Turbine blade root extension circumferential seal structure leakage test device

Abstract

The utility model discloses a turbine blade stretchs root circumferential sealing structure leakage testing arrangement, include: base, adapter section, simulation blade, outer pressure plate group, inner pressure plate group, seal piece, compact disc and detection unit, wherein, the inside formation of base is gas collection cavity, and the adapter section sealed connection is in the top of base, and simulation blade is multiple and is along the circumferential sealing fixed in the top of adapter section through outer pressure plate group and inner pressure plate group, and the adjacent simulation blade forms the circumferential installation gap, and seal piece is along the circumferential sealing installation in the upper portion of simulation blade through compact disc, and detection unit is used for detecting the temperature, pressure and intake flow of gas collection cavity. This turbine blade stretchs root circumferential sealing structure leakage testing arrangement, can simulate measurement aero -engine under different working condition and structure condition through turbine blade stretchs root circumferential sealing structure's gas leakage amount, provides data support for aero -engine structure optimization and air system optimization.

Description

Technical Field

[0001] This utility model belongs to the field of leakage testing of sealing structures of aero-engines, and specifically provides a leakage testing device for the circumferential sealing structure of turbine blade root extension. Background Technology

[0002] The turbine of an aircraft engine is located next to the combustion chamber, and the main flow channel is filled with high-temperature and high-pressure combustion gases during operation. Figure 5 The red arrows indicate the flow area and direction of the high-temperature combustion gas. This high-temperature, high-pressure combustion gas enters the turbine disk cavity through the turbine rim seal, causing the turbine disk cavity temperature to be too high. However, although the turbine disk material is a high-temperature alloy, its heat resistance is far inferior to that of the mainstream blades, and the turbine disk cannot be made hollow, preventing the flow of cool air inside. Therefore, overheating of the turbine disk cavity will lead to uncontrollable disk deformation and fatigue. To prevent this, cooling gas is generally extracted from the cold-end components and passed through the rim seal to prevent the mainstream combustion gas from entering the disk cavity. However, if too much cooling gas is extracted, it will mix with the mainstream gas, which will reduce the turbine stage's operating efficiency. Therefore, quantitatively calibrating the leakage at various points on the turbine blades and rim is of great significance for optimizing the performance and structure of aero-engines.

[0003] Existing research has extensively analyzed the flow and heat transfer issues of turbine rim seals in aero-engines, but it has neglected the impact of leaked combustion gases through the circumferential sealing structure of the turbine blade root cavity on the turbine disk rim temperature, such as... Figure 5 As shown, the main gas flow will pass through the installation gap between blades 110 (such as...). Figure 5 (As shown by the green line in the image) After passing through the root cavity of the blade root 111, it leaks into the turbine disk cavity through the circumferential sealing structure 120 located at the rear of the blade root 111. Figure 5 The blue line in the diagram corresponds to the leakage flow, leading to excessively high turbine disk temperature. To address this issue, considering the unique structure and leakage path of the turbine blade root circumferential seal, and taking into account the turbine blade positional relationships under different operating conditions, a test device is designed to quantitatively calibrate the leakage of the turbine blade root circumferential seal structure. This will provide data support for the optimization of aero-engine structures and air systems, and is thus an urgent problem to be solved. Utility Model Content

[0004] Therefore, the purpose of this utility model is to provide a turbine blade root circumferential sealing structure leakage test device to quantitatively measure the amount of gas leakage through the root cavity of the circumferential sealing structure under different working and structural conditions, thereby improving the design accuracy of the amount of cooling gas extracted from the cold end components to prevent mainstream gas from invading the disk cavity, and thus improving the working efficiency of the turbine stage.

[0005] The technical solution provided by this utility model is: a leakage testing device for the circumferential sealing structure of a turbine blade root, comprising: a base, a transition section, a simulated blade, an outer pressure plate assembly, an inner pressure plate assembly, a sealing plate, a clamping plate, and a detection unit. The base has an annular air collection chamber inside, and multiple air inlets communicating with the air collection chamber are evenly arranged on the outer periphery of the base. Each air inlet is connected to an air source via a distribution cylinder. The transition section includes an outer ring and an inner ring, both of which are sealed to the top of the base, forming an annular cavity communicating with the air collection chamber. The simulated blade includes a first sealing section, a second sealing section, and a clearance fit section connecting the first and second sealing sections. The thickness of the clearance fit section is less than the thickness of the first and second sealing sections. The simulated blades are multiple and are circumferentially fitted above the annular cavity of the transition section. The first sealing section of the simulated blade is sealed and pressed against the upper part of the outer ring by the outer pressure plate group, and the second sealing section of the simulated blade is sealed and pressed against the upper part of the inner ring by the inner pressure plate group. The first sealing sections and the second sealing sections of adjacent simulated blades are tightly sealed together. A gap is formed between the clearance fitting sections of adjacent simulated blades to simulate the circumferential installation gap of the turbine blade. The sealing plate is circumferentially sealed and installed on the upper part of the clearance fitting section and is pressed and fixed by the pressure plate to simulate the circumferential sealing structure of the turbine blade root. The detection unit includes a temperature detection unit, a pressure detection unit, and a flow detection unit for detecting the temperature, pressure, and intake flow of the gas collecting cavity, respectively.

[0006] Preferably, a sealing ring is provided between the outer ring and the base and the first sealing section, and a sealing ring is provided between the inner ring and the base and the second sealing section.

[0007] Further preferably, the adapter section is connected to the base by bolts.

[0008] Further preferably, the turbine blade root circumferential sealing structure leakage test device also includes an outer gasket and an inner gasket, which are respectively installed above the first sealing section and the second sealing section of the simulated blade, and the outer pressure plate group and the inner pressure plate group press the simulated blade through the outer gasket and the inner gasket respectively.

[0009] Further preferably, both the outer pressure plate assembly and the inner pressure plate assembly include a pressure plate, an adjusting bolt, and a support column. The base is provided with a T-slot that mates with the adjusting bolt. The top of the adjusting bolt passes through the middle of the pressure plate. The support column is supported at one end of the pressure plate, and the other end of the pressure plate is pressed against the upper part of the first sealing section or the second sealing section.

[0010] In a further preferred embodiment, all the simulated blades arranged circumferentially above the transition section are fastened together in a circle by clamps.

[0011] In a further preferred embodiment, the simulated blade is provided with a limiting groove that mates with one end of the sealing plate, and the other end of the sealing plate is pressed and fixed by the pressing plate.

[0012] More preferably, a support frame is connected to the top of the inner ring, and the top of the pressure plate is connected to the support frame by bolts.

[0013] Further preferably, the flow detection unit is located at the air inlet end of the air distribution cylinder.

[0014] The turbine blade root circumferential sealing structure leakage testing device provided by this utility model has a reasonable structure, is easy to operate, and has reliable testing capabilities. It can measure the amount of gas leakage through the turbine blade root circumferential sealing structure under different operating conditions (pressure and temperature) and structural conditions (such as turbine blade installation clearance, root cavity structure, bolt preload, sealing plate length and surface roughness, etc.). The test results can provide data support for the optimization of aero-engine structure and air system, thereby improving the working efficiency of turbine stage and the overall performance of aero-engine. Attached Figure Description

[0015] The present invention will be further described in detail below with reference to the accompanying drawings and embodiments: Figure 1 A schematic diagram of the leakage test device for the turbine blade root circumferential sealing structure provided by this utility model; Figure 2 A partial cross-sectional view of the leakage test device for the turbine blade root circumferential sealing structure provided by this utility model; Figure 3 This is a schematic diagram simulating the structure of a blade; Figure 4 A schematic diagram of the turbine blade structure after the blade has been removed; Figure 5 This is a schematic diagram showing the positions of turbine blades, turbine disks, and the circumferential sealing structure at the root of turbine blades inside an aero-engine. Detailed Implementation

[0016] The present invention will be further explained below with reference to specific implementation schemes, but it is not limited to the present invention.

[0017] To determine the amount of gas leakage through the circumferential sealing structure at the turbine blade root under different operating and structural conditions of an aero-engine, and to improve the design accuracy of the amount of cooling gas drawn from cold-end components to prevent mainstream gas intrusion into the turbine disk cavity, thereby improving the turbine stage efficiency, such as... Figures 1 to 3As shown, this utility model provides a leakage testing device for the circumferential sealing structure of a turbine blade root, comprising: a base 1, a transition section 2, a simulated blade 3, an outer pressure plate assembly 4, an inner pressure plate assembly 5, a sealing plate 6, a pressure plate 7, and a detection unit. The base 1 has an annular air collection chamber 11 inside, and multiple air inlets 12 communicating with the air collection chamber 11 are evenly arranged on the outer periphery of the base. Each air inlet 12 is connected to an air source via a distribution cylinder. The transition section 2 includes an outer ring 21 and an inner ring 22, both of which are sealed to the top of the base 1, forming an annular cavity communicating with the air collection chamber 11. The simulated blade 3 includes a first sealing section 31, a second sealing section 32, and a clearance fit section 33 connecting the first sealing section 31 and the second sealing section 32. The thickness of the clearance fit section 33 is less than that of the first sealing section 31 and the second sealing section 32. The thickness of section 32, the simulated blades 3 are multiple and are arranged circumferentially above the annular cavity of the transition section 2, the first sealing section 31 of the simulated blade 3 is sealed and pressed above the outer ring 21 by the outer pressure plate group 4, the second sealing section 32 of the simulated blade 3 is sealed and pressed above the inner ring 22 by the inner pressure plate group 5, the first sealing section 31 and the second sealing section 32 of adjacent simulated blades 3 are sealed and connected, and a gap is formed between the clearance fitting sections 33 of adjacent simulated blades 3 to simulate the circumferential installation gap of the turbine blade, the sealing plate 6 is circumferentially sealed and installed on the upper part of the clearance fitting section 33 and pressed and fixed by the pressure plate 7 to simulate the circumferential sealing structure of the turbine blade root, the detection unit includes a temperature detection unit, a pressure detection unit and a flow detection unit for detecting the temperature, pressure and intake flow of the gas collecting chamber 11 respectively.

[0018] This turbine blade root circumferential sealing structure leakage testing device can measure the amount of gas leakage through the turbine blade root circumferential sealing structure under different operating conditions (pressure and temperature) and structural conditions (such as turbine blade installation clearance, root cavity structure, bolt preload, sealing plate length and surface roughness, etc.). The measurement method for the leakage corresponding to different turbine blade installation clearances under the set operating conditions is as follows: First, a simulated blade is selected according to the circumferential installation clearance of the blade to be tested, and it is fixed and installed above the annular cavity of the transition section using inner and outer pressure plate assemblies, sealing plates, and a clamping plate. The simulated blade (e.g., ...) Figure 3 The structure shown is achieved by using real turbine blades (such as...) Figure 4The leading edge plate A and blade (as shown) are deleted, and the trailing edge plate B and tenon C are simplified into a first sealing section and a second sealing section, respectively. The thickness of the clearance fit section is less than the thickness of the first sealing section and the second sealing section, thus forming a boss. By adjusting the height of the boss, different installation gaps between blades can be simulated. During assembly, the components can be positioned by the stop. Next, the temperature detection unit (e.g., temperature sensor) and the pressure detection unit (e.g., pressure sensor) are installed on the base to detect the temperature and pressure of the air collection chamber. The flow detection unit (e.g., flow meter) is connected to the air intake pipe. The air intake is divided into multiple paths by the air distribution cylinder and then connected to the air intake port of the base. A one-to-one connection is established; then, the pressure and temperature of the gas collecting chamber are adjusted and monitored in real time through the pressure detection unit and temperature detection unit, and the leakage under the target pressure and temperature conditions is measured through the flow detection unit; after the test of a set of circumferential installation clearances of the turbine blades is completed, the simulated blades are replaced, and the circumferential installation clearances of the blades are changed and the test continues to obtain the leakage corresponding to different circumferential installation clearances of the turbine blades under the target pressure and temperature conditions. Similarly, different structural states can be simulated by changing the root extension cavity structure, bolt preload, sealing plate length and surface roughness, and different working states can be simulated by adjusting the pressure and temperature of the gas collecting chamber, and finally the leakage data under different states can be obtained.

[0019] As an improvement to the technical solution, such as Figure 2 As shown, a sealing ring is provided between the outer ring 21 and the base 1 and the first sealing section 31, and a sealing ring is provided between the inner ring 22 and the base 1 and the second sealing section 32. Non-design leakage can be achieved through the sealing rings.

[0020] As an improvement to the technical solution, such as Figure 2 As shown, the adapter section 2 is connected to the base 1 by bolts.

[0021] As an improvement to the technical solution, such as Figure 2 As shown, the turbine blade root circumferential sealing structure leakage test device also includes an outer gasket 8 and an inner gasket 9. The outer gasket 8 and the inner gasket 9 are respectively installed above the first sealing section 31 and the second sealing section 32 of the simulated blade 3. The outer pressure plate group 4 and the inner pressure plate group 5 press the simulated blade 3 through the outer gasket 8 and the inner gasket 9 respectively.

[0022] As an improvement to the technical solution, such as Figure 2As shown, both the outer pressure plate assembly 4 and the inner pressure plate assembly 5 include a pressure plate, an adjusting bolt, and a support column. The base 1 is provided with a T-slot that mates with the adjusting bolt. The top of the adjusting bolt passes through the middle of the pressure plate. The support column is supported on one end of the pressure plate. The other end of the pressure plate is pressed against the upper part of the first sealing section 31 or the second sealing section 32 to achieve the pressing and fixing of the first sealing section and the second sealing section.

[0023] As an improvement to the technical solution, such as Figure 1 As shown, all the simulated blades 3 arranged circumferentially above the transition section 2 are tightened into a circle by clamps 10 to achieve sealing between the first sealing section and between the second sealing section.

[0024] As an improvement to the technical solution, the simulated blade 3 is provided with a limiting groove that mates with one end of the sealing plate 6. One end of the sealing plate 6 is inserted into the limiting groove, and the other end of the sealing plate 6 is pressed and fixed by the pressing plate 7.

[0025] As an improvement to the technical solution, such as Figure 2 As shown, a support frame 221 is connected to the top of the inner ring 22, and the top of the clamping plate 7 is connected to the support frame 221 by bolts to achieve clamping of the simulated blade.

[0026] As an improvement to the technical solution, the flow detection unit is located at the air inlet end of the air distribution cylinder.

[0027] The specific embodiments of this utility model are written in a progressive manner, emphasizing the differences between each implementation scheme, and the similar parts can be referred to each other.

[0028] The embodiments of the present invention have been described in detail above with reference to the accompanying drawings. However, the present invention is not limited to the above embodiments. Within the scope of knowledge possessed by those skilled in the art, various changes can be made without departing from the spirit of the present invention.

Claims

1. A leakage testing device for a turbine blade root circumferential sealing structure, characterized in that, include: The base (1), transition section (2), simulated blade (3), outer pressure plate group (4), inner pressure plate group (5), sealing plate (6), pressing plate (7), and detection unit are provided. The base (1) has an annular air collection chamber (11) inside. Multiple air inlets (12) communicating with the air collection chamber (11) are evenly arranged on the outer periphery of the base. Each air inlet (12) is connected to an air source via a distribution cylinder. The transition section (2) includes an outer ring (21) and an inner ring (22). The outer ring (21) and inner ring (22) are sealed to the top of the base (1) and form an annular cavity communicating with the gas collection chamber (11). The simulated blade (3) includes a first sealing section (31), a second sealing section (32), and a clearance fit section (33) connecting the first sealing section (31) and the second sealing section (32). The thickness of the clearance fit section (33) is less than the thickness of the first sealing section (31) and the second sealing section (32). Multiple simulated blades (3) are arranged circumferentially above the annular cavity of the transition section (2). The first sealing section (31) of the simulated blade (3) is sealed and pressed against the outer ring (21) by the outer pressure plate group (4). The second sealing section (32) of the simulated blade (3) is sealed and pressed against the inner ring (22) by the inner pressure plate group (5). The first sealing section (31) and the second sealing section (32) of adjacent simulated blades (3) are sealed and connected. The gap between the clearance fitting section (33) of adjacent simulated blades (3) is formed to simulate the circumferential installation gap of the turbine blade. The sealing plate (6) is circumferentially sealed and installed on the upper part of the clearance fitting section (33) and pressed and fixed by the pressure plate (7) to simulate the circumferential sealing structure of the turbine blade root. The detection unit includes a temperature detection unit, a pressure detection unit and a flow detection unit for detecting the temperature, pressure and intake flow of the gas collecting chamber (11).

2. The leakage test device for the turbine blade root circumferential sealing structure according to claim 1, characterized in that, A sealing ring is provided between the outer ring (21) and the base (1) and the first sealing section (31), and a sealing ring is provided between the inner ring (22) and the base (1) and the second sealing section (32).

3. The turbine blade root circumferential sealing structure leakage test device according to claim 1, characterized in that, The adapter section (2) is connected to the base (1) by bolts.

4. The leakage test device for the turbine blade root circumferential sealing structure according to claim 1, characterized in that, It also includes an outer gasket (8) and an inner gasket (9), which are installed above the first sealing section (31) and the second sealing section (32) of the simulated blade (3), respectively. The outer pressure plate group (4) and the inner pressure plate group (5) press the simulated blade (3) through the outer gasket (8) and the inner gasket (9).

5. The turbine blade root circumferential sealing structure leakage test device according to claim 1, characterized in that, The outer pressure plate assembly (4) and the inner pressure plate assembly (5) both include a pressure plate, an adjusting bolt, and a support column. The base (1) is provided with a T-shaped groove that mates with the adjusting bolt. The top of the adjusting bolt passes through the middle of the pressure plate. The support column is supported at one end of the pressure plate. The other end of the pressure plate is pressed against the upper part of the first sealing section (31) or the second sealing section (32).

6. The leakage test device for the turbine blade root circumferential sealing structure according to claim 1, characterized in that, All the simulated blades (3) arranged circumferentially above the transition section (2) are fastened together in a circle by clamps (10).

7. The leakage test device for the turbine blade root circumferential sealing structure according to claim 1, characterized in that, The simulated blade (3) is provided with a limiting groove that matches one end of the sealing plate (6), and the other end of the sealing plate (6) is pressed and fixed by the pressing plate (7).

8. The turbine blade root circumferential sealing structure leakage test device according to claim 7, characterized in that, The top of the inner ring (22) is connected to a support frame (221), and the top of the pressure plate (7) is connected to the support frame (221) by bolts.

9. The leakage test device for the turbine blade root circumferential sealing structure according to claim 1, characterized in that, The flow detection unit is located at the air inlet end of the air distribution cylinder.

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