A turbine outer ring connection structure and its thermal matching test device and test method

Abstract

This application discloses a turbine outer ring connection structure, a thermal matching test apparatus, and a test method thereof, belonging to the field of aerospace engine testing technology. The turbine outer ring connection structure includes a turbine outer ring assembly: the turbine outer ring assembly includes the turbine outer ring and a metal casing connection assembly, the metal casing connection assembly includes a metal casing and a connector, a first connection hole is defined in the outer wall of the metal casing, and the connector is used to securely connect the turbine outer ring and the metal casing; the outer wall of the metal casing is defined by a plurality of displacement measurement holes spaced apart, and the displacement measurement holes are used to cooperate with preset markings on the turbine outer ring to observe and measure the displacement deformation of the turbine outer ring relative to the metal casing. The turbine outer ring is a monolithic CMC turbine outer ring, and the turbine outer ring connection structure is a full-ring assembly structure that enables modular installation. The thermal matching test apparatus can perform thermal fatigue testing of the CMC outer ring with alternating heating and cooling load cycles.

Description

Technical Field

[0001] The present application relates to the field of aero-engine testing technology, and in particular, to a turbine outer ring connection structure, and a thermal matching test device applied to the above-mentioned turbine outer ring connection structure. In addition, the present application also relates to a test method applied to the above-mentioned thermal matching test device. Background Art

[0002] The information provided in this section is for the purpose of generally presenting the background of the present application. To the extent described in this section, the work of the presently named inventors and aspects of the description that may not constitute prior art at the time of filing are neither explicitly nor implicitly admitted to be prior art to the present application.

[0003] Currently, one of the key approaches to improving aircraft engine performance is to increase the gas temperature before the turbine. However, this increased gas temperature poses a significant challenge to metal turbine hot-end components, particularly the turbine outer ring, which is subject to harsh environmental conditions. To address this issue, ceramic matrix composites (CMCs) are currently being used to manufacture the outer ring. To support the engineering application of this new material, it is necessary to verify that the ceramic outer ring support structure can withstand deformation coordination under high-temperature conditions.

[0004] The vast majority of existing engines use a segmented metal turbine outer ring, which is in contact with the metal turbine casing through a hook structure. However, for this mature connection structure, the stability and perfection of the existing structure have been verified through many tests at home and abroad. However, there are still many gaps in the component-level assessment method for the turbine outer ring made of ceramic materials, and the component-level assessment of the connection structure has not been fully carried out.

[0005] Our research revealed that existing technologies typically utilize high-temperature gas heating for thermal matching tests of the outer ring. However, high-temperature gas heating requires extensive test equipment, including large gas supply equipment, combustion chambers, aviation kerosene, cooling media, large test benches, and automatic control systems. This results in lengthy preparation and commissioning times. Furthermore, the presence of high-temperature gas during the test requires consideration of piping cooling protection, test piece cooling and sealing, and emergency safety devices. This complicates miniaturization of the test equipment, ultimately leading to high testing costs. Furthermore, the high-temperature impact zone created by gas impact testing on the test piece is relatively large, making deformation measurement during thermal matching tests of small outer ring connections challenging. Furthermore, the measurement equipment must be resistant to the effects of high temperatures. Therefore, a new test protocol is needed to verify the reliability and deformation compatibility of the connection between the CMC outer ring and metal components under high-temperature service conditions, thereby supporting the engineering application of CMC turbine outer rings.

[0006] It should be noted that the information disclosed in the above background technology section is only used to enhance the understanding of the background of this application, and therefore may include information that does not constitute prior art known to ordinary technicians in this field. Summary of the Invention

[0007] In view of at least one of the above technical problems, the present application provides a turbine outer ring connection structure and its thermal matching test device and test method, which are designed for component-level assessment of integral CMC outer rings, wherein the turbine outer ring is an integral CMC turbine outer ring, and the turbine outer ring connection structure is a full-ring assembly structure that can achieve modular installation. The thermal matching test device can realize thermal fatigue testing of the CMC outer ring with alternating heating-cooling load cycles.

[0008] At the same time, the present application also provides a test method applied to the above-mentioned thermal matching test device.

[0009] According to one aspect of the present application, a turbine outer ring connection structure is provided, comprising a turbine outer ring assembly:

[0010] The turbine outer ring assembly includes a turbine outer ring and a metal casing connection assembly, the metal casing connection assembly includes a metal casing and a connecting piece, the metal casing is a full-ring structure and a limiting groove is provided on its inner ring, the limiting groove is used to limit the turbine outer ring, the outer wall of the metal casing is provided with a first connecting hole, the connecting piece is used to pass through the connecting hole and cooperate with a second connecting hole preset on the turbine outer ring to fasten the turbine outer ring and the metal casing;

[0011] A plurality of displacement measurement holes are provided at intervals on the outer wall of the metal casing. The displacement measurement holes are used to cooperate with preset marks on the outer ring of the turbine to observe and measure the displacement deformation of the outer ring of the turbine relative to the metal casing.

[0012] In some embodiments of the present application, the turbine outer ring is a full-ring structure made of ceramic-based composite materials.

[0013] In some embodiments of the present application, a plurality of positioning bosses are arranged at intervals on the outer wall of the metal receiver, and the positioning bosses are used to cooperate with an external device to limit the installation of the metal receiver.

[0014] In some embodiments of the present application, a plurality of displacement measurement holes are arranged in segments along the circumference of the metal casing to measure the displacement deformation of each segment of the turbine outer ring.

[0015] According to another aspect of the present application, a thermal matching test device is provided for performing a thermal matching test on the above-mentioned turbine outer ring connection structure to assess the connection matching effect between the turbine outer ring and the metal casing. The thermal matching test device includes a mounting platform, a mounting member, a stopper, a cooling tube, and a radiation lamp tube:

[0016] The mounting part and the limiting part are both arranged on the mounting platform. The mounting part is a cylindrical structure with an open top. The limiting part is a cylindrical structure. The limiting part is located inside the mounting part and there is a partition cavity between the limiting part and the mounting part. The limiting part is used to support the limited turbine outer ring assembly. The radiation lamp tube is arranged in the partition cavity. The radiation lamp tube is used to heat the turbine outer ring assembly. A cooling nozzle is provided in the limiting part. The cooling nozzle is connected to the cooling pipe. The cooling pipe is used to connect to an external cooling air source. The cooling nozzle is used to spray cooling airflow to cool the turbine outer ring assembly.

[0017] In some embodiments of the present application, the thermal matching test device also includes a lamp tube bracket supported in the partition cavity, the lamp tube bracket is used to support and fix the radiation lamp tube, there are multiple radiation lamp tubes, and the multiple radiation lamp tubes are arranged in a circular array in the partition cavity, an annular mounting frame is provided in the limiting member, and there are multiple cooling nozzles, and the multiple cooling nozzles are arranged in a circular array on the outer wall of the annular mounting frame.

[0018] In some embodiments of the present application, a plurality of test measurement holes are spaced apart on the side wall of the mounting member, and the test measurement holes are used for temperature measuring instruments to monitor the temperature of the turbine outer ring and the metal casing.

[0019] In some embodiments of the present application, a side wall of the mounting member is provided with a radiation-proof heat-insulating component, which is used to reduce heat loss in the compartment cavity and isolate radiation from the radiation lamp tube.

[0020] According to another aspect of the present application, a test method using the above-mentioned thermal matching test device is also provided, comprising the following steps:

[0021] S100, sleeve the turbine outer ring assembly onto the outer wall of the limiting member, and monitor the temperature of the turbine outer ring and the metal casing in real time using a temperature measuring instrument;

[0022] S200, turning on the radiation lamp to heat the turbine outer ring assembly to 800-1000°C;

[0023] S300, turning on the cooling nozzle to cool the turbine outer ring assembly to room temperature, so as to achieve a complete thermal matching cycle;

[0024] S400, measuring the deformation data of the turbine outer ring and the metal casing to determine whether the thermal matching test of the entire turbine outer ring assembly is qualified. If qualified, proceed to step S500;

[0025] S500. Conduct a directional heating-cooling load cycle alternating test on the turbine outer ring assembly in sections. Divide the turbine outer ring assembly into multiple sections along the circumferential direction. Turn on the radiation lamp corresponding to the first section of the turbine outer ring assembly to heat the first section to 800-1000°C. After stopping the heating, turn on the cooling nozzle corresponding to the first section of the turbine outer ring assembly to cool the first section to room temperature. Then measure the temperature and deformation data of the turbine outer ring and the metal casing to complete the thermal matching cycle test of the first section of the turbine outer ring assembly. Then, according to the thermal matching cycle test steps of the first section of the turbine outer ring assembly, conduct thermal matching cycle tests on the second section, the third section...the nth section of the turbine outer ring assembly in sequence until the thermal matching cycle of each section of the entire circle of the turbine outer ring assembly is completed.

[0026] In some embodiments of the present application, all radiation lamps use the same preset power level in step S200, and in step S500, the radiation lamps at the tested section corresponding to the turbine outer ring assembly use the preset power, while the other radiation lamps reduce power or are turned off.

[0027] This application has the following beneficial effects:

[0028] The turbine outer ring connection structure of the present application is a full-ring assembly structure, including a turbine outer ring assembly. The turbine outer ring assembly includes a turbine outer ring and a metal casing connection assembly. The metal casing of the metal casing connection assembly can limit the installation of the turbine outer ring, and the turbine outer ring and the metal casing are connected and assembled through connectors to facilitate subsequent thermal matching tests. At the same time, a plurality of displacement measurement holes are spaced apart on the outer wall of the metal casing. The displacement deformation of the turbine outer ring relative to the metal casing during the thermal matching test can be measured through the displacement measurement holes in conjunction with the preset marks on the turbine outer ring, which facilitates the analysis and judgment of the assembly effect. The turbine outer ring assembly has a streamlined structure, which can facilitate overall test verification.

[0029] The thermal matching test device of the present application can realize the modular installation of the turbine outer ring assembly, and adopts radiation heating instead of conventional gas heating as the heat source for the CMC outer ring thermal matching test, which can realize directional heating of the working surface of the turbine outer ring assembly. During the test process, there is no need to frequently disassemble the turbine outer ring assembly, and the turbine outer ring assembly can be subjected to heating-cooling load cycle alternating tests in sections, which greatly improves the efficiency of the test and the accuracy of assembly verification. The test device is very small and easy to use as a whole, and there are no safety hazards of traditional tests using gas heating. The test device can complete the test with only electricity and a small amount of cooling air, and the test cost is low.

[0030] The test method for the thermal matching test device of this application also has the aforementioned beneficial effects. This application can conduct thermal matching tests on all existing ceramic turbine outer rings, requiring minimal space and equipment. The heating area can be controlled to achieve segmented, directional heating and cooling alternating tests, resulting in high test efficiency. This application can effectively replace such high-temperature gas test equipment, offering unique advantages in shortening test time and reducing test costs.

[0031] Of course, any product implementing this application does not necessarily need to achieve all of the advantages described above. In addition to the purposes, features, and advantages described above, this application also has other purposes, features, and advantages. This application will be further described in detail below with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] The accompanying drawings, which constitute part of this application, are intended to provide a further understanding of this application. The exemplary embodiments and descriptions of this application are intended to explain this application and do not constitute an improper limitation on this application. In the accompanying drawings:

[0033] Figure 1 This is a schematic diagram of the overall structure of the thermal matching test device according to the preferred embodiment of the present application;

[0034] Figure 2 This is a schematic structural diagram of the turbine outer ring connection structure of a preferred embodiment of the present application;

[0035] Figure 3 This is a schematic diagram of the installation of a radiation lamp tube according to a preferred embodiment of the present application;

[0036] Legend: 10. Turbine outer ring assembly; 101. Turbine outer ring; 102. Metal casing connection assembly; 1021. Metal casing; 1022. Displacement measurement hole; 1023. Positioning boss; 1024. Connector; 1. Mounting platform; 2. Mounting part; 3. Limiting part; 4. Cooling pipe; 5. Radiation lamp tube; 6. Cooling nozzle; 7. Test measurement hole. DETAILED DESCRIPTION

[0037] The embodiments of the present application are described in detail below with reference to the accompanying drawings, but the present application can be implemented in a variety of different ways defined and covered below.

[0038] A turbine outer ring connection structure includes a turbine outer ring assembly 10:

[0039] The turbine outer ring assembly 10 includes a turbine outer ring 101 and a metal casing connecting assembly 102. The metal casing connecting assembly 102 includes a metal casing 10211 and a connecting piece 1024. The metal casing 10211 is a full-ring structure and has a limiting groove defined in its inner ring. The limiting groove is used to limit the turbine outer ring 101. A first connecting hole is defined in the outer wall of the metal casing 10211. The connecting piece 1024 is used to pass through the connecting hole and cooperate with a second connecting hole preset in the turbine outer ring 101 to securely connect the turbine outer ring 101 to the metal casing 10211.

[0040] A plurality of displacement measurement holes 1022 are spaced apart on the outer wall of the metal casing 10211 . The displacement measurement holes 1022 are used to cooperate with preset marks on the turbine outer ring 101 to observe and measure the displacement deformation of the turbine outer ring 101 relative to the metal casing 10211 .

[0041] Here, the “connector 1024 ” refers to a component that connects the turbine outer ring 101 to the metal casing 10211 . In some embodiments, the connector 1024 is a connecting pin.

[0042] The "displacement measurement hole 1022" here can also be used by measuring instruments to directly measure the temperature and deformation of the turbine outer ring 101, so there is no need to set an identification on the turbine outer ring 101. At the same time, the temperature and deformation of the metal casing 10211 are measured by measuring instruments, which facilitates comparative analysis of the data of the metal casing 10211 and the turbine outer ring 101.

[0043] The turbine outer ring connection structure of the present application is a full-ring assembly structure, including a turbine outer ring assembly 10. The turbine outer ring assembly 10 includes a turbine outer ring 101 and a metal casing connection assembly 102. The metal casing 10211 of the metal casing connection assembly 102 can limit the installation of the turbine outer ring 101, and the turbine outer ring 101 and the metal casing 10211 are connected and assembled through a connector 1024 to facilitate subsequent thermal matching tests. At the same time, a plurality of displacement measurement holes 1022 are spaced apart on the outer wall of the metal casing 10211. The displacement deformation of the turbine outer ring 101 relative to the metal casing 10211 during the thermal matching test can be measured through the displacement measurement holes 1022 in conjunction with the preset marks on the turbine outer ring 101, which facilitates the analysis and judgment of the assembly effect. The turbine outer ring assembly 10 has a streamlined structure and can facilitate overall test verification.

[0044] Preferably, please refer to Figure 2 As shown, the turbine outer ring 101 is a full-ring structure made of ceramic-based composite materials.

[0045] It is understandable that in order to improve the performance of aircraft engines, the temperature of the gas before the turbine needs to be increased, which subjects the turbine outer ring to higher environmental tests. For this purpose, the turbine outer ring 101 is prepared by using ceramic-based composite materials, and the turbine outer ring 101 is designed as a full-ring structure. This can effectively improve the overall performance of the turbine outer ring 101 to cope with more stringent operating environments.

[0046] Preferably, please refer to Figure 2 As shown, a plurality of positioning bosses 1023 are arranged at intervals on the outer wall of the metal casing 10211 , and the positioning bosses 1023 are used to cooperate with an external device to limit the installation of the metal casing 10211 .

[0047] It can be understood that in order to achieve modular disassembly and assembly of the turbine outer ring assembly 10 as a whole, so as to improve the test efficiency of thermal matching of the turbine outer ring assembly 10, the positioning boss 1023 on the outer wall of the metal casing 10211 can be conveniently snap-fitted or limitedly installed with an external device. At the same time, the positioning boss 1023 can also play a role in limiting the position of the turbine outer ring assembly 10, ensuring that the turbine outer ring assembly 10 and the test device do not shift after assembly.

[0048] Preferably, please refer to Figure 2 As shown, multiple displacement measurement holes 1022 are arranged in segments along the circumference of the metal casing 10211 to measure the displacement deformation of each section of the turbine outer ring 101.

[0049] It can be understood that in order to more accurately analyze the performance of each section of the working surface of the turbine outer ring 101, the turbine outer ring 101 is subjected to a segmented test, and the displacement measurement holes 1022 at different positions can facilitate the measurement of the turbine outer ring 101 at different positions, effectively improving the convenience and efficiency of the measurement.

[0050] According to another aspect of the present application, a thermal matching test device is provided for performing a thermal matching test on the turbine outer ring connection structure to assess the connection matching effect between the turbine outer ring 101 and the metal casing 10211. The thermal matching test device includes a mounting platform 1, a mounting member 2, a stopper 3, a cooling tube 4, and a radiation lamp 5.

[0051] The mounting part 2 and the limiting part 3 are both arranged on the mounting platform 1. The mounting part 2 is a cylindrical structure with an open top, and the limiting part 3 is a cylindrical structure. The limiting part 3 is located inside the mounting part 2 and there is a partition cavity between the limiting part 3 and the mounting part 2. The limiting part 3 is used to support the limited turbine outer ring assembly 10. The radiation lamp tube 5 is arranged in the partition cavity, and the radiation lamp tube 5 is used to heat the turbine outer ring assembly 10; a cooling nozzle 6 is provided in the limiting part 3, and the cooling nozzle 6 is connected to the cooling pipe 4. The cooling pipe 4 is used to connect to an external cooling air source, and the cooling nozzle 6 is used to spray cooling airflow to cool the turbine outer ring assembly 10.

[0052] Here, the limit member 3 can be installed on the turbine outer ring assembly 10. In some embodiments, the limit member 3 is a cylindrical structure, which can uniformly conduct heat to the turbine outer ring assembly 10. In conjunction with the cooling nozzle 6, it can accelerate the cooling of the turbine outer ring assembly 10 and act as a cooling interlayer.

[0053] The thermal matching test device of the present application can realize the modular installation of the turbine outer ring assembly 10, and adopts radiation heating instead of conventional gas heating as the heat source for the CMC outer ring thermal matching test, which can realize directional heating of the working surface of the turbine outer ring assembly 10. During the test process, there is no need to frequently disassemble the turbine outer ring assembly 10, and the turbine outer ring assembly 10 can be subjected to heating-cooling load cycle alternating tests in sections, which greatly improves the efficiency of the test and improves the accuracy of assembly verification at the same time; the test device as a whole is very small and easy to use, and there is no safety hazard of traditional gas heating tests; the test device can complete the test with only electricity and a small amount of cooling air, and the test cost is low.

[0054] Preferably, please refer to Figure 1 As shown, the thermal matching test device also includes a lamp tube bracket supported in the partition cavity, the lamp tube bracket is used to support and fix the radiation lamp tube 5, there are multiple radiation lamp tubes 5, and the multiple radiation lamp tubes 5 are arranged in a circular array in the partition cavity, an annular mounting frame is provided in the limiting member 3, and there are multiple cooling nozzles 6, and the multiple cooling nozzles 6 are arranged in a circular array on the outer wall of the annular mounting frame.

[0055] As can be appreciated, the lamp holder facilitates the assembly and disassembly of the radiation lamps 5, allowing for flexible arrangement to accommodate varying numbers of lamps 5 under varying operating conditions. The compartment cavity provides ample operating space, facilitating manual assembly and disassembly, as well as adjustment of the test apparatus. Multiple cooling nozzles 6 can also be assembled and disassembled simultaneously via the mounting bracket, resulting in highly efficient operation. Compared to traditional, large-scale, high-temperature gas-fired heating test equipment, this system offers greater convenience and shorter commissioning time, significantly improving overall test efficiency and effectively reducing testing costs.

[0056] Preferably, please refer to Figure 1 As shown, a plurality of test measurement holes 7 are spaced apart on the side wall of the mounting member 2 , and the test measurement holes 7 are used for temperature measuring instruments to monitor the temperature of the turbine outer ring 101 and the metal casing 1021 .

[0057] It is understandable that in order to avoid the high temperature environment affecting the health of personnel, a relatively independent test environment can be achieved through the mounting part 2. In order to facilitate the measurement of the turbine outer ring 01 and the metal casing 1021, it is only necessary to open a plurality of test measurement holes 7 at intervals on the side wall of the mounting part 2 to provide infrared thermal imagers, thermocouples and other measuring instruments for convenient monitoring of the turbine outer ring 101 and the metal casing 1021. The operation is very safe and convenient.

[0058] Preferably, please refer to Figure 3 As shown, the side wall of the mounting member 2 is provided with a radiation-proof heat-insulating component, which is used to reduce the heat loss in the compartment cavity and isolate the radiation of the radiation lamp 5.

[0059] It is understood that the cylindrical mounting member 2 encloses a relatively independent test environment, and heating is provided by the radiation lamp 5, eliminating the need for high-temperature gas. Although this reduces sealing measures, to further improve safety during the test, reduce the impact of radiation, and centralize heat in the compartment cavity, accelerating temperature rise and improving test efficiency, a radiation-proof heat insulation assembly can be installed on the sidewall of the mounting member 2. In some embodiments, the radiation-proof heat insulation assembly includes a heat shield and / or a reflector.

[0060] According to another aspect of the present application, a test method using the above-mentioned thermal matching test device is also provided, comprising the following steps:

[0061] S100, the turbine outer ring assembly 10 is sleeved and limited on the outer wall of the limiter 3, and the temperature of the turbine outer ring 101 and the metal casing 1021 is monitored in real time by a temperature measuring instrument;

[0062] S200, turning on the radiation lamp 5 to heat the turbine outer ring assembly 10 to 800-1000° C.;

[0063] S300, turning on the cooling nozzle 6 to cool the turbine outer ring assembly 10 to room temperature, so as to achieve a complete thermal matching cycle;

[0064] S400, measuring the deformation data of the turbine outer ring 101 and the metal casing 1021, and determining whether the thermal matching test of the entire turbine outer ring assembly 10 is qualified. If qualified, proceeding to step S500;

[0065] S500. Perform a directional heating-cooling load cycle alternating test on the turbine outer ring assembly 10 in sections, divide the turbine outer ring assembly 10 into multiple sections along the circumferential direction, turn on the radiation lamp 5 corresponding to the first section of the turbine outer ring assembly 10 to heat the first section to 800-1000°C, stop heating, and turn on the cooling nozzle 6 corresponding to the first section of the turbine outer ring assembly 10 to cool the first section to room temperature, then measure the temperature and deformation data of the turbine outer ring 101 and the metal casing 1021 to complete the thermal matching cycle test of the first section of the turbine outer ring assembly 10; then, perform thermal matching cycle tests on the second section, the third section...the nth section of the turbine outer ring assembly 10 in sequence according to the thermal matching cycle test steps of the first section of the turbine outer ring assembly 10, until the thermal matching cycle of each section of the entire circle of the turbine outer ring assembly 10 is completed.

[0066] The test method for the thermal matching test device of this application also has the aforementioned beneficial effects. This application can conduct thermal matching tests on all existing ceramic turbine outer rings, requiring minimal space and equipment. The heating area can be controlled to achieve segmented, directional heating and cooling alternating tests, resulting in high test efficiency. This application can effectively replace such high-temperature gas test equipment, offering unique advantages in shortening test time and reducing test costs.

[0067] Preferably, in step S200, all radiation lamps 5 use the same preset power level. In step S500, the radiation lamps 5 at the tested section corresponding to the turbine outer ring assembly 10 use the preset power, while the other radiation lamps 5 reduce the power or are turned off.

[0068] It can be understood that in order to achieve controllable heating areas for the turbine outer ring assembly 10, avoid excessive temperature differences between areas that require heating and areas that do not require heating, and reduce the impact on the turbine outer ring 101, when conducting a segmented directional heating-cooling load cycle alternating test, it is only necessary to use the radiation lamp tubes 5 at the corresponding segments for normal power heating, and the other radiation lamp tubes 5 can reduce the power or be turned off. Since the radiation lamp tubes 5 heat the turbine outer ring 101 and the metal casing 10211 as a whole, the limiter 3 can also play a role in uniform heat conduction to the turbine outer ring assembly 10, which can accelerate the test process and improve the efficiency of the test.

[0069] It should be noted that, in this article, the terms "comprises", "includes" or any other variations thereof are intended to cover non-exclusive inclusion, so that a process, method, article or apparatus that includes a series of elements includes not only those elements, but also includes other elements not explicitly listed, or also includes elements that are inherent to such process, method, article or apparatus.

[0070] This article uses specific examples to illustrate the principles and implementation methods of this application. The above examples are only used to help understand the method and core ideas of this application. The above is only the preferred implementation method of this application. It should be pointed out that due to the limitations of textual expression, there are objectively infinite specific structures. For ordinary technicians in this technical field, without departing from the principles of this application, they can make several improvements, modifications or changes, and can also combine the above technical features in an appropriate manner; these improvements, modifications, changes or combinations, or the direct application of the inventive concept and technical solution to other occasions without improvement, should be regarded as protected by this application.

Claims

1. A turbine outer ring connection structure, characterized in that: The turbine outer ring assembly (10) includes: The turbine outer ring assembly (10) comprises a turbine outer ring (101) and a metal casing connecting assembly (102); the metal casing connecting assembly (102) comprises a metal casing (1021) and a connecting piece (1024); the metal casing (1021) is a full-ring structure and has a limiting groove provided on its inner ring; the limiting groove is used to limit the turbine outer ring (101); a first connecting hole is provided on the outer wall of the metal casing (1021); the connecting piece (1024) is used to pass through the connecting hole and cooperate with a second connecting hole preset on the turbine outer ring (101) to connect and fasten the turbine outer ring (101) and the metal casing (1021); A plurality of displacement measurement holes (1022) are provided at intervals on the outer wall of the metal casing (1021). The displacement measurement holes (1022) are used to cooperate with preset marks on the turbine outer ring (101) to observe and measure the displacement deformation of the turbine outer ring (101) relative to the metal casing (1021).

2. A turbine outer ring connection structure according to claim 1, characterized in that: The turbine outer ring (101) is a full-ring structure made of ceramic-based composite materials.

3. The turbine outer ring connection structure according to claim 1, characterized in that: A plurality of positioning bosses (1023) are arranged at intervals on the outer wall of the metal casing (1021), and the positioning bosses (1023) are used to cooperate with an external device to limit the installation of the metal casing (1021).

4. The turbine outer ring connection structure according to claim 1, characterized in that: A plurality of displacement measurement holes (1022) are arranged in a full circle and in sections along the circumference of the metal casing (1021) to measure the displacement deformation of each section of the turbine outer ring (101).

5. A thermal matching test device for performing a thermal matching test on the turbine outer ring connection structure according to any one of claims 1 to 4 to assess the connection matching effect between the turbine outer ring (101) and the metal casing (1021), characterized in that: The thermal matching test device comprises a mounting platform (1), a mounting member (2), a limiting member (3), a cooling tube (4) and a radiation lamp tube (5): The mounting member (2) and the limiting member (3) are both arranged on the mounting platform (1); the mounting member (2) is a cylindrical structure with an open top; the limiting member (3) is a cylindrical structure; the limiting member (3) is located inside the mounting member (2) and a spacer cavity is provided between the limiting member (3) and the mounting member (2); the limiting member (3) is used to support the limited turbine outer ring assembly (10); the radiation lamp tube (5) is provided in the spacer cavity; the radiation lamp tube (5) is used to heat the turbine outer ring assembly (10); a cooling nozzle (6) is provided inside the limiting member (3); the cooling nozzle (6) is connected to the cooling pipe (4); the cooling pipe (4) is used to connect to an external cooling air source; the cooling nozzle (6) is used to spray a cooling air flow to cool the turbine outer ring assembly (10).

6. A thermal matching test device according to claim 5, characterized in that: The thermal matching test device further comprises a lamp tube bracket supported in the spacer cavity, the lamp tube bracket being used to support and fix the radiation lamp tube (5), a plurality of radiation lamp tubes (5) being provided, and the plurality of radiation lamp tubes (5) being arranged in a circular array in the spacer cavity, a circular mounting frame being provided in the limiting member (3), a plurality of cooling nozzles (6) being provided, and the plurality of cooling nozzles (6) being arranged in a circular array on the outer wall of the circular mounting frame.

7. The thermal matching test device according to claim 5, characterized in that: A plurality of test measurement holes (7) are spaced apart on the side wall of the mounting member (2), and the test measurement holes (7) are used for a temperature measuring instrument to monitor the temperature of the turbine outer ring (101) and the metal casing (1021).

8. The thermal matching test device according to claim 5, characterized in that: The side wall of the mounting member (2) is provided with a radiation-proof heat-insulating component, which is used to reduce heat loss in the compartment cavity and isolate the radiation of the radiation lamp tube (5).

9. A thermal matching test method, characterized in that: Using the thermal matching test device according to any one of claims 5 to 8, the thermal matching test method includes the following steps: S100, sleeve the turbine outer ring assembly (10) on the outer wall of the limiting member (3) and monitor the temperature of the turbine outer ring (101) and the metal casing (1021) in real time using a temperature measuring instrument; S200, turning on the radiation lamp (5) to heat the turbine outer ring assembly (10) to 800-1000° C.; S300, turning on the cooling nozzle (6) to cool the turbine outer ring assembly (10) to room temperature, thereby achieving a complete thermal matching cycle; S400, measuring deformation data of the turbine outer ring (101) and the metal casing (1021), and judging whether the thermal matching test of the entire turbine outer ring assembly (10) is qualified, and if qualified, proceeding to step S500; S500, conduct a directional heating-cooling load cycle alternating test on the turbine outer ring assembly (10) in sections, divide the turbine outer ring assembly (10) into multiple sections along the circumferential direction, turn on the radiation lamp (5) corresponding to the first section of the turbine outer ring assembly (10) to heat the first section to 800-1000°C, stop heating, turn on the cooling nozzle (6) corresponding to the first section of the turbine outer ring assembly (10) to cool the first section to room temperature, then measure the temperature and deformation data of the turbine outer ring (101) and the metal casing (1021), and complete the thermal matching cycle test of the first section of the turbine outer ring assembly (10); then, according to the thermal matching cycle test steps of the first section of the turbine outer ring assembly (10), perform the thermal matching cycle test of the second section, the third section...the nth section of the turbine outer ring assembly (10) in sequence, until the thermal matching cycle of each section of the entire circle of the turbine outer ring assembly (10) is completed.

10. The thermal matching test method according to claim 9, characterized in that: In step S200, all radiation lamps (5) use the same preset power level. In step S500, the radiation lamps (5) at the test section corresponding to the turbine outer ring assembly (10) use the preset power, while the other radiation lamps (5) reduce the power or turn off.

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