to the adjusting wheel, and a rotating shaft is fixedly connected to the sealing plate near the slider. A corresponding arc-shaped guide slide is inserted into one side of the rotating shaft, and the slider is slidably connected in the corresponding linear guide slide. When the adjusting wheel rotates, the linear guide slide on one side of the adjusting wheel slides on the slider, causing the sealing plate to move towards the center channel of the adjusting wheel and cooperate with the rotating shaft to guide the sliding in the arc-shaped guide slide to achieve synchronous rotation of the sealing plate.

[0013] As a further preferred embodiment of this utility model, the fixed flange and the toothed ring seat are fixedly connected by several connecting rods by bolts, so that the toothed ring seat is fixed to one side of the fixed flange by the cooperation of the connecting rods and bolts, and one end of the impact tube is inserted into the central channel of the adjusting wheel. Thus, when the high-pressure turbine blade is subjected to impact testing, the high negative pressure in the test chamber allows the impact test material to be quickly sucked into the test chamber through the impact tube to conduct impact testing on the high-pressure turbine blade.

[0014] Compared with the prior art, the present invention has the following beneficial effects:

[0015] In this invention, the actual operating environment of high-pressure turbine blades can be simulated. The fuel supply pipe enables the high-pressure burner to generate high temperatures, which, in conjunction with the drive shaft, drive the compressor turbine to increase pressure. This causes the blades on the power turbine fixing fixture to withstand high temperatures and high-speed rotational stress, thus restoring the real stress state. At the same time, a sealing mechanism is set at one end of the impact tube. Its motor drives gears, gear rings, and other components, and the sealing plate switch can be adjusted. Combined with the negative pressure between the impact tube and the test chamber, an impactor can be inserted from the sealing mechanism, allowing the impactor to accurately impact the blades. This simulates the impact of parts falling from inside the engine compartment or foreign objects impacting the high-pressure turbine, thus solving the problem of static test deviation. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the main structure of this utility model;

[0017] Figure 2 This is a cross-sectional view of the main structure of this utility model;

[0018] Figure 3 This is a schematic diagram showing the disassembled structure of the fixed flange and sealing mechanism of this utility model;

[0019] Figure 4 This is a schematic diagram of the disassembled structure of the sealing mechanism of this utility model;

[0020] Figure 5 This is a schematic diagram showing the disassembled structure of the fixed wheel, adjusting wheel, and sealing plate of this utility model;

[0021] Figure 6 This is a schematic diagram of the sealing plate structure of this utility model.

[0022] In the diagram: 1. Test chamber; 2. High-pressure burner; 3. Intake chamber; 4. Fuel pipe; 5. Drive shaft; 6. Compressor turbine; 7. Power turbine fixing clamp; 8. Impact pipe; 9. Fixed flange; 10. Sealing mechanism; 11. Gear ring seat; 12. Motor; 13. Rotary groove; 14. Fixed wheel; 15. Gear ring; 16. Connecting ring frame; 17. Adjusting wheel; 18. Sealing plate; 19. Pad plate; 20. Gear; 21. Arc-shaped guide slide; 22. Connecting block; 23. Linear guide slide; 24. Slider; 25. Rotating shaft; 26. Connecting rod. Detailed Implementation

[0023] To make the technical means, creative features, objectives and effects of this utility model easier to understand, the present utility model will be further described below in conjunction with specific embodiments.

[0024] like Figures 1-6 As shown, the present invention provides a blade high-temperature impact testing device, comprising a test chamber 1, several high-pressure burners 2 fixedly connected to the outside of the test chamber 1, an air intake chamber 3 fixedly connected to the rear of the test chamber 1, a fuel pipe 4 fixedly connected to the outside of the air intake chamber 3, and multiple extensions of the fuel pipe 4 connected to corresponding high-pressure burners 2, a drive shaft 5 rotatably connected between the test chamber 1 and the air intake chamber 3, a compressor turbine 6 fixedly connected to the drive shaft 5 located in the air intake chamber 3, and an impact pipe 8 fixedly connected to the outside of the test chamber 1, the impact pipe 8 being located away from the test chamber 1. A fixed flange 9 is fixedly connected to one end, and a sealing mechanism 10 is fixedly connected to one side of the fixed flange 9. The sealing mechanism 10 includes a toothed ring seat 11, a motor 12 is fixedly connected to one side of the toothed ring seat 11, a rotating groove 13 is opened in the toothed ring seat 11, a fixed wheel 14 is fixedly connected to one side of the toothed ring seat 11 near the inner diameter of the rotating groove 13, a toothed ring 15 is rotatably connected in the rotating groove 13, a connecting ring frame 16 is fixedly connected to one side of the toothed ring 15, an adjusting wheel 17 is fixedly connected to one side of the connecting ring frame 16, and several sealing plates 18 are movably connected between the fixed wheel 14 and the adjusting wheel 17.

[0025] like Figure 1 As shown, several pads 19 are fixedly connected to the inner side of the test chamber 1, thereby improving the impact resistance of the test chamber 1 and preventing damage to the structure of the test chamber 1 when the high-pressure turbine blade breaks during the high-temperature impact test.

[0026] like Figure 2 As shown, the drive shaft 5 located in the test chamber 1 is fixedly connected to the power turbine fixing clamp 7, which can fix the high-pressure turbine under test on the drive shaft 5. This allows the high-pressure turbine to rotate and generate high temperature after the fuel pipe 4 is started. At the same time, the high-pressure turbine drives the compressor turbine 6 to rotate through the drive shaft 5, thereby increasing the pressure in the test chamber 1 and increasing the speed of the high-pressure turbine.

[0027] like Figures 2-6As shown, the motor 12 is electrically connected with an external master control unit through a cable, the output end of the motor 12 is fixedly connected with a gear 20, the gear 20 is meshingly connected with the rotating groove 13, so as to provide a power source for the rotating adjusting wheel 17, a plurality of arc-shaped guide slides 21 are arranged in the fixed wheel 14, so as to cooperate with the adjusting wheel 17 to realize the guided rotation of the plurality of sealing plates 18, and then realize that the plurality of sealing plates 18 close or open the passage at the center position of the fixed wheel 14 and the adjusting wheel 17, a plurality of connecting blocks 22 are fixedly connected to the outer side of the adjusting wheel 17, a plurality of linear guide slides 23 are arranged on one side of the adjusting wheel 17, the connecting blocks 22 are fixedly connected to one side of the connecting ring frame 16, the gear 20 drives the rotating groove 13 to rotate, the rotating groove 13 drives the adjusting wheel 17 to rotate through the cooperation of the connecting ring frame 16 and the connecting blocks 22, the sliding block 24 is fixedly connected to one side of the adjusting wheel 17 relative to the sealing plate 18, the rotating shaft 25 is fixedly connected to the position close to the sliding block 24 in the sealing plate 18, the corresponding arc-shaped guide slides 21 are inserted into one side of the rotating shaft 25, and the sliding block 24 is slidingly connected in the corresponding linear guide slide 23, when the adjusting wheel 17 rotates, the linear guide slide 23 on one side of the adjusting wheel 17 slides on the sliding block 24, so that the sealing plate 18 moves to the center passage of the adjusting wheel 17 and cooperates with the rotating shaft 25 to realize the synchronous rotation of the sealing plate 18 by guiding sliding in the arc-shaped guide slide 21, a plurality of connecting rods 26 are fixedly connected between the fixed flange 9 and the gear ring seat 11 through bolts, so that the gear ring seat 11 is fixed on one side of the fixed flange 9 through the cooperation of the connecting rods 26 and the bolts, and one end of the impact pipe 8 is inserted into the center passage in the adjusting wheel 17, so that when the high-pressure turbine blade is subjected to impact test, the impact test object is quickly sucked into the test cabin 1 through the impact pipe 8 under the high negative pressure in the test cabin 1, and the high-pressure turbine blade is subjected to impact test.

[0028] It should be noted that the utility model is a kind of blade high-temperature impact test device, before testing, high-pressure turbine is fixed on the transmission shaft 5 in test cabin 1 by power turbine fixing clamp 7, ensure that high-pressure turbine is stable in the position during testing, and it will not be offset due to subsequent high temperature and impact effect;

[0029] During the test, the fuel pipe 4 starts to deliver fuel through the external fuel pump, and the fuel is delivered to the corresponding high-pressure combustor 2 through the multiple extensions outside the fuel pipe 4, and the high-pressure combustor 2 combusts after receiving the fuel, and high-temperature gas is generated, which enters the test cabin 1, so that the high-temperature gas drives the high-pressure turbine blades on the power turbine fixed clamp 7 to rotate, the rotation of the blades drives the transmission shaft 5 to rotate, and the transmission shaft 5 further drives the compressor turbine 6 in the air inlet cabin 3 to rotate, and the compressor turbine 6 rotates to suck external air into the air inlet cabin 3 and compresses the sucked air, and the compressed air enters the test cabin 1, further increases the rotating speed of the high-pressure turbine blades, and the blades not only bear high temperature, but also bear centrifugal force generated by high-speed rotation and aerodynamic force brought by air flow, when the temperature, pressure and blade rotating speed in the test cabin 1 reach the set conditions required by the test, the motor 12 is started by the external main control unit, the motor 12 drives the gear 20 to rotate, the gear 20 is engaged with the gear ring 15, thereby driving the gear ring 15 to rotate in the rotating groove 13 of the gear ring seat 11, the gear ring 15 drives the adapter ring frame 16 to move, the adapter ring frame 16 drives the adjusting wheel 17 to rotate through the connecting block 22, when the adjusting wheel 17 rotates, the linear guide slide 23 on one side of the adjusting wheel 17 slides on the sliding block 24 of the sealing plate 18, so as to drive the sealing plate 18 to move to the center channel of the adjusting wheel 17, and the rotating shaft 25 of the sealing plate 18 slides in the arc-shaped guide slide 21 of the fixed wheel 14, so as to realize the synchronous rotation of the sealing plate 18, thereby opening the channel between the fixed wheel 14 and the center of the adjusting wheel 17, and then the impact test object can be put into the channel through the feeding mechanism such as the mechanical claw, since the test cabin 1 is in a high-pressure state and forms a pressure difference with the outside, under the action of negative pressure, the impact test object is quickly sucked into the test cabin 1 through the impact pipe 8, and finally accurately impacts the high-pressure turbine blades in the high-temperature and high-speed rotating state, simulates the scene that the internal parts fall or the external foreign matters impact the blades during the engine operation, and completes the high-temperature impact test of the blades.

[0030] The basic principle and main features of the utility model and the advantages of the utility model are shown and described above. It should be understood by those skilled in the art that the utility model is not limited by the above-mentioned embodiments, and the above-mentioned embodiments and the description in the specification only illustrate the principle of the utility model, and various changes and improvements can be made to the utility model without departing from the spirit and scope of the utility model, and these changes and improvements all fall within the scope of the utility model claimed. The protection scope of the utility model is defined by the appended claims and their equivalents.

Claims

1. A blade high temperature impact testing apparatus, characterized by: Including test cabin (1), a plurality of high pressure combustor (2) are fixedly connected outside the test cabin (1), the rear side of test cabin (1) is fixedly connected with air inlet cabin (3), the outer side of air inlet cabin (3) is fixedly connected with fuel pipe (4), and the outer side of the fuel pipe (4) is extended and is connected with corresponding high pressure combustor (2) respectively, the transmission shaft (5) is rotatably connected in test cabin (1) and air inlet cabin (3), the transmission shaft (5) fixedly connected with pressure turbine (6) is located in the air inlet cabin (3), the outer side of test cabin (1) is fixedly connected with impact tube (8), the end of impact tube (8) away from test cabin (1) is fixedly connected with fixed flange (9), the one side of fixed flange (9) is fixedly connected with blocking mechanism (10), the blocking mechanism (10) includes gear ring seat (11), the one side of gear ring seat (11) is fixedly connected with motor (12), the gear ring seat (11) is provided with rotation groove (13) in, the one side of gear ring seat (11) is fixedly connected with fixed wheel (14) near the inner diameter of rotation groove (13), the rotation groove (13) is rotatably connected with gear ring (15), the one side of gear ring (15) is fixedly connected with link ring frame (16), the one side of link ring frame (16) is fixedly connected with adjusting wheel (17), a plurality of sealing plates (18) are movably connected between fixed wheel (14) and adjusting wheel (17).

2. The blade high-temperature impact test device according to claim 1, characterized by: The inner side of test cabin (1) is fixedly connected with a plurality of pad plates (19).

3. The blade high-temperature impact test apparatus according to claim 1, characterized by: The transmission shaft (5) fixedly connected with power turbine fixed clamp (7) is located in the test cabin (1).

4. The blade high-temperature impact test apparatus according to claim 1, characterized by: The motor (12) is electrically connected with the external main control unit through cable, the output end of motor (12) is fixedly connected with gear (20), and gear (20) is engagedly connected with rotation groove (13).

5. The blade high-temperature impact test apparatus according to claim 1, characterized by: A plurality of arc-shaped guide slides (21) are formed in the fixed wheel (14).

6. A high temperature blade impact testing apparatus as claimed in claim 5, wherein: The outer side of adjusting wheel (17) is fixedly connected with a plurality of connecting blocks (22), a plurality of linear guide slides (23) are formed in the one side of adjusting wheel (17), and the connecting block (22) is fixedly connected on the one side of link ring frame (16).

7. A high temperature blade impact testing apparatus as claimed in claim 6, wherein: The sliding block (24) is fixedly connected on the one side of adjusting wheel (17) of sealing plate (18), the rotating shaft (25) is fixedly connected in sealing plate (18) near the position of sliding block (24), the one side of rotating shaft (25) is inserted into corresponding arc-shaped guide slide (21), and the sliding block (24) is slidably connected in corresponding linear guide slide (23).

8. The blade high temperature impact testing apparatus according to claim 1, wherein: A plurality of connecting rods (26) are fixedly connected between fixed flange (9) and gear ring seat (11) through bolts.

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