Cooling effect test assembly of high-pressure turbine blade

Abstract

The utility model discloses a cold effect test assembly of high pressure turbine blade, relates to industrial production technical field, including mounting disc and locking assembly, locking assembly is provided on one side of mounting disc, locking assembly includes test blade, test blade is movably connected on one side of mounting disc, locking assembly is provided on the other side of mounting disc, locking assembly is provided on the other side of mounting disc. A through groove is formed in the test blade, and a limiting groove is formed in one side of the installation disc. According to the cold effect test assembly of the high-pressure turbine blade, by installing the locking assembly, a worker aligns a through groove in the test blade to a limiting groove in an installation disc, a first connecting rod penetrates through the through groove and is inserted into the limiting groove, then a rotary knob is pressed downwards, and the rotary knob extrudes the first connecting rod to move downwards through an extrusion disc; then the knob is rotated to drive the limiting rod to rotate by 90 degrees, the knob is loosened after rotation is completed, the limiting rod is in contact with the inner wall of the limiting groove under the elastic recovery capability of the spring, the test blade is connected with the mounting disc, and the mode is relatively simple and very convenient to operate.

Description

Technical Field

[0001] The utility model relates to the technical field of industrial production, in particular to a cooling effect test component for high-pressure turbine blades. Background Art

[0002] High-pressure turbine blades are responsible for guiding the high-temperature and high-pressure airflow and driving the turbine to rotate, thereby driving the compressor or other loads to maintain the normal operation of the engine. They are the core components of the engine's energy conversion and have a direct impact on the engine's performance and efficiency. The high-pressure turbine blade cooling efficiency test is a crucial link in the aircraft engine design process. It is used to evaluate the cooling effect of turbine blades in extremely high temperature and high pressure environments to ensure that the blades can maintain stable performance and extend their service life during long-term operation.

[0003] Existing devices typically use bolts to secure high-pressure turbine blades during cooling efficiency tests. However, multiple high-pressure turbine blades are required during cooling efficiency tests, and workers must constantly rotate the bolts when replacing or installing high-pressure turbine blades. This is cumbersome and inconvenient. Therefore, those skilled in the art have provided a cooling efficiency test assembly for high-pressure turbine blades to address the issues raised in the background art. Utility Model Content

[0004] The purpose of the present utility model is to provide a cooling efficiency test assembly for high-pressure turbine blades to solve the problems raised in the above-mentioned background technology.

[0005] To achieve the above objectives, the present invention provides the following technical solutions:

[0006] A cooling effect test assembly for a high-pressure turbine blade comprises a mounting plate and a locking assembly, wherein the locking assembly is arranged on one side of the mounting plate, the locking assembly comprises a test blade, the test blade is movably connected to one side of the mounting plate, a through groove is provided inside the test blade, a limiting groove is provided on one side of the mounting plate, a locking rod is movably connected to one side of the test blade, a movable hole is provided inside the locking rod, a connecting rod 1 is movably connected to the inside of the movable hole, a spring is sleeved on the side surface of the connecting rod 1, and an extrusion disc is fixedly connected to one side of the connecting rod 1. A knob is fixedly connected to one side of the extrusion disk, and a limit rod is fixedly connected to the side surface of the connecting rod. By installing the locking assembly, the staff aligns the through slot on the test blade with the limit slot on the mounting disk, passes the connecting rod through the through slot and inserts it into the limit slot, and then presses the knob downward. The knob squeezes the connecting rod through the extrusion disk and moves downward. The knob is then rotated to drive the limit rod to rotate ninety degrees. After the rotation is completed, the knob is released. Under the elastic recovery ability of the spring, the limit rod contacts the inner wall of the limit slot, and the test blade is connected to the mounting disk. This method is relatively simple to operate and very convenient.

[0007] As a further solution of the present invention: a load-bearing column is fixedly connected to the other side of the mounting plate, a fixing frame is fixedly connected to the other side of the load-bearing column, a base is fixedly connected to one side of the base, and a mounting plate is fixedly connected to one side of the base.

[0008] As a further solution of the present invention: a servo motor is fixedly connected to the top of the mounting plate, a connecting shaft is fixedly connected to the transmission end of the servo motor, and a gear is fixedly connected to the other side of the connecting shaft.

[0009] As a further solution of the present invention: a connecting rod 2 is fixedly connected to the other side of the gear, a rack is meshedly connected to one side of the gear, a fixed rod is fixedly connected to the top of the rack, a connecting column is fixedly connected to one side of the fixed rod, and a sealing frame is fixedly connected to one side of the connecting column. The staff starts the servo motor, the servo motor drives the connecting shaft to rotate, the connecting shaft drives the two gears to rotate, the two gears drive the rack to move up and down, and the rack moves up and down through the fixed rod and the connecting column, so as to facilitate the staff to take the test blade and ensure the sealing of the experiment.

[0010] As a further solution of the present invention: a cold air inlet hole is opened on the top of the test blade, the top of the cold air inlet hole is fixedly connected to a cold air introduction pipe, and the side surface of the cold air introduction pipe is fixedly connected to a cold air flange.

[0011] As a further solution of the present invention: an air outlet is provided on the other side of the test blade, a connecting hole is provided on one side of the test blade, and a connecting pipe is fixedly connected to one side of the connecting hole.

[0012] As a further solution of the present invention: one side of the sealing frame is fixedly connected to a gas inlet pipe, and the side surface of the gas inlet pipe is fixedly connected to a gas flange.

[0013] As a further solution of the present invention: the other side of the sealing frame is fixedly connected to an exhaust pipe, and a valve is provided inside the exhaust pipe.

[0014] Compared with the prior art, the beneficial effects of the present invention are:

[0015] 1. By installing the locking assembly, the staff aligns the through slot on the test blade with the limit slot on the mounting plate, inserts the connecting rod through the through slot into the limit slot, and then presses the knob downward. The knob squeezes the connecting rod through the squeezing disk and moves downward. Then, the knob is rotated to drive the limit rod to rotate ninety degrees. After the rotation is completed, the knob is released. Under the elastic recovery ability of the spring, the limit rod contacts the inner wall of the limit slot, connecting the test blade to the mounting plate. This method is relatively simple to operate and very convenient.

[0016] 2. The staff starts the servo motor, which drives the connecting shaft to rotate, and the connecting shaft drives the two gears to rotate. The two gears drive the rack to move up and down. The rack moves up and down through the fixed rod and the connecting column, making it convenient for the staff to take the test blade while ensuring the sealing of the experiment. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is a schematic diagram of the three-dimensional structure of a cooling effect test assembly for a high-pressure turbine blade.

[0018] Figure 2 This is a schematic diagram of the left-view structure of a high-pressure turbine blade cooling effect test assembly.

[0019] Figure 3 A partial three-dimensional enlarged diagram of the cooling effect test assembly of a high-pressure turbine blade Figure 1 .

[0020] Figure 4 A partial three-dimensional enlarged diagram of the cooling effect test assembly of a high-pressure turbine blade Figure 2 .

[0021] Figure 5 This is a schematic diagram of a partial three-dimensional explosion structure in a cooling effect test assembly of a high-pressure turbine blade.

[0022] Figure 6 A partial three-dimensional enlarged diagram of the cooling effect test assembly of a high-pressure turbine blade Figure 3 .

[0023] In the figure: 1. Mounting plate; 2. Locking assembly; 201. Test blade; 202. Through slot; 203. Limiting slot; 204. Locking rod; 205. Movable hole; 206. Connecting rod 1; 207. Spring; 208. Extrusion plate; 209. Knob; 210. Limiting rod; 3. Load-bearing column; 4. Fixed frame; 5. Base; 6. Mounting plate; 7. Servo motor; 8. Connecting shaft; 9. Gear; 10. Connecting rod 2; 11. Rack; 12. Fixed rod; 13. Connecting column; 14. Sealing frame; 15. Cooling air inlet hole; 16. Cooling air inlet pipe; 17. Cooling air flange; 18. Air outlet; 19. Connecting hole; 20. Connecting pipe; 21. Gas inlet pipe; 22. Gas flange; 23. Exhaust pipe; 24. Valve. DETAILED DESCRIPTION

[0024] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention. Example 1

[0025] Reference Figure 1 - Figure 5 , This embodiment provides a cooling effect test assembly for a high-pressure turbine blade, comprising a mounting plate 1 and a locking assembly 2, the locking assembly 2 being arranged on one side of the mounting plate 1, the locking assembly 2 comprising a test blade 201, the test blade 201 being movably connected to one side of the mounting plate 1, a through groove 202 being provided inside the test blade 201, a limiting groove 203 being provided on one side of the mounting plate 1, a locking rod 204 being movably connected to one side of the test blade 201, a movable hole 205 being provided inside the locking rod 204, a connecting rod 1 206 being movably connected inside the movable hole 205, a spring 207 being sleeved on the side surface of the connecting rod 1 206, a squeeze disc 208 being fixedly connected to one side of the squeeze disc 208, a knob 209 being fixedly connected to the side surface of the connecting rod 1 206, a limiting rod 210 being fixedly connected to the side surface of the connecting rod 1 206, a load-bearing column 3 being fixedly connected to the other side of the load-bearing column 3, a fixing frame 4 being fixedly connected to the fixing frame 4, a base 5, and a base 5. One side of the servo motor 7 is fixedly connected to the mounting plate 6. When in use, the staff starts the servo motor 7, and the servo motor 7 drives the connecting shaft 8 to rotate, and the connecting shaft 8 drives the two gears 9 to rotate. The two gears 9 drive the rack 11 to move up and down, and the rack 11 moves up and down through the fixing rod 12 and the connecting column 13, so as to facilitate the staff to take the test blade 201 while ensuring the sealing of the experiment. Then the staff aligns the through groove 202 on the test blade 201 with the limiting groove 203 on the mounting disk 1, and the staff passes the connecting rod 1 206 through the through groove 202 and inserts it into the limiting groove 203, and then presses the knob 209 downward. The knob 209 squeezes the connecting rod 1 206 downward through the squeezing disk 208, and then rotates the knob 209 to drive the limiting rod 210 to rotate ninety degrees. After the rotation is completed, release the knob 209. Under the elastic recovery ability of the spring 207, the limiting rod 210 contacts the inner wall of the limiting groove 203, and the test blade 201 is connected to the mounting disk 1. Example 2

[0026] Reference Figure 1 - Figure 6This embodiment is based on the previous embodiment, and is different from the previous embodiment in that a servo motor 7 is fixedly connected to the top of the mounting plate 6, a connecting shaft 8 is fixedly connected to the transmission end of the servo motor 7, a gear 9 is fixedly connected to the other side of the connecting shaft 8, a connecting rod 2 10 is fixedly connected to the other side of the gear 9, a rack 11 is meshedly connected to the one side of the gear 9, a fixing rod 12 is fixedly connected to the top of the rack 11, a connecting column 13 is fixedly connected to one side of the fixing rod 12, a sealing frame 14 is fixedly connected to one side of the connecting column 13, a cold air inlet hole 15 is provided at the top of the test blade 201, a cold air inlet hole 15 is fixedly connected to the top of the cold air inlet hole 15, a cold air inlet pipe 16 is fixedly connected to the side surface of the cold air inlet pipe 16, a cold air flange 17 is fixedly connected to the side surface of the cold air inlet pipe 16, an air outlet 18 is provided on the other side of the test blade 201, a connecting hole 19 is provided on one side of the test blade 201, and a connecting pipe 20 is fixedly connected to one side of the connecting hole 19 , one side of the sealing frame 14 is fixedly connected with a gas inlet pipe 21, and the side surface of the gas inlet pipe 21 is fixedly connected with a gas flange 22, and the other side of the sealing frame 14 is fixedly connected with an exhaust pipe 23, and a valve 24 is arranged inside the exhaust pipe 23. Then the staff drives the sealing frame 14 downward through the servo motor 7, and the gas inlet pipe 21 is connected to the external gas source and fixed through the gas flange 22 to simulate the high-temperature gas environment in the turbine engine. The gas flows in the sealing frame 14 and generates heat exchange with the test blade 201, the cold air inlet hole 15 and the cold air introduction pipe 16, the cold air enters the test blade 201 through the cold air inlet hole 15, and then enters each test blade 201 through the connecting hole 19 and the connecting pipe 20, and then is discharged from the air outlet 18, taking away the heat on the test blade 201. The gas and cold air after the test are discharged through the exhaust pipe 23, and the valve 24 is used to control the exhaust flow.

[0027] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above and that the present invention can be implemented in other specific forms without departing from the spirit or essential characteristics of the present invention. Therefore, the embodiments should be considered in all respects as illustrative and non-restrictive, and the scope of the present invention is defined by the appended claims, not the foregoing description, and all variations within the meaning and range of equivalents of the claims are intended to be encompassed within the present invention. Any reference sign in a claim should not be construed as limiting the claim to which it relates.

[0028] In addition, it should be understood that although this specification is described in terms of implementation methods, not every implementation method contains only one independent technical solution. This narrative method of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment can also be appropriately combined to form other implementation methods that can be understood by those skilled in the art.

Claims

1. A cooling efficiency test assembly for a high-pressure turbine blade, comprising a mounting plate (1) and a locking assembly (2), characterized in that: The locking assembly (2) is arranged on one side of the mounting plate (1), and the locking assembly (2) includes a test blade (201), the test blade (201) is movably connected to one side of the mounting plate (1), a through groove (202) is provided inside the test blade (201), a limiting groove (203) is provided on one side of the mounting plate (1), a locking rod (204) is movably connected to one side of the test blade (201), a movable hole (205) is provided inside the locking rod (204), a connecting rod (206) is movably connected inside the movable hole (205), a spring (207) is sleeved on the side surface of the connecting rod (206), a pressing plate (208) is fixedly connected to one side of the pressing plate (208), a knob (209) is fixedly connected to one side of the connecting rod (206), and a limiting rod (210) is fixedly connected to the side surface of the connecting rod (206).

2. A cooling efficiency test assembly for high-pressure turbine blades according to claim 1, characterized in that: The other side of the mounting plate (1) is fixedly connected to a load-bearing column (3), the other side of the load-bearing column (3) is fixedly connected to a fixing frame (4), the fixing frame (4) is fixedly connected to a base (5), and one side of the base (5) is fixedly connected to a mounting plate (6).

3. A cooling efficiency test assembly for high-pressure turbine blades according to claim 2, characterized in that: A servo motor (7) is fixedly connected to the top of the mounting plate (6), a connecting shaft (8) is fixedly connected to the transmission end of the servo motor (7), and a gear (9) is fixedly connected to the other side of the connecting shaft (8).

4. A cooling efficiency test assembly for high-pressure turbine blades according to claim 3, characterized in that: The other side of the gear (9) is fixedly connected to a second connecting rod (10), one side of the gear (9) is meshedly connected to a rack (11), the top of the rack (11) is fixedly connected to a fixing rod (12), one side of the fixing rod (12) is fixedly connected to a connecting column (13), and one side of the connecting column (13) is fixedly connected to a sealing frame (14).

5. The cooling efficiency test assembly for high-pressure turbine blades according to claim 1, characterized in that: A cold air inlet hole (15) is provided at the top of the test blade (201), a cold air inlet pipe (16) is fixedly connected to the top of the cold air inlet hole (15), and a cold air flange (17) is fixedly connected to the side surface of the cold air inlet pipe (16).

6. The cooling efficiency test assembly for high-pressure turbine blades according to claim 1, characterized in that: An air outlet hole (18) is provided on the other side of the test blade (201), a connection hole (19) is provided on one side of the test blade (201), and a connection pipe (20) is fixedly connected to one side of the connection hole (19).

7. The cooling efficiency test assembly for high-pressure turbine blades according to claim 4, characterized in that: One side of the sealing frame (14) is fixedly connected to a gas inlet pipe (21), and a side surface of the gas inlet pipe (21) is fixedly connected to a gas flange (22).

8. The cooling efficiency test assembly for high-pressure turbine blades according to claim 4, characterized in that: The other side of the sealing frame (14) is fixedly connected to an exhaust pipe (23), and a valve (24) is provided inside the exhaust pipe (23).

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