Turbine outer ring connecting structure and thermal matching test device and test method thereof

Abstract

The invention discloses a turbine outer ring connecting structure and a thermal matching test device and method thereof, and belongs to the technical field of aero-engine tests.The turbine outer ring connecting structure comprises a turbine outer ring assembly, and the turbine outer ring assembly comprises a turbine outer ring and a metal casing connecting assembly; the metal casing connecting assembly comprises a metal casing and a connecting piece, a first connecting hole is formed in the outer wall of the metal casing, and the connecting piece is used for connecting and fastening the turbine outer ring and the metal casing; a plurality of displacement measuring holes are formed in the outer wall of the metal casing at intervals, and the displacement measuring holes are used for being matched with preset marks on the turbine outer ring so as to observe and measure the displacement deformation quantity of the turbine outer ring relative to the metal casing. The turbine outer ring is an integral CMC turbine outer ring, the turbine outer ring connecting structure is an integral ring type assembly structure, modular installation can be achieved, and the thermal matching test device can achieve a thermal fatigue test of heating-cooling load circulation alternation of the CMC outer ring.

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] At present, one of the important ways to improve the performance of aircraft engines is to increase the gas temperature before the turbine. However, the increase in gas temperature poses a severe challenge to the hot end parts of the turbine made of metal materials, especially the outer ring of the turbine, which is subjected to the test of harsh environment. In order to solve the problem of high-temperature service of the outer ring, ceramic matrix composite (CMC) materials are currently used to prepare the outer ring. In order to support the engineering application of new materials, it is necessary to verify whether the ceramic outer ring support structure has 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, many tests have already been conducted at home and abroad to verify the stability and perfection of the existing structure. 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] After investigation, we found that under the existing technical conditions, the thermal matching test of the outer ring is basically carried out by high-temperature gas heating. However, it is well known that high-temperature gas requires large-scale gas supply equipment, combustion chambers, aviation kerosene, cooling media, large test benches, automatic control equipment and other test equipment. The preparation time for the test process is long and the debugging time is long. Moreover, due to the presence of high-temperature gas in the test process, the cooling protection of the pipeline, the cooling and sealing of the test piece, and the emergency safety device all need to be taken into consideration. These force the test equipment to be impossible to miniaturize, which will eventually lead to high test costs. In other words, the high-temperature impact zone formed on the test piece under the impact of gas is relatively large, which will pose certain difficulties for the deformation measurement of the thermal matching test of the small-sized outer ring connection structure, and the measurement equipment also needs to avoid the influence of high temperature. Therefore, it is necessary to design a new test plan to verify the reliability and deformation coordination of the connection structure between the CMC outer ring and metal parts under high-temperature service conditions, so as to support the engineering application of the CMC turbine outer ring.

[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 the present application, and therefore may include information that does not constitute the prior art known to ordinary technicians in the 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 a thermal matching test device and test method thereof, which are a solution designed for component-level assessment of an integral CMC outer ring, 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 realize modular installation, and 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, including a turbine outer ring assembly:

[0010] The turbine outer ring assembly includes a turbine outer ring and a metal casing connection component, the metal casing connection component includes a metal casing and a connection 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, a first connection hole is provided on the outer wall of the metal casing, and the connection piece is used to pass through the connection hole and cooperate with a second connection hole preset on the turbine outer ring to connect and fasten the turbine outer ring and the metal casing;

[0011] The outer wall of the metal casing is provided with a plurality of displacement measuring holes at intervals, and the displacement measuring holes are used to cooperate with preset marks on the turbine outer ring to observe and measure the displacement deformation of the turbine outer ring 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 opening at the top, and 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 and limit the turbine outer ring assembly. The radiation lamp tube is arranged in the partition cavity, and the radiation lamp tube is used to heat the turbine outer ring assembly. A cooling nozzle is arranged in the limiting part, and the cooling nozzle is connected to the cooling pipe. The cooling pipe is used to connect to an external cooling air source, and 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 arranged 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 a temperature measuring instrument 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 limiter, and monitor the temperature of the turbine outer ring and the metal casing in real time by 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, opening 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, and judging whether the thermal matching test of the whole ring of the turbine outer ring assembly is qualified, if qualified, proceeding 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 tube corresponding to the first section of the turbine outer ring assembly to heat the first section to 800-1000°C, stop 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, and 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, in step S200, all radiation lamps use the same preset power level. 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, and 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 a connector 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, so as to facilitate the analysis and judgment of the assembly effect. The structure of the turbine outer ring assembly is streamlined, which can facilitate overall test verification.

[0029] The thermal matching test device of the present application can realize 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 as a whole and easy to use, and there are no safety hazards of traditional tests using gas heating. The test device can complete the test using only electricity and a small amount of cooling air, and the test cost is low.

[0030] The test method of the thermal matching test device of the present application also has the above-mentioned beneficial effects. The present application can carry out thermal matching test assessments on all existing ceramic material turbine outer rings, and it occupies less space, requires less test equipment, and the heating area is controllable to achieve segmented directional heating-cooling alternating tests, with high test efficiency. The present application can effectively replace such high-temperature gas test equipment, and has 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 the advantages described above at the same time. In addition to the purposes, features and advantages described above, this application also has other purposes, features and advantages. The following will further describe this application in detail with reference to the figures. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] The drawings constituting a part of the present application are used to provide a further understanding of the present application. The illustrative embodiments and descriptions of the present application are used to explain the present application and do not constitute an improper limitation on the present application. In the drawings:

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

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

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

[0036] Legend: 10. Turbine outer ring assembly; 101. Turbine outer ring; 102. Metal casing connection component; 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 in conjunction with 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 connection assembly 102. The metal casing connection assembly 102 includes a metal casing 10211 and a connection piece 1024. The metal casing 10211 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 101. A first connection hole is provided on the outer wall of the metal casing 10211. The connection piece 1024 is used to pass through the connection hole and cooperate with a second connection hole preset on the turbine outer ring 101 to connect and fasten the turbine outer ring 101 and the metal casing 10211.

[0040] The outer wall of the metal casing 10211 is provided with a plurality of displacement measuring holes 1022 at intervals. The displacement measuring 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 the measuring instrument 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 can be measured by the measuring instrument, 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, so as 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, and 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, so as to facilitate the analysis and judgment of the assembly effect. The turbine outer ring assembly 10 has a streamlined structure, which 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 outer ring of the turbine to higher environmental tests. For this reason, the outer ring 101 of the turbine is prepared by ceramic-based composite materials, and the outer ring 101 of the turbine is designed as a full-ring structure, which can effectively improve the overall performance of the outer ring 101 of the turbine to cope with more severe 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 limit the position of the turbine outer ring assembly 10, ensuring that the turbine outer ring assembly 10 and the test device are not offset after assembly.

[0048] Preferably, please refer to Figure 2 As shown, a plurality of displacement measuring holes 1022 are arranged in segments along the circumference of the metal casing 10211 in a full circle to measure the displacement deformation of each segment 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 above-mentioned 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 tube 5:

[0051] 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, and the limiting member 3 is a cylindrical structure. The limiting member 3 is located inside the mounting member 2 and there is a partition cavity 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 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 member 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 a 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 evenly 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 serve as a cooling interlayer.

[0053] The thermal matching test device of the present application can realize 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 is very small as a whole and easy to use, and there is no safety hazard 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.

[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, the multiple radiation lamp tubes 5 are arranged in a circular array in the partition cavity, an annular mounting frame is arranged in the limiting member 3, there are multiple cooling nozzles 6, the multiple cooling nozzles 6 are arranged in a circular array on the outer wall of the annular mounting frame.

[0055] It is understandable that the lamp holder can facilitate the disassembly and assembly and flexible arrangement of the radiation lamp 5, so as to adapt to the installation of different numbers of radiation lamps 5 under different working conditions, and the partition cavity has a certain operating space, which can facilitate manual disassembly and assembly and arrangement adjustment of the test device; at the same time, multiple cooling nozzles 6 can also be disassembled and assembled at one time through the mounting frame, and the operation is very efficient. Compared with traditional large-scale high-temperature gas heating test equipment, it has higher convenience and shorter debugging time, which can greatly improve the efficiency of the test as a whole and effectively reduce the test cost.

[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 a temperature measuring instrument 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, so that measuring instruments such as infrared thermal imagers and thermocouples can be used to conveniently monitor 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 tube 5 .

[0059] It can be understood that a relatively independent test environment is formed by enclosing the cylindrical mounting member 2, and heating is performed by the radiation lamp tube 5 without using high-temperature gas. Although the sealing measures can be reduced, in order to further improve the safety during the test, reduce the impact of radiation, and form concentrated heat in the compartment cavity, accelerate the temperature rise, and improve the efficiency of the test, a radiation-proof heat insulation component can be set on the side wall of the mounting member 2. In some embodiments, the radiation-proof heat insulation component includes a heat insulation board 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, sleeve the turbine outer ring assembly 10 on the outer wall of the stopper 3, and monitor the temperature of the turbine outer ring 101 and the metal casing 1021 in real time by using a temperature measuring instrument;

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

[0063] S300, opening 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 judging whether the thermal matching test of the whole ring of the turbine outer ring assembly 10 is qualified, if qualified, proceeding to step S500;

[0065] 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 tube 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, conduct thermal matching cycle tests on 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.

[0066] The test method of the thermal matching test device of the present application also has the above-mentioned beneficial effects. The present application can carry out thermal matching test assessments on all existing ceramic material turbine outer rings, and it occupies less space, requires less test equipment, and the heating area is controllable to achieve segmented directional heating-cooling alternating tests, with high test efficiency. The present application can effectively replace such high-temperature gas test equipment, and has 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, and 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 area for the turbine outer ring assembly 10, avoid excessive temperature difference between the area that needs to be heated and the area that does not need to be heated, 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 tube 5 at the corresponding segment for normal power heating, and other radiation lamp tubes 5 can reduce the power or be turned off. Since the radiation lamp tube 5 heats the turbine outer ring 101 and the metal casing 10211 as a whole, the limit member 3 can also have the effect of uniform heat conduction on the turbine outer ring assembly 10, which can accelerate the progress of the test 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 other elements not explicitly listed, or also includes elements 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 its 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 and the objective existence of infinite specific structures, ordinary technicians in this technical field can make several improvements, modifications or changes without departing from the principles of this application, 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 the protection of 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 connection assembly (102); the metal casing connection assembly (102) comprises a metal casing (1021) and a connection piece (1024); the metal casing (1021) is a full-ring structure and has a limiting groove on its inner ring, the limiting groove is used to limit the turbine outer ring (101); a first connection hole is provided on the outer wall of the metal casing (1021); the connection piece (1024) is used to pass through the connection hole and cooperate with a second connection 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), and 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 amount 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. A turbine outer ring connection structure according to claim 1, characterized in that: The outer wall of the metal casing (1021) is provided with a plurality of positioning bosses (1023) at intervals, and the positioning bosses (1023) are used to cooperate with an external device to limit the installation of the metal casing (1021).

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

5. A thermal matching test device, used for performing a thermal matching test on the turbine outer ring connection structure according to any one of claims 1 to 4, so as to evaluate 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 stop 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 opening at the top; the limiting member (3) is a cylindrical structure; the limiting member (3) is located inside the mounting member (2) and a spacing cavity is provided between the limiting member (3) and the mounting member (2); the limiting member (3) is used to support a limiting turbine outer ring assembly (10); a radiation lamp tube (5) is provided in the spacing 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 a cooling pipe (4); the cooling pipe (4) is used to connect 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 also includes a lamp tube support supported in the spacer cavity, the lamp tube support is used to support and fix the radiation lamp tube (5), a plurality of radiation lamp tubes (5) are provided, and the plurality of radiation lamp tubes (5) are arranged in a circular array in the spacer cavity, an annular mounting frame is arranged in the limiting member (3), a plurality of cooling nozzles (6) are provided, and the plurality of cooling nozzles (6) are arranged in a circular array on the outer wall of the annular mounting frame.

7. A 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. A 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 the 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 as described in 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 stopper (3) and monitor the temperature of the turbine outer ring (101) and the metal casing (1021) in real time by using a temperature measuring instrument; S200, turning on the radiation lamp tube (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, so as to achieve a complete thermal matching cycle; S400, measuring 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; S500, performing a directional heating-cooling load cycle alternating test on the turbine outer ring assembly (10) in sections, dividing the turbine outer ring assembly (10) into multiple sections along the circumferential direction, turning on the radiation lamp tube (5) corresponding to the first section of the turbine outer ring assembly (10) to heat the first section to 800-1000° C., stopping the heating, turning 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, and then measuring the temperature and deformation data of the turbine outer ring (101) and the metal casing (1021), completing the thermal matching cycle test of the first section of the turbine outer ring assembly (10); then, performing the thermal matching cycle test of 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.

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

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