Turbine high conductivity analog ring

Abstract

The application belongs to the field of aero-engine simulation test, and particularly relates to a turbine high-conductivity simulation ring, which comprises an outer ring, an outer disc in a circular ring shape and an outer cylinder formed by the axial extension of the outer wall of the outer disc, the outer cylinder having a plurality of circumferentially uniformly distributed first mounting holes, the first mounting holes being axial through holes; an inner ring, an inner disc in a circular ring shape and an inner cylinder formed by the axial extension of the outer wall of the inner disc, the inner cylinder having a plurality of circumferentially uniformly distributed second mounting holes, the second mounting holes being axial through holes; a plurality of high-conductivity blades distributed in a circumferential direction, each high-conductivity blade having a first internally threaded hole corresponding to the first mounting hole and a second internally threaded hole corresponding to the second mounting hole, a first bolt being threadedly connected through the first mounting hole and the first internally threaded hole, and a second bolt being threadedly connected through the second mounting hole and the second internally threaded hole; by installing the high-conductivity blades of the turbine high-conductivity simulation ring in a split manner, the machining cost can be greatly reduced.

Description

Technical Field

[0001] This application belongs to the field of aero-engine simulation testing, and specifically relates to a turbine high-conductivity simulation ring. Background Technology

[0002] Modern aero-engines mostly employ annular combustors. Ignition performance is a crucial factor in combustor design, especially high-altitude ignition performance, which is a key determinant of a successful combustor design. Traditional combustor component ignition tests often fail to consider the blocking effect of high-pressure turbine guide vanes on the combustor outlet, or simply simulate the throttling area of ​​the high-guide vanes using perforated circular plates. In such cases, the airflow conditions at the combustor outlet differ significantly from the actual conditions of the combustor mounted on the entire engine, leading to substantial discrepancies between test results and the overall engine ignition performance. Using real turbine high-guide vanes in component testing not only introduces significant complexity to the test system and equipment but also increases testing costs due to the complex manufacturing processes of high-guide vanes, which are typically made of directionally cast high-temperature alloys or single-crystal metals. Summary of the Invention

[0003] To address the aforementioned problems, this application provides a turbine high-conductivity simulation ring, comprising:

[0004] The outer ring includes a circular outer disk and an outer cylinder formed by the axial extension of the inner wall of the outer disk. The outer cylinder has a plurality of circumferentially evenly distributed first mounting holes, and the first mounting holes are axially oriented through holes.

[0005] The inner ring includes an annular inner disk and an inner cylinder formed by the axial extension of the outer wall of the inner disk. The inner cylinder has a plurality of circumferentially evenly distributed second mounting holes, and the second mounting holes are axially oriented through holes.

[0006] Multiple high-guide blades are distributed circumferentially. Each high-guide blade has a first internal threaded hole corresponding to the first mounting hole and a second internal threaded hole corresponding to the second mounting hole. A first bolt passes through the first mounting hole and is threadedly connected to the first internal threaded hole, and a second bolt passes through the second mounting hole and is threadedly connected to the second internal threaded hole.

[0007] Both the outer and inner discs are threadedly connected to the rear end of the combustion chamber test piece via their mounting holes.

[0008] Preferably, the first and second internal threaded holes of the same high-guide blade are on the same axis, and the inner wall surface of the outer cylinder or the outer wall surface of the inner cylinder has a boss for limiting the high-guide blade. The first and second internal threads are formed by tapping on the same through hole. This structure can greatly reduce the processing cost of the high-guide blade. However, the threaded holes on the same axis will give the high-guide blade the freedom to rotate along the axial direction of the threaded hole. Therefore, the corresponding boss on the inner wall surface of the outer cylinder or the outer wall surface of the inner cylinder is provided to limit the high-guide blade's freedom to rotate along the axial direction of the threaded hole, and will not hinder the installation of the high-guide blade.

[0009] Preferably, the first internal threaded hole and the second internal threaded hole of the same high-guide blade are misaligned in the axial direction or in the circumferential direction. The installation of the first internal threaded hole and the second internal thread can completely fix the high-guide blade. The structure is simple, easy to install, and easy to process.

[0010] Preferably, the inner wall surface of the outer cylinder is curved inward in the axial direction, and the outer wall surface of the inner cylinder is a curved surface. The curved surface has the same curvature as the surface of the turbine high-guide ring simulated by this turbine high-guide ring, which can simulate the same function as the turbine high-guide ring and improve the authenticity of the test data.

[0011] Preferably, both the inner wall of the outer cylinder and the outer wall of the inner cylinder are flat. Under certain conditions, the flat surface can greatly reduce the processing cost and is a preferred choice that can well balance cost and test data effect in non-high-requirement environments.

[0012] Preferably, the inner wall surface of the outer cylinder is inclined inward in the axial direction to form a tapered surface with a slope. The inclined surface, i.e. the tapered surface with a slope, is a sloped surface simulated according to the profile of the turbine high-guide ring simulated by this turbine high-guide ring. Under the condition of low plane cost, the plane is tilted to restore the real profile as much as possible.

[0013] Preferably, the material of the turbine high-conductivity simulation ring includes alloys or stainless steel that can withstand a maximum temperature of no more than 1000°C. The material types include GH536 and GH188. Using a material with lower strength than that of the real turbine ring can effectively control costs, and since the test time is shorter than that of actual flight, this material is perfectly suitable.

[0014] Preferably, both the first internal threaded hole and the second internal threaded hole are through holes with internal threads, and the inner cylinder has a first through hole at the corresponding position of the first internal threaded hole that is connected to the first bolt, and the outer cylinder has a second through hole at the corresponding position of the second internal threaded hole that is connected to the second bolt. In other words, the outer cylinder and the inner cylinder have two sets of mounting holes when installing the same high-guide blade, and are fixed by two bolts respectively.

[0015] Preferably, the mounting hole of the inner disk is an axial through hole, which extends radially toward the center of the inner disk until it communicates with the inner wall surface of the inner disk. The radial extension of the mounting hole allows for installation with leeway even when the device has a large error, which reduces the requirements for the machining accuracy of the turbine high-conductivity simulation ring and can significantly reduce the cost of the high-conductivity simulation ring.

[0016] The advantages of this application include: by installing the high-guide-rate blades of the turbine high-guide-rate simulation ring separately, the processing cost can be greatly reduced. In actual processing environments, if even one blade of an integrated high-guide-rate blade fails to meet the requirements, the entire turbine high-guide-rate simulation ring cannot be used. However, the separate high-guide-rate blades can greatly reduce the scrap rate, thereby reducing costs. Furthermore, by using the above-mentioned different installation methods, the cost of using the simulation ring is greatly reduced, solving the data distortion problem caused by the inability to use real turbine rings due to cost issues. In addition, the number and blade profile of the high-guide-rate blades can be adjusted according to the test requirements, greatly improving the versatility of this device. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of a turbine high-conductivity simulation ring;

[0018] Figure 2 This is a schematic diagram of the outer ring road;

[0019] Figure 3 This is a schematic diagram of the inner ring road;

[0020] Figure 4 This is a schematic diagram of a high-conductivity blade;

[0021] Figure 5 This is a cross-sectional view of a high-conductivity blade;

[0022] Among them, 1-outer ring, 12-outer disk, 11-outer cylinder, 2-inner ring, 22-inner disk, 21-inner cylinder, 3-high-guide blade. Detailed Implementation

[0023] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, not all, of the embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without inventive effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0024] like Figure 1 As shown, this application provides a turbine high-conductivity simulation ring, comprising:

[0025] Outer ring 1, as Figure 2 As shown, it includes an annular outer disk 12 and an outer cylinder 11 formed by axially extending the inner wall of the outer disk 12. The outer cylinder 11 has a plurality of circumferentially evenly distributed first mounting holes, and the orientation of the first mounting holes is an axial through hole.

[0026] Inner Ring 2 Figure 3 As shown, it includes an annular inner disk 22 and an inner cylinder 21 formed by the axial extension of the outer wall of the inner disk 22. The inner cylinder 21 has a plurality of circumferentially evenly distributed second mounting holes, and the second mounting holes are through holes facing the axial direction.

[0027] Multiple high-conductivity blades distributed circumferentially, such as Figure 4 As shown, each high-conductivity blade 3 has a first internal threaded hole corresponding to the first mounting hole, as shown in the figure. Figure 5 As shown, the second internal threaded hole corresponds to the second mounting hole. The first bolt passes through the first mounting hole and is threaded to the first internal threaded hole, and the second bolt passes through the second mounting hole and is threaded to the second internal threaded hole. The outer disk 12 and inner disk 22 of the high-guide simulation ring are both connected to the outer ring casing of the combustion chamber by 20 bolts with a diameter of Φ12. The high-guide blades, the outer edge profile of the high-guide, and the inner edge profile of the high-guide are consistent with the existing high-pressure turbine guide. The inner disk 22 is connected to the inner ring casing of the combustion chamber by 60 bolts. The inner mounting edge is a racetrack-shaped open hole to ensure that the simulation ring can expand in the radial direction after being heated, avoid the connecting bolts being subjected to shear force, and at the same time reduce the assembly accuracy.

[0028] Both the outer disk 12 and the inner disk 22 are threadedly connected to the rear end of the combustion chamber test piece through their mounting holes.

[0029] Preferably, the first and second internal threaded holes of the same high-guide blade 3 are on the same axis, and the inner wall surface of the outer cylinder 11 or the outer wall surface of the inner cylinder 21 has a boss that limits the high-guide blade 3. The first and second internal threads are formed by tapping on the same through hole. This structure can greatly reduce the processing cost of the high-guide blade 3. However, the threaded holes on the same axis will give the high-guide blade 3 the freedom to rotate along the axial direction of the threaded hole. Therefore, the boss that limits the high-guide blade 3 is located on the inner wall surface of the outer cylinder 11 or the outer wall surface of the inner cylinder 21. This can limit the freedom of the high-guide blade 3 to rotate along the axial direction of the threaded hole and will not hinder the installation of the high-guide blade.

[0030] Preferably, the first internal threaded hole and the second internal threaded hole of the same high-guide blade 3 are misaligned in the axial direction or in the circumferential direction. The installation of the first internal threaded hole and the second internal thread can completely fix the high-guide blade 3. The structure is simple, easy to install, and easy to process.

[0031] Preferably, the inner wall surface of the outer cylinder 11 is curved inward in the axial direction, and the outer wall surface of the inner cylinder 21 is a curved surface. The curved surface has the same curvature as the surface of the turbine high-guide ring simulated by this turbine high-guide ring, which can simulate the same function as the turbine high-guide ring and improve the authenticity of the test data.

[0032] Preferably, the inner wall surface of the outer cylinder 11 and the outer wall surface of the inner cylinder 21 are both planar. Under certain conditions, the planar shape can greatly reduce the processing cost and is a preferred choice that can well balance cost and test data effect in non-high-requirement environments.

[0033] Preferably, the inner wall surface of the outer cylinder 11 is inclined inward in the axial direction to form a tapered surface with a slope. The inclined surface, i.e. the tapered surface with a slope, is a sloped surface simulated according to the profile of the turbine high-guide ring simulated by this turbine high-guide ring. Under the condition of low plane cost, the plane is tilted to restore the real profile as much as possible.

[0034] Preferably, the material of the turbine high-conductivity simulation ring includes alloys or stainless steel that can withstand a maximum temperature of no more than 1000°C. The material types include GH536 and GH188. Using a material with lower strength than that of the real turbine ring can effectively control costs, and since the test time is shorter than that of actual flight, this material is perfectly suitable.

[0035] Preferably, both the first internal threaded hole and the second internal threaded hole are through holes with internal threads, and the inner cylinder 21 has a first through hole at the position corresponding to the first internal threaded hole that is connected to the first bolt, and the outer cylinder 11 has a second through hole at the position corresponding to the second internal threaded hole that is connected to the second bolt. That is to say, the outer cylinder 11 and the inner cylinder have two sets of mounting holes when installing the same high-guide blade, and are fixed by two bolts respectively.

[0036] Preferably, the mounting hole of the inner disk 22 is an axial through hole, which extends radially toward the center of the inner disk 22 until it communicates with the inner wall surface of the inner disk 22. The radial extension of the mounting hole allows for installation with leeway even when the device has a large error, which reduces the requirements for the machining accuracy of the turbine high-conductivity simulation ring and can significantly reduce the cost of the high-conductivity simulation ring.

[0037] The advantages of this application include: by installing the high-guide-rate blades of the turbine high-guide-rate simulation ring separately, the processing cost can be greatly reduced. In the actual processing environment, if even one blade of the integrated high-guide-rate blade fails to meet the requirements, the entire turbine high-guide-rate simulation ring cannot be used. The separate high-guide-rate blades can greatly reduce the scrap rate, thereby reducing costs. Furthermore, by using the above-mentioned different installation methods, the cost of using the simulation ring is greatly reduced, solving the data distortion problem caused by the inability to use real turbine rings due to cost issues in the past.

[0038] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A turbine high-conductivity simulation ring, characterized in that, include: The outer ring (1) includes an annular outer disk (12) and an outer cylinder (11) formed by axially extending the inner wall of the outer disk (12). The outer cylinder (11) has a plurality of circumferentially evenly distributed first mounting holes. The inner ring (2) includes an annular inner disk (22) and an inner cylinder (21) formed by the axial extension of the outer wall of the inner disk (22). The inner cylinder (21) has a plurality of circumferentially evenly distributed second mounting holes. Multiple high-guide blades (3) are distributed circumferentially. Each high-guide blade (3) has a first internal threaded hole corresponding to the first mounting hole and a second internal threaded hole corresponding to the second mounting hole. A first bolt passes through the first mounting hole and is threadedly connected to the first internal threaded hole, and a second bolt passes through the second mounting hole and is threadedly connected to the second internal threaded hole. The outer disk (12) and the inner disk (22) are both threadedly connected to the rear end of the combustion chamber test piece through their mounting holes.

2. The turbine high-conductivity simulation ring as described in claim 1, characterized in that, The first internal threaded hole and the second internal threaded hole of the same high-guide blade (3) are on the same axis, and the inner wall surface of the outer cylinder (11) or the outer wall surface of the inner cylinder (21) has a boss that limits the high-guide blade (3).

3. The turbine high-conductivity simulation ring as described in claim 1, characterized in that, The first internal threaded hole and the second internal threaded hole of the same high-conductivity blade (3) are misaligned in the axial direction or in the circumferential direction.

4. The turbine high-conductivity simulation ring as described in claim 1, characterized in that, The inner wall surface of the outer cylinder (11) is curved inward in the axial direction, and the outer wall surface of the inner cylinder (21) is a curved surface.

5. The turbine high-conductivity simulation ring as described in claim 1, characterized in that, The inner wall surface of the outer cylinder (11) and the outer wall surface of the inner cylinder (21) are both planes.

6. The turbine high-conductivity simulation ring as described in claim 5, characterized in that, The inner wall of the outer cylinder (11) is inclined inward in the axial direction.

7. The turbine high-conductivity simulation ring as described in claim 1, characterized in that, The materials for the turbine high-conductivity simulation ring include alloys or stainless steel that can withstand a maximum temperature of no more than 1000℃.

8. The turbine high-conductivity simulation ring as described in claim 3, characterized in that, Both the first internal threaded hole and the second internal threaded hole are through holes with internal threads. The inner cylinder (21) has a first through hole at the position corresponding to the first internal threaded hole, which is connected to the first bolt. The outer cylinder (11) has a second through hole at the position corresponding to the second internal threaded hole, which is connected to the second bolt.

9. The turbine high-conductivity simulation ring as described in claim 1, characterized in that, The mounting hole of the inner disk (22) is an axial through hole, which extends radially toward the center of the inner disk (22) until it communicates with the inner wall surface of the inner disk (22).

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