Engine high pressure turbine casing containment test structure

Abstract

The application belongs to the field of aero-engine design and is a high-pressure turbine casing containment test structure for an engine, which comprises a first tester upper cover, a high-pressure turbine casing, a first adapter shaft, a test rotor and a transmission mechanism; the casing protection mechanism comprises a casing adapter plate and a simulated split casing; the transmission mechanism comprises a driving shaft assembly and the first adapter shaft; the high-pressure turbine casing is fixed to the first tester upper cover through the casing adapter plate and the simulated split casing, a larger cavity structure can be formed inside, so that the high-pressure turbine rotor test capability and the containment test capability can be simultaneously possessed. The measure realizes the capability of carrying out the high-pressure turbine casing containment test and solves the technical problem of starting from nothing; through the setting of the simulated split casing, the two parts of the simulated split casing can be separately installed, have the characteristics of simple and flexible installation, can be installed after the high-pressure turbine casing is installed, and can provide a relatively free rising space for the high-pressure turbine casing.

Description

Technical Field

[0001] This application belongs to the field of aero-engine design, and specifically relates to a test structure for a high-pressure turbine casing of an engine. Background Technology

[0002] The high-pressure turbine rotor is the component of an aero-engine operating under the most severe conditions, requiring it to withstand harsh environments of high temperature, high pressure, and high speed. Over time, the high-pressure turbine blades are prone to centrifugal breakage at high speeds. If the broken blades are not contained within the casing, high-energy debris may penetrate the casing, causing severe engine damage and even resulting in a fatal crash. Therefore, it is essential to study high-pressure turbine casing containment tests before obtaining engine airworthiness certification.

[0003] Currently, containment tests have not been conducted on high-pressure turbine rotors. Research mainly focuses on high-pressure turbine rotor over-spin, fracture, and low-cycle fatigue tests, all of which are performed on rotor testing equipment. Existing rotor testing structures include... Figure 1 As shown, it includes a second tester cover 26, a rotor tester drive shaft 27, a drive shaft sleeve 28, a drive shaft pin 29, a drive shaft flange 30, a second adapter shaft 31, and a high-pressure turbine test piece 32. During rotor testing, the rotor tester drive shaft 27 drives the drive shaft flange 30, the drive shaft flange 30 drives the second adapter shaft 31, and the second adapter shaft 31 drives the high-pressure turbine test piece 32 to rotate. The drive shaft sleeve 28 and the drive shaft pin 29 serve to secure the rotor tester drive shaft 27 to the drive shaft flange 30.

[0004] In other rotor strength component tests, when the casing fixing issue is involved, it is necessary to drill many threaded holes on the test fixture and use bolts to fix the casing through adapters. The current state of damage morphology of the threaded holes on the test fixture cover is as follows. Figure 2 As shown.

[0005] The main drawbacks of existing technical solutions are as follows:

[0006] 1. Technical aspects

[0007] Existing high-pressure turbine rotor test structures can be used for over-speed, fracture, damage tolerance, and low-cycle fatigue tests. However, casing containment tests have not yet been conducted on high-pressure turbine rotors, and the rotor test equipment lacks the capability to install a high-pressure turbine casing for containment tests. While casings are not required for over-speed, fracture, damage tolerance, and low-cycle fatigue tests, they are necessary for containment tests.

[0008] Because the drive shaft of the rotor tester is a long flexible shaft, the high-pressure turbine rotor under the tester will generate radial displacement during the start-up stage due to the influence of rotor dynamics. When the gap between the blade and the casing is less than the radial displacement, the turbine blade will scrape against the casing, causing damage to the test rotor.

[0009] Due to the limitations of existing rotor testers, the high-pressure turbine rotor needs a certain upward and slewing distance in the axial length of the tester during installation. After the casing is installed, the blades are prone to hitting the casing during the rotor's upward phase, causing friction and damaging the blades or casing structure. Often, it is necessary to remove the parts inside the casing, thereby increasing the axial installation space distance, which may result in the blades not being contained by the casing.

[0010] 2. Cost aspect

[0011] Under the existing high-pressure turbine rotor test structure, if a containment test is conducted and a turbine blade breaks off, it will cause a very large unbalanced force. Under this force, the rotor shaft system, damper, and gearbox will be severely damaged, and the drive shaft may even break, causing the high-pressure turbine rotor to fall. This will cause huge economic losses not only to the test equipment but also to the aero-engine rotor. Repairing the test equipment after the damage also requires a large investment of funds.

[0012] In addition, the numerous threaded holes used to secure the casing also caused serious damage to the tester's top cover.

[0013] 3. Efficiency

[0014] Existing technologies have limited space for the assembly of adapter shafts and high-pressure turbine disks, such as... Figure 3 As shown, its fixing pin 33 is difficult to install, which brings great difficulties to the assembly and affects the assembly efficiency.

[0015] The existing high-pressure turbine test rotor balancing structure only includes the high-pressure turbine test piece 32 and the second adapter shaft 31. Balancing requires the assistance of an auxiliary functional shaft 34, and balancing is achieved through fulcrums ① and ②. Figure 4 As shown, the drive shaft assembly is not balanced during this process, and the balance state of the drive shaft assembly is unknown. It is impossible to achieve integrated balance of the high-pressure turbine rotor shaft system. After the high-pressure turbine rotor is installed, it is necessary to start the engine to check the balance state of the rotor. If the rotor vibration is too large during the trial run, it is necessary to stop the engine and remove it from the platform for rebalancing, which affects the test efficiency.

[0016] Therefore, improving the efficiency of testing the high-pressure turbine casing of the engine, reducing costs, and minimizing friction between the high-pressure turbine rotor and the casing are problems that need to be solved. Summary of the Invention

[0017] The purpose of this application is to provide a test structure for the containment of a high-pressure turbine casing in an engine, in order to solve the problems of easy rubbing between the high-pressure turbine rotor and the casing in the prior art, as well as low test efficiency and high cost.

[0018] The technical solution of this application is: a test structure for a high-pressure turbine casing of an engine, including a first tester cover, a high-pressure turbine casing, a first adapter shaft, a test rotor, and a transmission mechanism; a casing protection structure is connected between the first test rotor cover and the high-pressure turbine casing; the transmission mechanism is connected between the middle of the first tester cover and the first adapter shaft and is used to drive the first adapter shaft to rotate; the transmission mechanism is located inside the casing protection structure; and the test rotor is connected to the first adapter shaft.

[0019] The casing protection mechanism includes a casing adapter plate and a simulated split casing. The casing adapter plate is detachably connected to the top cover of the first tester. There are two sets of simulated split casings, which are arranged in opposite directions. The top of the simulated split casing is bolted to the casing adapter plate, and the bottom is bolted to the high-pressure turbine casing. A protective cavity is formed between the casing adapter plate, the simulated split casing, the high-pressure turbine casing, and the test rotor. The transmission mechanism and the first adapter shaft are both located inside the protective cavity.

[0020] The transmission mechanism includes a drive shaft assembly and a first adapter shaft. Both the drive shaft assembly and the first adapter shaft are coaxially arranged with the high-pressure turbine casing. The upper end of the drive shaft assembly is rotatably connected to the upper cover of the first tester, and the lower end is detachably connected to the test shaft assembly. The test shaft and the test rotor are connected by bolts.

[0021] Preferably, a conical protective cylinder is coaxially provided on the outside of the drive shaft assembly. The diameter of the conical protective cylinder gradually decreases from top to bottom. The upper end of the conical protective cylinder is connected to the casing adapter plate by a first bolt, and there is a 1mm gap between the lower end and the drive shaft sleeve on the drive shaft assembly.

[0022] Preferably, the drive shaft assembly is connected to the first adapter shaft by a second bolt, and the outer side of the conical protective cylinder is provided with a protective seat and a protective plate; the upper end of the protective seat is connected to the casing adapter plate by a third bolt, and the lower end is connected to the protective plate by a fourth bolt, and the inner side of the protective plate is connected to the first adapter shaft by a second bolt.

[0023] Preferably, the upper end of the conical protective cylinder has six limiting grooves evenly spaced along its circumferential edge; there are six sets of protective seats, and the six sets of protective seats are respectively located in the six limiting grooves to form an open annular structure; the protective plate is a split structure.

[0024] Preferably, the casing adapter plate is coaxially provided with an inner ring boss and an outer ring boss. The inner ring boss is connected to the conical protective cylinder and the protective seat, and the outer ring boss is connected to the simulated split casing. The axial length of the outer ring boss is greater than the axial length of the inner ring boss. Both ends of the simulated split casing are provided with flanges. The simulated split casing is threadedly connected to the casing adapter plate and the high-pressure turbine casing respectively by tightening self-locking nuts on the flanges.

[0025] Preferably, the top cover of the first tester has four screw holes along the circumference, and each of the four screw holes is provided with a fixing bolt connected to the casing adapter plate. The fixing bolt has a stepped structure and the diameter of the step gradually decreases from the head to the end of the fixing bolt. A fixing nut is threaded onto the end of the fixing bolt. A fifth bolt is also connected between the casing adapter plate and the top cover of the first tester at the position corresponding to the inner side of the fixing bolt.

[0026] Preferably, a first flange and a second flange are coaxially disposed on the first adapter shaft. The first flange is bolted to the drive shaft assembly, and the second flange is connected to the test rotor by a pin. The maximum radius of the first flange is less than the straight-line distance from the axis of the second flange to the innermost edge of the pin hole on the second flange. There is a gap between the first flange and the second flange.

[0027] Preferably, the first adapter shaft is provided with two balance points: a first balance point and a second balance point. The first balance point is located in the middle of the drive shaft sleeve of the drive shaft assembly, and the second balance point is located on the first adapter shaft at the end away from the test rotor.

[0028] This application discloses a test structure for the containment of a high-pressure turbine casing, comprising a first test chamber cover, a high-pressure turbine casing, a first adapter shaft, a test rotor, and a transmission mechanism. The casing protection mechanism includes a casing adapter plate and a simulated split casing. The transmission mechanism includes a drive shaft assembly and the first adapter shaft. The high-pressure turbine casing is fixed to the first test chamber cover via the casing adapter plate and the simulated split casing, forming a large cavity structure internally, thus enabling simultaneous high-pressure turbine rotor testing and containment testing. This measure achieves the capability to conduct high-pressure turbine casing containment tests, solving the technical problem of starting from scratch. By setting up a simulated split casing, the two parts of the simulated split casing can be installed separately, featuring simple and flexible installation. It can be installed after the high-pressure turbine casing is installed, providing relatively free upward space for the high-pressure turbine casing. Attached Figure Description

[0029] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0030] Figure 1 This is a schematic diagram of the rotor test structure in the background art;

[0031] Figure 2 This is a schematic diagram illustrating the current state of damage to the threaded holes on the upper cover of the testing instrument in the background art.

[0032] Figure 3 This is a schematic diagram of the assembly structure of the adapter shaft and high-pressure turbine disk in the background art.

[0033] Figure 4 This is a schematic diagram of the balancing structure of a high-pressure turbine test rotor in the background technology;

[0034] Figure 5 This is a schematic diagram of the overall structure of this application;

[0035] Figure 6 This is a top view of the conical protective cylinder of this application;

[0036] Figure 7 This is a schematic diagram of the casing adapter plate structure of this application;

[0037] Figure 8 This is a schematic diagram simulating the cross-sectional structure of the split-type casing in this application;

[0038] Figure 9 This is a schematic cross-sectional view of the protective base of this application;

[0039] Figure 10 This is a schematic diagram of the protective plate structure of this application;

[0040] Figure 11 This is a schematic cross-sectional view of the first adapter shaft of this application;

[0041] Figure 12 This is a schematic diagram of the experimental rotor balancing structure of this application.

[0042] 1. Fixing bolt; 2. Fifth bolt; 3. Third bolt; 4. Conical protective cylinder; 5. First tester cover; 6. Casing adapter plate; 7. Simulated split casing; 8. First bolt; 9. High-pressure turbine casing; 10. Fourth bolt; 11. Test rotor; 12. Drive shaft assembly; 13. First adapter shaft; 14. Second bolt; 15. Protective plate; 16. Protective seat; 17. Sixth bolt; 18. Fixing nut; 19. Limiting groove; 20. Inner ring boss; 21. Outer ring boss; 22. First flange; 23. Second flange; 24. First balance support point; 25. Second balance support point; 26. Second tester cover; 27. Rotor tester drive shaft; 28. Drive shaft sleeve; 29. ​​Drive shaft pin; 30. Drive shaft flange; 31. Second adapter shaft; 32. High-pressure turbine test piece; 33. Fixing pin; 34. Auxiliary function shaft. Detailed Implementation

[0043] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings.

[0044] A test structure for containing a high-pressure turbine casing of an engine, such as Figure 5 As shown, it includes a first tester cover 5, a high-pressure turbine casing 9, a first adapter shaft 13, a test rotor 11, and a transmission mechanism; a casing protection structure is connected between the first test rotor 11 cover and the high-pressure turbine casing 9, the transmission mechanism is connected between the middle of the first tester cover 5 and the first adapter shaft 13 and the transmission mechanism is used to drive the first adapter shaft 13 to rotate, the transmission mechanism is located inside the casing protection mechanism, and the test rotor 11 is connected to the first adapter shaft 13.

[0045] The casing protection mechanism includes a casing adapter plate 6 and a simulated split casing 7. The casing adapter plate 6 is detachably connected to the top cover 5 of the first tester. There are two sets of simulated split casings 7, which are set in opposite directions. The top of the simulated split casing 7 is bolted to the casing adapter plate 6, and the bottom is connected to the high-pressure turbine casing 9 through the sixth bolt 17. A protective cavity is formed between the casing adapter plate 6, the simulated split casing 7, the high-pressure turbine casing 9 and the test rotor 11. The transmission mechanism and the first adapter shaft 13 are both located in the protective cavity.

[0046] The transmission mechanism includes a drive shaft assembly 12 and a first adapter shaft 13. Both the drive shaft assembly 12 and the first adapter shaft 13 are coaxially arranged with the high-pressure turbine casing 9. The upper end of the drive shaft assembly 12 is rotatably connected to the upper cover 5 of the first tester, and the lower end is connected to the test shaft assembly by a pin. The test shaft and the test rotor 11 are connected by bolts.

[0047] Due to the limitations of existing rotor testers, the high-pressure turbine rotor needs a certain upward and slewing distance in the axial length of the tester during installation. After the casing is installed, the blades are prone to hitting the casing during the rotor's upward phase, causing friction and damaging the blades or casing structure. Often, it is necessary to remove the parts inside the casing, thereby increasing the axial installation space distance, which may result in the blades not being contained by the casing.

[0048] The high-pressure turbine casing 9 of this application is fixed to the upper cover 5 of the first test apparatus via the casing adapter plate 6 and the simulated split casing 7, forming a large cavity structure inside, thus enabling both high-pressure turbine rotor testing and containment testing capabilities. This measure realizes the capability to conduct containment testing of the high-pressure turbine casing 9, solving the technical problem of achieving this from scratch.

[0049] By setting up a simulated split-type casing 7, the two simulated split-type casings 7 can be installed separately, which has the characteristics of simple and flexible installation. It can be installed after the high-pressure turbine casing 9 is installed, which can provide relatively free upward space for the high-pressure turbine casing 9. This space facilitates the upward movement of the high-pressure turbine casing 9 without colliding with it, thus avoiding damage to the test rotor 11.

[0050] The drive shaft assembly 12 includes a rotor tester drive shaft 27, a drive shaft sleeve 28, a drive shaft pin 29, and a drive shaft flange 30, etc., and is assembled according to the existing connection structure, which will not be described in detail here.

[0051] Combination Figure 6 Preferably, a conical protective cylinder 4 is coaxially provided on the outside of the drive shaft assembly 12. The diameter of the conical protective cylinder 4 gradually decreases from top to bottom. The upper end of the conical protective cylinder 4 is connected to the casing adapter plate 6 by the first bolt 8, and there is a 1mm gap between the lower end and the drive shaft sleeve 28 on the drive shaft assembly 12.

[0052] The conical protective sleeve 4 can limit the radial displacement of the high-pressure turbine rotor during the start-up phase. When the high-pressure turbine rotor starts up, if the drive shaft sleeve 28 abuts against the conical protective sleeve, it cannot move further outward under the limit of the conical protective sleeve. In this way, the radial displacement of the test rotor 11 is also limited, thereby effectively preventing the test rotor 11 from rubbing against the high-pressure turbine casing 9 and ensuring that the test rotor 11 is not damaged.

[0053] Combination Figure 7-8 Preferably, the casing adapter plate 6 is coaxially provided with an inner ring boss 20 and an outer ring boss 21. The inner ring boss 20 is connected to the conical protective cylinder 4 and the protective seat 16, and the outer ring boss 21 is connected to the simulated split casing 7. The axial length of the outer ring boss 21 is greater than the axial length of the inner ring boss 20. Both ends of the simulated split casing 7 are provided with flanges. The simulated split casing 7 is threadedly connected to the casing adapter plate 6 and the high-pressure turbine casing 9 by tightening self-locking nuts on the flanges. The inner ring boss 20 and the outer ring boss 21 provided on the casing adapter plate 6 position and limit the conical protective cylinder 4, the protective seat 16 and the simulated split casing 7, effectively ensuring the installation position requirements of the high-pressure turbine casing 9. By providing flanges at both ends of the simulated split casing 7 and fixing the two split semi-cylindrical wall structures with 16 self-locking nuts, support is provided for the stable installation of the high-pressure turbine casing 9.

[0054] Combination Figure 9-10Preferably, the drive shaft assembly 12 is connected to the first adapter shaft 13 by a second bolt 14, and the outer side of the conical protective cylinder 4 is provided with a protective seat 16 and a protective plate 15; the upper end of the protective seat 16 is connected to the casing adapter plate 6 by a third bolt 3, and the lower end is connected to the protective plate 15 by a fourth bolt 10, and the inner side of the protective plate 15 is connected to the first adapter shaft 13 by six second bolts 14.

[0055] In the prior art, when the blades on the test rotor 11 break off, the instantaneous huge unbalanced force will cause the wheel to fly out and fall, causing serious damage to the test rotor 11. However, this application, by setting the protective seat 16 and the protective plate 15, can work with the casing adapter plate 6 and the simulated split casing 7 to prevent the test rotor 11 from flying out and falling when subjected to huge impact force.

[0056] Preferably, the upper end of the conical protective cylinder 4 has six evenly spaced limiting grooves 19 along its circumferential edge, such as... Figure 6 There are six sets of protective seats 16, each set located within a limiting groove 19, forming an open annular structure. The protective plate 15 has a split structure. By opening the limiting grooves 19 on the conical protective cylinder 4, the installation position of the protective seat 16 can be reserved, ensuring that the protective seat 16 can be stably assembled onto the casing adapter plate 6, while effectively saving cost and space. The split structure of the protective plate 15 effectively improves the flexibility of assembly and reduces the difficulty of assembly.

[0057] Preferably, the first tester cover 5 has four screw holes along its circumference. Each of the four screw holes contains a fixing bolt 1 that connects to the casing adapter plate 6. The fixing bolt 1 has a stepped structure, and the diameter of the steps gradually decreases from the head to the end. A fixing nut 18 is threaded onto the end of the fixing bolt 1. A fifth bolt 2 is also connected between the casing adapter plate 6 and the first tester cover 5 at the position corresponding to the inner side of the fixing bolt 1. The casing adapter plate 6 is initially installed and positioned by the fifth bolt 2. Then, the fixing bolt 1 passes through the first tester cover 5 and connects to the casing adapter plate 6, unifying the installation interface of the casing adapter plate 6, preventing damage to the tester cover from numerous threaded holes on the first tester cover 5, and reducing the testing cost.

[0058] Combination Figure 11Preferably, a first flange 22 and a second flange 23 are coaxially arranged on the first adapter shaft 13. The first flange 22 is bolted to the drive shaft assembly 12, and the second flange 23 is connected to the test rotor 11 by a pin. The maximum radius of the first flange 22 is less than the straight-line distance from the axis of the second flange 23 to the innermost edge of the pin hole on the second flange 23. There is a gap between the first flange 22 and the second flange 23. By setting the first flange 22 and the second flange 23, the distance between the test rotor 11 and the drive shaft assembly 12 is increased, and there is a larger space above the test rotor 11 to ensure that the test rotor 11 will not collide with other structures during the test. At the same time, sufficient space is provided for the installation of the pin, which shortens the assembly efficiency and improves the test efficiency.

[0059] Preferably, two balancing points are provided on the first adapter shaft 13: a first balancing point 24 and a second balancing point 25. The first balancing point 24 is located in the middle of the drive shaft sleeve 28 of the drive shaft assembly 12, and the second balancing point 25 is located at the end of the first adapter shaft 13 away from the test rotor 11. By optimizing the arrangement of the first adapter shaft 13 and the drive shaft assembly 12, the circumferential radius of the drive shaft flange 30 is reduced to facilitate the assembly of the first adapter shaft 13. At the same time, the auxiliary function shaft 34 does not need to be assembled. The high-pressure turbine rotor is integrated and balanced through the two balancing points, which reduces the initial imbalance of the rotor shaft system. After balancing, the rotor can be directly installed on the rotor tester, avoiding repeated disassembly and assembly, reducing the risk of blades rubbing against the casing, protecting the test rotor 11 and improving test efficiency.

[0060] During the assembly of the containment test structure, the test rotor 11 is first connected to the first adapter shaft 13 with pins, and then the first adapter shaft 13 is connected to the drive shaft assembly 12 with bolts, thus forming the high-pressure turbine test rotor 11. Next, the casing adapter plate 6 is installed on the first tester cover 5 and secured with four No. 1 bolts and four No. 2 bolts. Then, the conical protective cylinder 4 is installed and secured to the casing adapter plate 6 with the first bolt 8. The high-pressure turbine casing 9 is then connected to the casing adapter plate 6, and the test rotor 11 is installed on the tester. Finally, the conical protective cylinder 4 is installed onto the casing adapter plate 6 with the first bolt 8.

[0061] Connect the high-pressure turbine casing 9 to the casing adapter plate 6, and then install the test rotor 11 onto the test apparatus. Next, slowly lower the high-pressure turbine casing 9 to a distance of 1 cm axially from the test rotor 11, taking care not to touch the test rotor 11 during installation. After the high-pressure turbine casing 9 is installed, install six protective seats 16 evenly distributed around the circumference on the casing adapter plate 6; then install the protective plate 15 and secure it with bolts. Finally, install the simulated split casing 7 between the casing adapter plate 6 and the high-pressure turbine casing 9, completing the installation of the entire test setup.

[0062] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. An engine high pressure turbine casing containment test structure, characterised in that: It includes a first tester cover (5), a high-pressure turbine casing (9), a first adapter shaft (13), a test rotor (11), and a transmission mechanism; the test rotor (11) and the high-pressure turbine casing (9) are connected by a casing protection structure, the transmission mechanism is connected between the middle of the first tester cover (5) and the first adapter shaft (13) and the transmission mechanism is used to drive the first adapter shaft (13) to rotate, the transmission mechanism is located inside the casing protection mechanism, and the test rotor (11) is connected to the first adapter shaft (13); The casing protection mechanism includes a casing adapter plate (6) and a simulated split casing (7). The casing adapter plate (6) is detachably connected to the top cover (5) of the first tester. There are two sets of simulated split casings (7) that are split open. The top of the simulated split casing (7) is bolted to the casing adapter plate (6), and the bottom is bolted to the high-pressure turbine casing (9). A protective cavity is formed between the casing adapter plate (6), the simulated split casing (7), the high-pressure turbine casing (9), and the test rotor (11). The transmission mechanism and the first adapter shaft (13) are both located in the protective cavity. The transmission mechanism includes a drive shaft assembly (12) and a first adapter shaft (13). Both the drive shaft assembly (12) and the first adapter shaft (13) are coaxially arranged with the high-pressure turbine casing (9). The upper end of the drive shaft assembly (12) is rotatably connected to the upper cover (5) of the first tester, and the lower end is detachably connected to the test shaft assembly. The test shaft and the test rotor (11) are connected by bolts. A conical protective cylinder (4) is coaxially provided on the outside of the drive shaft assembly (12). The diameter of the conical protective cylinder (4) gradually decreases from top to bottom. The upper end of the conical protective cylinder (4) is connected to the casing adapter plate (6) by the first bolt (8), and there is a 1mm gap between the lower end and the drive shaft sleeve (28) on the drive shaft assembly (12). The drive shaft assembly (12) is connected to the first adapter shaft (13) by a second bolt (14). The outer side of the conical protective cylinder (4) is provided with a protective seat (16) and a protective plate (15). The upper end of the protective seat (16) is connected to the casing adapter plate (6) by a third bolt (3), and the lower end is connected to the protective plate (15) by a fourth bolt (10). The inner side of the protective plate (15) is connected to the first adapter shaft (13) by a second bolt (14).

2. The engine high pressure turbine enclosure containment test structure of claim 1, wherein: The upper end of the conical protective cylinder (4) is provided with 6 limiting grooves (19) evenly spaced along the circumferential edge; there are 6 sets of protective seats (16) and the 6 sets of protective seats (16) are respectively located in the 6 limiting grooves (19) to form an open annular structure; the protective plate (15) is a split structure.

3. The engine high pressure turbine enclosure containment test structure of claim 1, wherein: The casing adapter plate (6) is coaxially provided with an inner ring boss (20) and an outer ring boss (21). The inner ring boss (20) is connected to the conical protective cylinder (4) and the protective seat (16). The outer ring boss (21) is connected to the simulated split casing (7). The axial length of the outer ring boss (21) is greater than the axial length of the inner ring boss (20). Both ends of the simulated split casing (7) are provided with flanges. The simulated split casing (7) is threadedly connected to the casing adapter plate (6) and the high-pressure turbine casing (9) respectively by tightening self-locking nuts on the flanges.

4. The test structure for containing the high-pressure turbine casing of an engine as described in claim 1, characterized in that: The first tester cover (5) has four screw holes along the circumference. Each of the four screw holes is provided with a fixing bolt (1) connected to the casing adapter plate (6). The fixing bolt (1) has a stepped structure and the step diameter of the fixing bolt (1) gradually decreases from the head to the end. A fixing nut (18) is threaded onto the end of the fixing bolt (1). A fifth bolt (2) is also connected between the casing adapter plate (6) and the first tester cover (5) at the position corresponding to the inner side of the fixing bolt (1).

5. The test structure for containing the high-pressure turbine casing of an engine as described in claim 1, characterized in that: A first flange (22) and a second flange (23) are coaxially arranged on the first adapter shaft (13). The first flange (22) is bolted to the drive shaft assembly (12), and the second flange (23) is connected to the test rotor (11) by a pin. The maximum radius of the first flange (22) is less than the straight distance from the axis of the second flange (23) to the innermost edge of the pin hole on the second flange (23). There is a gap between the first flange (22) and the second flange (23).

6. The engine high-pressure turbine casing containment test structure as described in claim 5, characterized in that: Two balance points are provided on the first adapter shaft (13): a first balance point (24) and a second balance point (25). The first balance point (24) is located in the middle of the drive shaft sleeve (28) of the drive shaft assembly (12), and the second balance point (25) is located on the first adapter shaft (13) at one end away from the test rotor (11).

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