High pressure compressor rotor dynamic stress test structure

Abstract

The application discloses a high-pressure compressor rotor dynamic stress test structure, comprising: a low-pressure compressor and a high-pressure compressor, an adapter device, a dynamic stress test device and an adapter shaft group. The adapter device is internally provided with a first annular cavity arranged in a ring direction, so as to smoothly introduce the outlet airflow of the low-pressure compressor into the inlet of the high-pressure compressor. The adapter device is also internally provided with a mounting inner cavity, the dynamic stress test device is mounted in the mounting inner cavity, the two ends of the adapter shaft group are connected with the rotor part of the dynamic stress test device and a hollow rotating shaft respectively, the test lead of the dynamic stress test device passes through the adapter shaft group and the high-pressure disc of the high-pressure compressor in sequence, and the strain gauge of the test lead is pasted to the blade of the high-pressure compressor. The adapter device is also provided with an air inlet channel and an air outlet channel, which are used for introducing cooling air into the mounting inner cavity and leading the test lead and internal functional pipelines outwards. The structure of the application has low requirements on the test platform, high accuracy of the test structure, small requirements on the size of the high-pressure compressor rotor and the dynamic stress test device, and high structural adaptability.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology with a dual-shaft gas generator, and in particular, to a dynamic stress testing structure for a high-pressure compressor rotor. Background Technology

[0002] Blade vibration is a technical challenge that must be addressed in the design and operation of aero-engines, especially for high-order vibrations. Due to the lack of corresponding design guidelines, high-cycle vibration fatigue failures frequently occur during engine design and operation. Dynamic stress testing of rotor blades is currently the most effective verification method for blade vibration stress analysis. Dynamic stress testing typically uses a telemetry system or slip ring actuator to transmit test signals from a high-speed rotating rotor to ground-based testing equipment. The telemetry system or slip ring actuator consists of a rotor and a stator. The rotor is connected to the engine rotor (or, due to structural characteristics, usually connected to the shaft end), and the stator is fixed to the engine casing.

[0003] For aero-engines with dual-shaft gas generators and dual-rotor structures, the design of dynamic stress testing schemes for the high-pressure rotor faces several technical bottlenecks, including limited modification space, difficulties in the layout of dynamic stress testing equipment systems, and challenges in extracting test signals, because the low-pressure rotor must pass through the shaft of the high-pressure rotor. Since it is impossible to install telemetry or slip ring electrical devices on the shaft end of the high-pressure rotor under full-engine conditions, dynamic stress testing of the high-pressure rotor is mainly carried out on the core engine. This involves simulating the working environment of the high-pressure rotor components in the engine by using high-temperature and high-pressure intake conditions to test the dynamic stress of the high-pressure rotor blades during operation.

[0004] In addition, patent CN 113565583 B discloses a dynamic stress testing device for the high-pressure turbine rotor of a dual-rotor turbofan engine. This device uses a telemetry system to perform dynamic stress testing on the high-pressure turbine rotor under full-engine conditions. The telemetry mounting base is located at the interstage disk center of the high-pressure compressor rotor assembly and connected to the high-pressure compressor rotor assembly, thus achieving the technical effect of performing dynamic stress testing on the high-pressure turbine rotor of a dual-rotor turbofan engine under full-engine conditions.

[0005] The disadvantages of the two existing technologies are as follows: For engines with dual rotor compressors, dynamic stress testing of the high-pressure compressor requires the design of a core engine platform. The high-temperature and high-pressure intake conditions require the test bench to have a large flow rate of high-temperature and high-pressure air supply capacity and precise control capability, which places high demands on the test bench. Moreover, the high-temperature and high-pressure intake conditions are artificially introduced through ideal analysis and differ from actual working conditions.

[0006] The technical solution disclosed in patent CN 113565583 B places the telemetry system at the center of the high-pressure compressor rotor disk, requiring the high-pressure compressor rotor disk to have a large space to accommodate the telemetry device, and placing certain requirements on the structural dimensions of the high-pressure compressor rotor and the telemetry device. Summary of the Invention

[0007] This invention provides a dynamic stress testing structure for a high-pressure compressor rotor to solve the technical problems of existing tests, such as high requirements for the test bench, differences from actual work, and certain requirements on the structural dimensions of the high-pressure compressor rotor and telemetry device.

[0008] The technical solution adopted in this invention is as follows: A dynamic stress testing structure for a high-pressure compressor rotor includes: a low-pressure compressor and a high-pressure compressor arranged sequentially and spaced apart along the engine axial direction; a transition device connecting the low-pressure compressor and the high-pressure compressor; a dynamic stress testing device for testing the dynamic stress of the high-pressure compressor rotor; and a transition shaft assembly serving as the transition. The transition device has a first annular cavity arranged circumferentially, with its axial ends connected to the main outlet of the low-pressure compressor and the main inlet of the high-pressure compressor, respectively, to smoothly introduce the outlet airflow of the low-pressure compressor into the inlet of the high-pressure compressor. The transition device also includes... The device has an internal mounting cavity in which the dynamic stress testing equipment is installed. The adapter shaft assembly is hollow and axially mounted inside the hollow rotating shaft of the high-pressure compressor. Both ends of the adapter shaft assembly are connected to the rotor part of the dynamic stress testing equipment and the hollow rotating shaft, respectively. The test leads of the dynamic stress testing equipment pass through the adapter shaft assembly and the high-pressure wheel of the high-pressure compressor in sequence, and the strain gauges connected to its ends are attached to the blades of the high-pressure compressor. The adapter device is also equipped with an air intake channel and an exhaust channel. The air intake channel is used to introduce cooling air into the mounting cavity, and the exhaust channel is used to lead the test leads and internal functional pipelines outward.

[0009] Furthermore, the adapter includes an inner and outer casing that are coaxially fitted together and radially spaced apart, and multiple connecting support plates connected between the inner and outer casings; the axial ends of the outer casing are respectively sealed to the low-pressure compressor outer casing and the high-pressure compressor outer casing, and the multiple connecting support plates are arranged sequentially and spaced apart along the circumference of the inner casing to connect and fix the inner casing and the outer casing, and the annular channel between the inner casing and the outer casing forms a first annular cavity.

[0010] Furthermore, multiple connecting support plates are arranged sequentially at intervals along the circumference, and each connecting support plate is hollow and airfoil-shaped. The number and angular position of the multiple connecting support plates are arranged in a one-to-one correspondence with the support plates inside the front end of the high-pressure compressor.

[0011] Furthermore, the adapter also includes an inner casing coaxially disposed within the middle casing, and a mounting bracket; both the middle casing and the inner casing are transversely arranged in a "U" shape, and their openings face the high-pressure compressor, forming an mounting cavity with the inner cavity of the inner casing; the mounting bracket is disposed at the open ends of the middle casing and the inner casing, and the mounting bracket is fixed to the inner casing of the high-pressure compressor, with the inner casing axially confined between the closed end of the middle casing and the mounting bracket.

[0012] Furthermore, the bottom ends of the two connecting support plates pass through the middle casing and extend to the outer wall surface near the inner casing, so that the inner channels of the two connecting support plates form the first air intake channel. The upper ends of the two connecting support plates also extend out of the outer casing and are respectively connected to the first air intake nozzles, which are connected to the first air intake channel. The inner casing wall surface is provided with a first through hole corresponding to the two connecting support plates to connect to the corresponding first air intake channel. The first through hole is also connected to the mounting cavity.

[0013] Furthermore, the two connecting support plates with the first air intake channel are arranged circumferentially opposite each other, so that one of the first air intake channels forms an inlet channel for introducing external cooling air into the installation cavity, and the other first air intake channel forms an outlet channel for drawing gas out of the installation cavity; the wall surface of the first air intake nozzle that connects to the inlet channel is also provided with multiple outlets that penetrate the wall surface, and the outlets are used for test leads and internal functional pipelines to be drawn out respectively.

[0014] Furthermore, the middle casing and the inner casing are radially spaced apart to form a second annular cavity arranged in a circumferential direction between them; the bottom ends of the two connecting support plates are fixedly connected to the middle casing, so that the inner channels of the two connecting support plates form a second air intake channel, and the upper ends of the two connecting support plates extend out of the outer casing and are respectively connected to the second air intake nozzles, which are connected to the second air intake channel; the wall surface of the middle casing is provided with a second through hole corresponding to the two connecting support plates to connect to the corresponding second air intake channel, and the second through hole is also connected to the second annular cavity; Furthermore, the outer circle of the mounting bracket is inserted into the middle casing through the open end of the middle casing, and a first sealing element is provided between the outer circle of the mounting bracket and the inner wall surface of the middle casing to prevent the first annular cavity from communicating with the second annular cavity; the inner circle of the mounting bracket is inserted into the inner casing through the open end of the inner casing, and a third sealing element is provided between the outer circle of the mounting bracket and the outer wall surface of the inner casing to prevent the mounting inner cavity from communicating with the second annular cavity; a third annular cavity is also formed between the adapter shaft assembly, the front end of the high-pressure compressor and the mounting bracket, and a plurality of third through holes are provided on the mounting bracket at intervals along the circumference, the third through holes being used to communicate with the third annular cavity and the mounting inner cavity.

[0015] Furthermore, the adapter shaft assembly includes a lead shaft and a lead tube arranged sequentially along the axial direction, both of which are hollow. The lead tube is installed axially inside the hollow rotating shaft of the high-pressure compressor, and the front end of the lead tube is connected to the front end of the hollow rotating shaft as a whole. The outer wall of the rear end of the lead tube is sealed to the disk center of the high-pressure wheel through a second sealing element. The front end of the lead shaft is connected to the rotor part of the dynamic stress testing equipment, and the rear end of the lead shaft is connected to the front end of the lead tube. After the test lead passes through the lead shaft and the lead tube, it runs close to the wall of the high-pressure wheel and passes through the high-pressure wheel, so that the strain gauge at its end is attached to the blade of the high-pressure compressor.

[0016] Furthermore, the inner hole of the lead tube is connected to the lead shaft end with a polygonal cross-section; each of the outer circles at both ends of the lead shaft is provided with a multi-faceted head that mates with the multi-faceted head, and the longitudinal section of each multi-faceted head along the axial direction is a drum-shaped arc surface that is low at both ends and convex in the middle; the front end of the lead shaft extends into the inner hole of the rotor part of the dynamic stress testing equipment for connection, and the rear end of the lead shaft is inserted into the multi-faceted hole of the lead tube along the axial direction.

[0017] The present invention has the following beneficial effects: This invention proposes a dynamic stress testing structure for a high-pressure compressor rotor. Compared to existing core engine tests, which involve only a high-pressure compressor, combustion chamber, and high-pressure turbine but lack a low-pressure compressor, core engine tests require a high-temperature, high-pressure intake platform. This places high demands on the platform, and the artificially introduced intake air differs from actual operating conditions, leading to inaccurate test results. In contrast, the test structure in this application uses a dual-rotor compressor. The testing system mainly includes a low-pressure compressor, a transfer device, a high-pressure compressor, and a transfer shaft assembly. This test component is driven by power at both ends, avoiding the need for separate high- and low-pressure rotor shaft structures. This provides installation conditions for the transfer device, dynamic stress testing equipment, and transfer shaft assembly. Furthermore, the inclusion of a low-pressure compressor allows it to provide high-pressure air during operation. The compressor provides high-temperature, high-pressure air, thus reducing the requirements for the test platform. Furthermore, by controlling the operating speeds of the high-pressure and low-pressure compressors, the operation of the low-pressure and high-pressure compressors along the engine's common operating line can be replicated, resulting in a high accuracy of the test structure, similar to actual operation. In this application's structure, the slip ring actuator or telemetry device of the dynamic stress testing equipment is placed within the adapter. The dynamic stress testing equipment includes a rotor and a stator. The rotor of the dynamic stress testing equipment is connected to the hollow shaft of the high-pressure compressor via an adapter shaft assembly, and the stator is mounted on the adapter. During the test, by controlling the speeds of the high-pressure and low-pressure compressors, the test piece can run along the engine's common operating line, thereby realistically simulating the operating state of the engine's high-pressure compressor and improving test accuracy. Compared to the technical solution disclosed in existing patent CN 113565583 B, this application's structure has fewer requirements for the high-pressure compressor rotor size and the dynamic stress testing equipment, exhibiting high structural adaptability.

[0018] In addition to the objectives, features, and advantages described above, the present invention has other objectives, features, and advantages. The invention will now be described in further detail with reference to the figures. Attached Figure Description

[0019] The accompanying drawings, which form part of this application, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings: Figure 1 This is a schematic diagram of the dynamic stress test structure for a high-pressure compressor rotor according to a preferred embodiment of the present invention; Figure 2 yes Figure 1 A magnified schematic diagram of the central part of the structure; Figure 3 yes Figure 1 Schematic diagram of internal cavity venting installation; Figure 4 yes Figure 1 Schematic diagram of air evacuation in the second annular cavity; Figure 5 This is a cross-sectional front view schematic diagram of the first air intake nozzle; Figure 6 This is a schematic diagram of the cross-sectional main view of the lead shaft; Figure 7 yes Figure 6 A schematic diagram of the right-side structure.

[0020] Legend: 1. Low-pressure compressor; 2. High-pressure compressor; 21. Hollow shaft; 22. High-pressure impeller; 23. High-pressure compressor blades; 3. Adapter; 301. First annular cavity; 302. Mounting inner cavity; 303. First air intake channel; 304. First through hole; 305. Second annular cavity; 306. Second air intake channel; 307. Second through hole; 308. Third annular cavity; 309. Third through hole; 31. Outer casing; 32. Middle casing; 33. Inner casing; 34. Connecting support plate; 35. First air intake nozzle; 351. Outlet; 36. Mounting support; 37. Second air intake nozzle; 38. First seal; 39. Third seal 4. Dynamic stress testing equipment; 41. Test leads; 42. Strain gauges; 5. Adapter shaft assembly; 51. Lead wire shaft; 511. Multi-faceted head; 52. Lead wire tube; 53. Second seal. Detailed Implementation

[0021] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below. Examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention.

[0022] Those skilled in the art will understand that, unless specifically stated otherwise, the term "comprising" as used in this specification means the presence of the stated features, integers, steps, operations, components, and / or components, but does not exclude the presence or addition of one or more other features, integers, steps, operations, components, and / or combinations thereof. It should be understood that when we say a component is "connected" to another component, it can be directly connected to the other component or connected via an intermediate component. The term "and / or" as used herein includes all or any unit and all combinations of one or more associated listed items. The terms "first" and "second," etc., in this specification and claims are used to distinguish different objects, not to describe a particular order.

[0023] Reference Figure 1 and Figure 2 A preferred embodiment of the present invention provides a dynamic stress testing structure for a high-pressure compressor rotor, comprising: a low-pressure compressor 1 and a high-pressure compressor 2 arranged sequentially at intervals along the engine axial direction; a transition device 3 connecting the low-pressure compressor 1 and the high-pressure compressor 2; a dynamic stress testing device 4 for performing dynamic stress testing on the rotor of the high-pressure compressor 2; and a transition shaft assembly 5 serving as the transition. The transition device 3 has a first annular cavity 301 arranged circumferentially. The two axial ends of the first annular cavity 301 are respectively connected to the main flow outlet of the low-pressure compressor 1 and the main flow inlet of the high-pressure compressor 2, so as to smoothly introduce the outlet airflow of the low-pressure compressor 1 into the inlet of the high-pressure compressor 2. The adapter 3 also includes an installation cavity 302, in which the dynamic stress testing equipment 4 is installed. The adapter shaft assembly 5 is hollow and axially mounted within the hollow rotating shaft 21 of the high-pressure compressor 2. Both ends of the adapter shaft assembly 5 are connected to the rotor portion of the dynamic stress testing equipment 4 and the hollow rotating shaft 21, respectively. The test lead 41 of the dynamic stress testing equipment 4 passes sequentially through the adapter shaft assembly 5 and the high-pressure rotor 22 of the high-pressure compressor 2, and its end is connected to a strain gauge 42 which is bonded to the high-pressure compressor blade 23. The adapter 3 also includes an air intake channel and an exhaust channel. The air intake channel is used to introduce cooling air into the installation cavity 302, and the exhaust channel is used to lead the test lead 41 and internal functional pipelines outwards.

[0024] This invention proposes a dynamic stress testing structure for a high-pressure compressor rotor. Compared to existing core engine tests, which involve only a high-pressure compressor, combustion chamber, and high-pressure turbine, omitting a low-pressure compressor, core engine tests require a high-temperature, high-pressure intake platform. This places high demands on the platform, and the artificially introduced intake differs from actual operating conditions, leading to inaccurate test results. In contrast, the test structure in this application uses a dual-rotor compressor. The testing system mainly includes a low-pressure compressor 1, a transfer device 3, a high-pressure compressor 2, and a transfer shaft assembly 5. This test component is driven by power at both ends, avoiding the need for separate high- and low-pressure rotor shaft structures. This provides installation conditions for the transfer device 3, dynamic stress testing equipment 4, and transfer shaft assembly 5. Furthermore, the low-pressure compressor 1 provides power to the high-pressure compressor 2 during operation. The system provides high-temperature and high-pressure gas supply, thus reducing the requirements for the test platform. Furthermore, by controlling the operating speeds of the high-pressure and low-pressure compressors, it can reproduce the operation of the low-pressure and high-pressure compressors along the common working line of the engine, thus mimicking actual operation and ensuring high accuracy of the test structure. In this application's structure, the slip ring actuator or telemetry device of the dynamic stress testing equipment 4 is placed within the adapter 3. The dynamic stress testing equipment 4 includes a rotor and a stator. The rotor of the dynamic stress testing equipment 4 is connected to the hollow shaft 21 of the high-pressure compressor 2 via the adapter shaft assembly 5. The stator is mounted on the adapter 3. During the test, by controlling the speeds of the high-pressure compressor 2 and the low-pressure compressor 1, the test piece can run along the common working line of the engine, thereby realistically simulating the operating state of the high-pressure compressor 2 and improving test accuracy. Compared to the technical solution disclosed in the existing patent CN 113565583 B, this application's structure has fewer requirements for the high-pressure compressor rotor size and the dynamic stress testing equipment, resulting in high structural adaptability.

[0025] Optionally, such as Figure 1 and Figure 2 As shown, the adapter 3 includes an inner casing 32 and an outer casing 31, which are coaxially fitted together and radially spaced, and multiple connecting support plates 34 connecting the inner casing 32 and the outer casing 31. The axial ends of the outer casing 31 are respectively sealed to the low-pressure compressor outer casing and the high-pressure compressor outer casing. The multiple connecting support plates 34 are sequentially spaced along the circumference of the inner casing 32 to connect and fix the inner casing 32 and the outer casing 31, and the annular channel between the inner casing 32 and the outer casing 31 forms a first annular cavity 301. In this optional embodiment, the outer casing 31 and the inner casing 32 are welded together by several connecting support plates 34, resulting in high overall support strength and structural stability.

[0026] Preferably, multiple connecting support plates 34 are arranged sequentially at intervals along the circumference, and each connecting support plate 34 is hollow and airfoil-shaped. The number and angular position of the multiple connecting support plates 34 correspond one-to-one with the support plates inside the front end of the high-pressure compressor 2. This structural arrangement of multiple connecting support plates 34 can reduce the impact of the total pressure loss of the airflow from the transfer device 3 on the performance of the dual-rotor compressor test piece, while avoiding the introduction of new excitation sources that could affect the dynamic stress test results of the high-pressure rotor.

[0027] Optionally, such as Figure 1 and Figure 2 As shown, the adapter 3 also includes an inner casing 33 coaxially disposed within the middle casing 32, and a mounting bracket 36. Both the middle casing 32 and the inner casing 33 are laterally arranged in a "U" shape, with their openings facing the high-pressure compressor 2, and the inner cavity of the inner casing 33 forming a mounting cavity 302. The mounting bracket 36 is disposed at the open ends of the middle casing 32 and the inner casing 33, and is fixed to the inner casing of the high-pressure compressor. The inner casing 33 is axially confined between the closed end of the middle casing 32 and the mounting bracket 36, and the dynamic stress testing equipment 4 is fixed on the mounting bracket 36.

[0028] Preferably, such as Figure 3 As shown, the bottom ends of two connecting support plates 34 pass through the middle casing 32 and extend to the outer wall near the inner casing 33, so that the inner channels of the two connecting support plates 34 form a first air intake channel 303. The upper ends of the two connecting support plates 34 also extend out of the outer casing 31 and are respectively connected to the first air intake nozzle 35, which communicates with the first air intake channel 303. The inner casing 33 has a first through hole 304 on its wall corresponding to the two connecting support plates 34, connecting to the corresponding first air intake channel 303. The first through hole 304 also communicates with the mounting cavity 302. In actual operation, the low-pressure outlet airflow temperature of the low-pressure compressor 1 is relatively high, usually above 200℃, while the operating temperature of the dynamic stress testing equipment 4 is required to not exceed 80℃. Therefore, the mounting cavity 302 needs to be cooled by air intake. In this preferred embodiment, the first air intake nozzle 35 is connected to the external cold air flow path, and the first air intake nozzle 35, the first air intake channel 303, and the first through hole 304 are connected in sequence to introduce external cooling air into the mounting cavity 302.

[0029] Furthermore, such as Figure 3 As shown, two connecting support plates 34 with first air intake channels 303 are arranged circumferentially opposite each other, so that one of the first air intake channels 303 forms an inlet channel for introducing external cooling air into the mounting cavity 302, and the other first air intake channel 303 forms an outlet channel for drawing gas out of the mounting cavity 302. The inlet and outlet channels conduct air convection heat exchange, thereby enhancing the cooling effect on the mounting cavity 302. Figure 5As shown, the wall surface of the first air inlet 35, which connects to the inlet channel, is also provided with multiple outlets 351 that penetrate the wall surface. The outlets 351 are used for the test leads 41 and internal functional pipelines to be led outwards respectively. At the same time, the outlets 351 are sealed with sealant, so that the introduced cooling air can simultaneously cool the internal functional pipelines of the dynamic stress testing equipment 4 (which are required to be in a normal temperature environment), reducing the impact of the high temperature mainstream in the first annular cavity 301 on the internal functional pipelines.

[0030] Optionally, such as Figure 2 and Figure 4 As shown, the middle casing 32 and the inner casing 33 are radially spaced to form a second annular cavity 305 circumferentially arranged between them. The bottom ends of two connecting support plates 34 are fixedly connected to the middle casing 32, forming a second air intake channel 306 within their inner passages. The upper ends of these two connecting support plates 34 extend beyond the outer casing 31 and are respectively connected to second air intake nozzles 37, which communicate with the second air intake channel 306. The wall surface of the middle casing 32 has second through holes 307 corresponding to the two connecting support plates 34, each penetrating the wall surface to connect to the corresponding second air intake channel 306. These second through holes 307 also communicate with the second annular cavity 305. In actual operation, the low-pressure outlet airflow temperature of the low-pressure compressor 1 is relatively high, typically exceeding 200℃, while the operating temperature of the dynamic stress testing equipment 4 is required to not exceed 80℃. Therefore, the mounting cavity 302 needs to be insulated and cooled. Thus, in the structure of this application, the second air intake nozzle 37 is connected to the external cold air flow path. The second air intake nozzle 37, the second air intake channel 306, and the second through hole 307 are connected in sequence to introduce external cooling air into the second annular cavity 305, thereby isolating the high-temperature environment of the first annular cavity 301 from the mounting cavity 302, so as to further enhance the cooling effect of the mounting cavity 302.

[0031] Preferably, such as Figure 2As shown, the outer circle of the mounting bracket 36 is inserted into the middle casing 32 through the open end of the middle casing 32. A first sealing element 38 is also provided between the outer circle of the mounting bracket 36 and the inner wall of the middle casing 32 to prevent the first annular cavity 301 from communicating with the second annular cavity 305, thereby preventing the high temperature and high pressure mainstream of the first annular cavity 301 from entering the internal area of ​​the middle casing 32. The inner circle of the mounting bracket 36 is inserted into the inner casing 33 through the open end of the inner casing 33. A third sealing element 39 is also provided between the inner circle of the mounting bracket 36 and the outer wall of the inner casing 33 to prevent the mounting inner cavity 302 from communicating with the second annular cavity 305, thereby isolating the mounting inner cavity 302 from the second annular cavity 305. A third annular cavity 308 is formed circumferentially between the front end of the adapter shaft assembly 5, the high-pressure compressor 2, and the mounting support 36. The mounting support 36 is also provided with multiple third through holes 309 spaced circumferentially. These through holes 309 connect the third annular cavity 308 and the mounting inner cavity 302, allowing cooling air from the mounting inner cavity to enter the third annular cavity 308 and cool the slip ring rotor interface end. The support plate is hollow, and an air duct interface is provided in the corresponding outer casing area. Air duct nozzles are installed on the air duct interface. There are at least two air duct channels connecting to the second annular cavity 305, used for air intake and exhaust respectively, forming convective heat exchange. By filling the second annular cavity 305 with cooling air, the high-temperature environment of the first annular cavity 301 and the mounting inner cavity 302 are isolated.

[0032] Optionally, such as Figure 2As shown, the adapter shaft assembly 5 includes a lead shaft 51 and a lead tube 52 arranged sequentially along the axial direction, both of which are hollow. The lead tube 52 is installed axially inside the hollow rotating shaft 21 of the high-pressure compressor 2, and the front end of the lead tube 52 is connected to the front end of the hollow rotating shaft 21 as a whole. The outer wall of the rear end of the lead tube 52 is sealed to the center of the high-pressure wheel 22 through a second sealing element 53. The front end of the lead shaft 51 is connected to the rotor part of the dynamic stress testing device 4, and the rear end of the lead shaft 51 is connected to the front end of the lead tube 52. The test lead 41 passes through the lead shaft 51 and the lead tube 52, runs close to the wall of the high-pressure wheel 22, and passes through the high-pressure wheel 22, so that the strain gauge 42 at its end is attached to the high-pressure compressor blade 23. In actual design, the high-temperature strain gauge 42 is installed on the high-pressure compressor blade 23. The test lead 41 connects the strain gauge 42 and the main body of the dynamic stress testing device 4. The test lead 41 is led along the wall of the high-pressure wheel 22 to the hollow rotating shaft 21, and then through the lead tube 52 and the lead shaft 51 to the dynamic stress testing device 4. The inside of the lead tube 52 needs to be sealed with high-temperature resistant sealant to prevent the high-temperature gas in the compressor disk cavity from flowing into the dynamic stress testing device 4 through the lead tube 52, which would damage the dynamic stress testing device 4. The front end of the lead tube 52 is provided with sufficient interference fit with the hollow rotating shaft 21 to ensure that the lead tube 52 rotates with the rotor or an anti-rotation groove is provided at the shaft end. The lead tube 52 is provided with a boss, and the two work together to prevent rotation. The rear end of the lead tube 52 is provided with a rubber ring sealing installation groove to install the second sealing element 53 to cooperate with the disk core for sealing.

[0033] Preferably, such as Figure 6 and Figure 7 As shown, the inner hole of the lead tube 52 is a polygonal hole with a polygonal cross-section. Each end of the lead shaft 51 has a polygonal head 511 on its outer circumference that mates with the polygonal hole. Each polygonal head 511 has a drum-shaped arc surface with low ends and a convex middle section along the axial direction. The front end of the lead shaft 51 extends into the inner hole of the rotor portion of the dynamic stress testing device 4 for connection, and the rear end of the lead shaft 51 is inserted axially into the polygonal hole of the lead tube 52. During operation, the drum-shaped arc surface contacts the inner wall of the polygonal hole in the lead tube 52. This connection method allows for a certain axial eccentricity between the lead shaft 51 and the high-pressure compressor rotor and the dynamic stress testing device rotor. A certain amount of axial movement exists between the lead shaft 51 and the lead tube 52 and the dynamic stress testing device rotor to meet the axial movement requirements of the high-pressure compressor rotor during operation.

[0034] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A dynamic stress testing structure for a high-pressure compressor rotor, characterized in that, include: A low-pressure compressor (1) and a high-pressure compressor (2) are arranged sequentially and alternately along the engine axis, a transfer device (3) connecting the low-pressure compressor (1) and the high-pressure compressor (2), a dynamic stress testing device (4) for performing dynamic stress testing on the rotor of the high-pressure compressor (2), and a transfer shaft assembly (5) that serves as a transfer. The adapter (3) is provided with a first annular cavity (301) arranged in a ring direction. The two axial ends of the first annular cavity (301) are respectively connected to the main outlet of the low-pressure compressor (1) and the main inlet of the high-pressure compressor (2) so as to smoothly introduce the outlet airflow of the low-pressure compressor (1) into the inlet of the high-pressure compressor (2). The adapter (3) is also provided with an installation cavity (302), and the dynamic stress testing equipment (4) is installed in the installation cavity (302). The adapter shaft assembly (5) is hollow and installed axially in the hollow rotating shaft (21) of the high-pressure compressor (2). The two ends of the adapter shaft assembly (5) are respectively connected to the rotor part of the dynamic stress testing equipment (4) and the hollow rotating shaft (21). The test lead (41) of the dynamic stress testing equipment (4) passes through the adapter shaft assembly (5) and the high-pressure wheel (22) of the high-pressure compressor (2) in sequence, and the strain gauge (42) connected to its end is pasted to the high-pressure compressor blade (23). The adapter (3) is also provided with an air intake channel and an exhaust channel. The air intake channel is used to introduce cooling air into the installation cavity (302), and the exhaust channel is used to lead the test lead (41) and internal functional pipelines outward.

2. The high-pressure compressor rotor dynamic stress testing structure according to claim 1, characterized in that, The adapter (3) includes an inner casing (32) and an outer casing (31) that are coaxially fitted together and radially spaced apart, and multiple connecting support plates (34) connecting the inner casing (32) and the outer casing (31). The outer casing (31) is sealed at both ends of the axial direction to the low-pressure compressor outer casing and the high-pressure compressor outer casing, respectively. Multiple connecting support plates (34) are arranged sequentially and at intervals along the circumference of the middle casing (32) to connect and fix the middle casing (32) and the outer casing (31), and the annular channel between the middle casing (32) and the outer casing (31) forms the first annular cavity (301).

3. The high-pressure compressor rotor dynamic stress testing structure according to claim 2, characterized in that, Multiple connecting support plates (34) are arranged sequentially and spaced apart along the circumference. Each connecting support plate (34) is hollow and airfoil-shaped. The number and angular position of the multiple connecting support plates (34) are distributed in a one-to-one correspondence with the support plates in the front end of the high-pressure compressor (2).

4. The high-pressure compressor rotor dynamic stress testing structure according to claim 2, characterized in that, The adapter (3) also includes an inner casing (33) coaxially disposed within the middle casing (32), and a mounting bracket (36). The middle casing (32) and the inner casing (33) are both arranged in a horizontal "U" shape, and their openings face the high-pressure compressor (2), and the inner cavity of the inner casing (33) forms the mounting cavity (302). The mounting bracket (36) is arranged at the open ends of the middle casing (32) and the inner casing (33), and the mounting bracket (36) is fixed to the inner casing of the high-pressure compressor. The inner casing (33) is axially limited between the closed end of the middle casing (32) and the mounting bracket (36).

5. The high-pressure compressor rotor dynamic stress testing structure according to claim 4, characterized in that, The bottom ends of two connecting support plates (34) pass through the middle casing (32) and extend to the outer wall near the inner casing (33), so that the inner channel of the two connecting support plates (34) forms the first air intake channel (303). The upper ends of the two connecting support plates (34) also extend out of the outer casing (31) and are respectively connected to the first air intake nozzle (35). The first air intake nozzle (35) is connected to the first air intake channel (303). The inner casing (33) has a first through hole (304) on the wall surface corresponding to the two connecting support plates (34) to connect the corresponding first air intake channel (303). The first through hole (304) also connects to the mounting cavity (302).

6. The high-pressure compressor rotor dynamic stress testing structure according to claim 5, characterized in that, Two connecting support plates (34) with a first air intake channel (303) are arranged circumferentially opposite each other, so that one of the first air intake channels (303) forms an inlet channel for introducing external cooling air into the mounting cavity (302), and the other first air intake channel (303) forms an outlet channel for drawing gas out of the mounting cavity (302); The first air inlet (35) connecting the inlet channel is also provided with multiple outlets (351) that penetrate the wall. The outlets (351) are used for the test leads (41) and internal functional pipelines to be led outward respectively.

7. The high-pressure compressor rotor dynamic stress testing structure according to claim 4, characterized in that, The middle casing (32) and the inner casing (33) are radially spaced apart to form a second annular cavity (305) arranged in a ring between them. The bottom ends of two connecting support plates (34) are fixedly connected to the middle casing (32) so that the inner channels of the two connecting support plates (34) form a second air intake channel (306). The upper ends of the two connecting support plates (34) also extend out of the outer casing (31) and are respectively connected to the second air intake nozzle (37). The second air intake nozzle (37) is connected to the second air intake channel (306). The wall of the middle casing (32) is provided with a second through hole (307) at each of the two connecting support plates (34) to connect the corresponding second air intake channel (306). The second through hole (307) also connects to the second annular cavity (305).

8. The high-pressure compressor rotor dynamic stress testing structure according to claim 7, characterized in that, The outer circle of the mounting bracket (36) is inserted into the middle casing (32) through the opening end of the middle casing (32), and a first sealing element (38) is provided between the outer circle of the mounting bracket (36) and the inner wall surface of the middle casing (32) to prevent the first annular cavity (301) from communicating with the second annular cavity (305); the inner circle of the mounting bracket (36) is inserted into the inner casing (33) through the opening end of the inner casing (33), and a third sealing element (39) is provided between the outer circle of the mounting bracket (36) and the outer wall surface of the inner casing (33) to prevent the mounting inner cavity (302) from communicating with the second annular cavity (305); The front end of the adapter shaft assembly (5), the high-pressure compressor (2) and the mounting support (36) also form a third annular cavity (308) arranged in a circumferential direction. The mounting support (36) is also provided with a plurality of third through holes (309) arranged in a circumferential direction at intervals. The third through holes (309) are used to connect the third annular cavity (308) and the mounting inner cavity (302).

9. The dynamic stress testing structure for a high-pressure compressor rotor according to claim 4, characterized in that, The adapter shaft assembly (5) includes a lead shaft (51) and a lead tube (52) arranged sequentially along the axial direction, and both the lead shaft (51) and the lead tube (52) are hollow. The lead tube (52) is installed axially inside the hollow rotating shaft (21) of the high-pressure compressor (2), and the front end of the lead tube (52) is connected to the front end of the hollow rotating shaft (21) as a whole. The outer wall of the rear end of the lead tube (52) is sealed to the disc core of the high-pressure wheel (22) through the second sealing element (53). The front end of the lead shaft (51) is connected to the rotor part of the dynamic stress testing equipment (4), and the rear end of the lead shaft (51) is connected to the front end of the lead tube (52). The test lead (41) passes through the lead shaft (51) and the lead tube (52) and then runs close to the wall of the high-pressure wheel (22). After passing through the high-pressure wheel (22), the strain gauge (42) at its end is attached to the high-pressure compressor blade (23).

10. The dynamic stress testing structure for a high-pressure compressor rotor according to claim 9, characterized in that, The inner hole of the lead tube (52) is connected to the end of the lead shaft (51) which has a polygonal cross-section. The outer circles at both ends of the lead shaft (51) are provided with multi-faceted heads (511) that mate with multi-faceted holes, and the longitudinal section of each multi-faceted head (511) along the axial direction is a drum-shaped arc surface that is low at both ends and convex in the middle. The front end of the lead shaft (51) is inserted into the inner hole of the rotor part of the dynamic stress testing device (4) and connected. The rear end of the lead shaft (51) is inserted into the polygonal hole of the lead tube (52) along the axial direction.

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