A turbine test piece and its assembly method

Abstract

The turbine test piece includes a load-bearing casing, a turbine rotor shaft, and an adapter shaft. The load-bearing casing, the adapter shaft, and the sealing structure form a sealing cavity. The turbine test piece further includes an adjusting ring, which is arranged in the accommodation space between the turbine rotor shaft and the adapter shaft. Among them, a first air inlet hole is provided on the adapter shaft, a second air inlet hole is provided on the turbine rotor shaft, and a third air inlet hole is provided on the adjusting ring. In the assembled state, the third air inlet hole communicates with the first air inlet hole and the second air inlet hole to form an exhaust passage from the sealing cavity to the central shaft hole. A method for assembling the turbine test piece is also provided.

Description

Technical Field

[0001] The present invention relates to engine assembly, and particularly to a turbine test piece and an assembly method thereof. Background Art

[0002] The turbine test piece is composed of a turbine and a load-bearing casing. A plurality of bearings are provided on the load-bearing casing to support the turbine rotor shaft, enabling the rotation of the turbine test piece. During the working process of the bearings, lubricating oil needs to be continuously supplied for lubrication and cooling to ensure that the bearings are in a good working environment. However, the lubricating oil must be restricted within a relatively enclosed cavity, and the sealing of the bearing cavity is very crucial in the design of the turbine test piece.

[0003] In order to effectively seal the bearing cavity, sealing gas at a certain pressure needs to be supplied to the sealing cavity outside the bearing cavity, so that the pressure in the sealing cavity is greater than the pressure in the bearing cavity. At the same time, the sealing gas in the sealing cavity outside the bearing cavity needs to be discharged outside the test piece to maintain the stability of the pressure in the sealing cavity. Usually, the air intake is realized through an air intake pipe, and the exhaust is realized through an exhaust pipe (or ventilation pipe). This design requires an additional external ventilation pipeline to discharge the sealing gas, and the structure is relatively complex. Therefore, it is necessary to provide a test piece with a compact sealing structure to simplify the design of the sealing cavity. Summary of the Invention

[0004] An object of the present invention is to provide a turbine test piece that can simplify the design of the sealing structure.

[0005] The above-mentioned turbine test piece includes a load-bearing casing, a turbine rotor shaft, and a connecting shaft. The load-bearing casing, the connecting shaft, and the sealing structure form a sealing cavity. The turbine test piece further includes: an adjusting ring disposed in the accommodation space between the turbine rotor shaft and the connecting shaft; wherein, a first air intake hole is provided on the connecting shaft, a second air intake hole is provided on the turbine rotor shaft, and a third air intake hole is provided on the adjusting ring. In the assembled state, the third air intake hole communicates the first air intake hole with the second air intake hole, forming an exhaust passage from the sealing cavity to the central shaft hole of the turbine rotor shaft.

[0006] In one or more embodiments, a plurality of the first air intake holes are provided on the connecting shaft, a plurality of the second air intake holes are provided on the turbine rotor shaft, and a plurality of the third air intake holes are provided on the adjusting ring, forming a plurality of the exhaust passages.

[0007] In one or more embodiments, the first air intake hole, the second air intake hole, and the third air intake hole are circumferentially evenly distributed and have the same number.

[0008] The above-mentioned turbine test piece is easy to adjust to align and connect the air intake holes on the turbine rotor shaft and the adapter shaft by providing air intake holes on the turbine rotor shaft and the adapter shaft and through the transitional connection of the adjusting ring, forming an exhaust passage from the seal cavity to the outside of the test piece to maintain the pressure stability in the seal cavity, without the need to additionally arrange an air duct to discharge the seal gas, thus simplifying the seal structure design.

[0009] Another object of the present invention is to provide a method for assembling a turbine test piece, which is easy to realize the assembly of the above-mentioned turbine test piece.

[0010] The above-mentioned method for assembling a turbine test piece includes the following steps: providing an adapter shaft with a first air intake hole provided thereon; providing a turbine rotor shaft with a second air intake hole provided thereon; providing an adjusting ring with a third air intake hole provided thereon; docking the adapter shaft with the turbine rotor shaft, and after docking, the first air intake hole and the second air intake hole are correspondingly arranged, and a receiving space is formed between the adapter shaft and the turbine rotor shaft;

[0011] Installing the adjusting ring in the receiving space includes: adjusting the angular position of the adjusting ring to connect the third air intake hole with the first air intake hole and the second air intake hole; providing a fastener, and fixing the adjusting ring in the receiving space through the fastener.

[0012] In one or more embodiments, the method for assembling a turbine test piece further includes: providing a turbine test piece installation tool, and using the turbine test piece installation tool to install the adjusting ring in the receiving space. The turbine test piece installation tool includes: a first positioning member including a positioning seat and one of a plurality of guide shafts or a plurality of guide holes, the positioning seat having a limiting surface and a mounting hole; a second positioning member including the other of the plurality of guide holes or the plurality of guide shafts and a plurality of first positioning portions; and a positioning pin;

[0013] The adjusting ring includes a plurality of second positioning portions. In the assembled state, the plurality of first positioning portions cooperate with the plurality of second positioning portions to connect the third air intake hole with the first air intake hole and the second air intake hole;

[0014] Installing the adjusting ring in the receiving space includes: mounting the first positioning member on the end of the turbine rotor shaft through the limiting surface; rotating the first positioning member to align the mounting hole with the second air intake hole; installing the positioning pin in the mounting hole so that the positioning pin protrudes and inserts into the second air intake hole; placing the adjusting ring in the receiving space; installing the second positioning member so that the plurality of guide shafts are arranged in the plurality of guide holes; rotating the adjusting ring so that the plurality of second positioning portions cooperate with the plurality of first positioning portions.

[0015] In one or more embodiments, the second positioning member has a first positioning surface and a second positioning surface which are oppositely arranged. The plurality of guiding holes are formed in the first positioning surface, and the plurality of first positioning portions are arranged on the second positioning surface.

[0016] In one or more embodiments, the second positioning member further includes a force applying portion.

[0017] In one or more embodiments, the first positioning portion is a positioning boss, and the second positioning portion is a positioning hole.

[0018] In one or more embodiments, at least one side of the positioning seat is provided with an avoidance notch.

[0019] The above-mentioned turbine test piece assembly method positions the adjustment ring by adjusting its angular position, so that the third air guiding hole can communicate with the first air guiding hole and the second air guiding hole to form an exhaust passage, so as to maintain the pressure stability in the sealing cavity. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The above and other features, properties and advantages of the present invention will become more obvious through the following description with reference to the drawings and embodiments, wherein:

[0021] Figure 1 is a schematic structural diagram of a turbine test piece according to an embodiment.

[0022] Figure 2 is a partially enlarged schematic diagram of a turbine test piece according to an embodiment.

[0023] Figure 3 is an installation schematic diagram of a turbine test piece installation tool according to an embodiment.

[0024] Figure 4 is a schematic structural diagram of a turbine test piece installation tool according to an embodiment.

[0025] Figure 5 is a schematic diagram of a turbine test piece installation tool in an assembled state according to an embodiment. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0026] The present invention will be further described below in conjunction with specific embodiments and the accompanying drawings. In the following description, more details are set forth to facilitate a full understanding of the present invention. However, the present invention is clearly capable of being implemented in many other ways different from this description. Those skilled in the art can make similar generalizations and deductions according to the actual application situation without departing from the connotation of the present invention. Therefore, the protection scope of the present invention should not be limited by the content of these specific embodiments. It should be noted that these and subsequent other drawings are only examples, and they are not drawn under the condition of equal proportion, and should not be used to limit the actual required protection scope of the present invention.

[0027] As Figure 1 and Figure 2 shown, the turbine test piece includes a turbine assembly 1, a load-bearing casing 2, a turbine rotor shaft 3, a transfer shaft 4, a bearing assembly 6, and an adjusting ring 7. The stator component in the turbine assembly 1 is connected to the load-bearing casing 2, and the rotor component in the turbine assembly 1 is connected to the turbine rotor shaft 3 through the transfer shaft 4. Front and rear bearing assemblies 6 are arranged on the turbine rotor shaft 3 to support the load-bearing casing 2. The bearing assembly 6 requires lubrication with lubricating oil. To ensure that the lubricating oil in the bearing assembly 6 can be restricted within the bearing cavity 61, as Figure 2 shown, the load-bearing casing 2, the transfer shaft 4, and the sealing structure form a sealing cavity 62. An air supply pipe 21 is arranged in the load-bearing casing 2, and sealing air with a certain pressure is supplied to the sealing cavity 62 through the air supply pipe 21 in the direction shown by the arrow in the figure, so that the pressure in the sealing cavity 62 is greater than the pressure in the bearing cavity 61 to achieve the sealing effect on the bearing cavity 61.

[0028] The adjusting ring 7 is arranged in the accommodation space 5 between the turbine rotor shaft 3 and the transfer shaft 4. In a specific embodiment, the turbine rotor shaft 3 and the transfer shaft 4 are connected by splines 32. After connection, there is an accommodation space 5 between the end 33 of the rotor shaft and the transfer shaft 4, and the adjusting ring 7 is arranged in this accommodation space 5. Wherein, a first air intake hole 41 is formed on the transfer shaft 4, and the sealing cavity 62 and the accommodation space 5 can be communicated through the first air intake hole 41. A second air intake hole 31 is formed on the turbine rotor shaft 3, and the accommodation space 5 and the central shaft hole 35 of the turbine rotor shaft 3 can be communicated through the second air intake hole 31. A third air intake hole 72 is formed on the adjusting ring 7. In the assembled state, the inner and outer circumferential surfaces of the adjusting ring 7 are respectively in contact with the turbine rotor shaft 3 and the transfer shaft 4, and the third air intake hole 72 communicates the first air intake hole 41 and the second air intake hole 31 to jointly form an exhaust passage communicating the sealing cavity 62 to the central shaft hole 35. The central shaft hole 35 is communicated with the outside of the test piece. Therefore, the sealing air can, as Figure 2 shown by the arrow in the figure, enter the sealing cavity 62 from the air supply pipe 21 and then be discharged to the outside of the test piece through the first air intake hole 41, the third air intake hole 72, and the second air intake hole 31 in sequence to maintain the pressure stability in the sealing cavity 62.

[0029] In one embodiment, there are multiple first air guide holes 41 formed in the upper adapter shaft 4. Correspondingly, there are multiple second air guide holes 31 formed in the turbine rotor shaft 3. In this embodiment, by forming multiple third air guide holes 72 in the adjusting ring 7, multiple exhaust channels are formed, thereby increasing the exhaust efficiency of the sealing cavity 62.

[0030] In Figure 4 In the embodiment shown, the multiple third air guide holes 72 are circumferentially evenly distributed along the adjusting ring 7. The multiple first air guide holes 41 and the multiple second air guide holes 31 have the same circumferential position as the multiple third air guide holes 72 and the same number as the third air guide holes 72. By arranging the air guide holes evenly in the circumferential direction, it is easier to align the air guide holes with each other during assembly, improving the assembly efficiency.

[0031] In other embodiments, the number of the first air guide holes 41, the second air guide holes 31, and the third air guide holes 72 can be one or more, and the arrangement of the first air guide holes 41, the second air guide holes 31, and the third air guide holes 72 is not limited to the embodiment shown in the figure. For example, they can be unevenly distributed in the circumferential direction. As long as in the assembled state, the third air guide holes 72 can connect at least one group of the first air guide holes 41 and the second air guide holes 31 to form at least one exhaust channel so that the sealing gas can be discharged from the sealing cavity 62 to the outside of the turbine test piece.

[0032] In Figure 2 In the embodiment shown, a fastener 10 is provided on one side of the adjusting ring 7 close to the end 33 of the rotor shaft. In a specific embodiment, the fastener is a compression nut, which can fix the adjusting ring 7 in the accommodation space 5 after the installation of the adjusting ring 7 is completed, further limiting the adjusting ring 7 axially.

[0033] In the turbine test piece described in one or more of the above embodiments, by forming air guide holes in the turbine rotor shaft 3 and the adapter shaft 4 and through the transitional connection of the adjusting ring 7, it is easy to adjust to align and connect the air guide holes on the turbine rotor shaft 3 and the adapter shaft 4, forming an exhaust channel from the sealing cavity 62 to the outside of the test piece to maintain the pressure stability in the sealing cavity 62, without the need to additionally set up an air duct to discharge the sealing gas, simplifying the design of the sealing structure.

[0034] At the same time, after the third air guide holes 72 that play the role of adjusting and connecting are arranged on the adjusting ring 7 and locked by the compression nut, while achieving the assembly stability, it avoids the difficulty in balancing the alignment of the air guide holes and the torque caused by directly setting the air guide holes on the compression nut.

[0035] Another aspect of the present disclosure provides a method for installing a turbine test piece, which is easy to realize the assembly of the turbine test piece described in one or more of the above embodiments.

[0036] Since the accommodation space 5 between the transfer shaft 4 and the turbine rotor shaft 3 is a blind cavity, it is impossible to visually identify whether the third air guide hole 72 is adjusted to a suitable position during the assembly process so that it can communicate with the first air guide hole 41 and the second air guide hole 31. A turbine test piece installation method is provided to position the adjustment ring 7 in the circumferential direction and realize the installation of the adjustment ring 7. The turbine test piece assembly method includes the following steps:

[0037] Provide a transfer shaft 4, and a first air guide hole 41 is opened on the transfer shaft 4;

[0038] Provide a turbine rotor shaft 3, and a second air guide hole 31 is opened on the turbine rotor shaft 3;

[0039] Provide an adjustment ring 7, and a third air guide hole 72 is opened on the adjustment ring 7;

[0040] Dock the transfer shaft 4 with the turbine rotor shaft 3. After docking, the first air guide hole 41 and the second air guide hole 31 are arranged correspondingly, and an accommodation space 5 is formed between the transfer shaft 4 and the turbine rotor shaft 3;

[0041] Install the adjustment ring 7 in the accommodation space 5, including: adjusting the angular position of the adjustment ring 7 so that the third air guide hole 72 communicates with the first air guide hole 41 and the second air guide hole 31;

[0042] Provide a fastener 10, and fix the adjustment ring 7 in the accommodation space 5 through the fastener 10.

[0043] The corresponding arrangement of the first air guide hole 41 and the second air guide hole 31 means that in the assembled state, the first air guide hole 41 and the second air guide hole 31 can be communicated through the third air guide hole 72 opened on the adjustment ring 7 to form at least one exhaust channel. The specific arrangement mode and quantity of the first air guide hole 41 and the second air guide hole 31 are not limited. For example, when the third air guide hole 72 opened on the adjustment ring 7 is a straight hole, the first air guide hole 41 and the second air guide hole 31 need to be aligned. When the third air guide hole 72 opened on the adjustment ring 7 is an inclined hole, a certain angular position offset arrangement between the first air guide hole 41 and the second air guide hole 31 is allowed.

[0044] To realize the installation of the adjustment ring 7 in the accommodation space 5, the turbine test piece assembly method further includes: providing a turbine test piece installation tool, and using this turbine test piece installation tool to install the adjustment ring 7 in the accommodation space 5, as Figures 3 to 5 shown, the installation tool includes a first positioning member 8, a second positioning member 9 and a positioning pin 85.

[0045] The first positioning member 8 includes a positioning seat 81 and a plurality of guide shafts 83. The positioning seat 81 has a limiting surface 82 and a mounting hole 84. The limiting surface 82 is used to axially limit the first positioning member 8, and the first positioning member 8 is engaged with a positioning pin 85 through the mounting hole 84 on the positioning seat 81.

[0046] The second positioning member 9 includes a plurality of guide holes 93 and a plurality of first positioning portions 94. The plurality of guide holes 93 can be engaged with the plurality of guide shafts 83 to make the second positioning member 9 have the same angular position as the first positioning member 8 in the assembled state, and the second positioning member 9 is axially movable relative to the first positioning member 8. By providing a plurality of mutually engaged guide shafts 83 and a plurality of guide holes 93, it is possible to prevent the second positioning member 9 from rotating around a single guide shaft 83 and deflecting during movement.

[0047] In some other suitable embodiments, the guide holes can be provided on the first positioning member, and correspondingly, guide shafts can be provided on the second positioning member.

[0048] The adjusting ring 7 further includes a plurality of second positioning portions 73. The plurality of second positioning portions 73 can be engaged with the plurality of first positioning portions 94 to realize the mating assembly of the adjusting ring 7 and the second positioning member 9. And in the assembled state, through the engagement of the plurality of second positioning portions 73 and the first positioning portions 94, the angular position of the adjusting ring 7 can be determined. By reasonably configuring the second positioning portions 73 and the first positioning portions 94, it can be ensured that in the assembled state, the third air guide hole 72 is exactly in the position where it communicates with the first air guide hole 41 and the second air guide hole 31, realizing the assembly of the adjusting ring 7.

[0049] In one embodiment, the structure of the turbine test piece installation tool is as Figure 4 shown. The outer peripheral surface of the positioning seat 81 is a cylindrical surface corresponding to the central shaft hole 35. One end of the positioning seat 81 is provided with a limiting platform 88 protruding radially outward. The limiting platform 88 has a limiting surface 82. Combining Figure 3 , during the assembly process, by mating the limiting surface 82 with the rotor shaft end face 34 of the turbine rotor shaft 3, the first positioning member 8 can be axially limited. A plurality of guide shafts 83 are provided on the limiting platform, and the guide shafts 83 extend axially. In Figure 4 the shown embodiment, the outer peripheral surface of the limiting platform 88 is a cylindrical surface, and the diameter of this cylindrical surface needs to be smaller than the inner peripheral surface diameter of the adjusting ring 7, so that the adjusting ring 7 can pass through the first positioning member 8 during installation and be placed in the accommodation space 5 between the adapter shaft 4 and the turbine rotor shaft 3.

[0050] As Figure 4As shown, an installation hole 84 is formed in the positioning seat 81, and the center of the installation hole 84 is located on the axis of the positioning seat 81. The axis of the positioning seat 81 is also the axis of the central shaft hole 35 of the turbine rotor shaft 3. Thus, when adjusting the angular position of the positioning pin 85, the positioning seat 81 and the positioning pin 85 will only rotate around the axis. In the assembled state, the positioning pin 85 is arranged in the installation hole 84 and is movable along the axis direction of the installation hole 84. By adjusting the angular position of the positioning pin 85, one end of it can protrude and be inserted into the second air guide hole 31, realizing the angular positioning of the first positioning member 8.

[0051] In one embodiment, a groove 86 is axially formed in the positioning seat 81. By providing the groove 86, the operating space for adjusting the positioning pin 85 can be increased, facilitating the installation of the first positioning member 8 and also facilitating seeing the position of the installation hole 84 during the assembly process.

[0052] In one embodiment, avoidance notches 87 are provided on both sides of the positioning seat 81, enabling the visible installation of the positioning pin 85. Specifically, by providing the avoidance notch 87 on at least one side of the positioning seat 81, when the first positioning member 8 is mounted on the central shaft hole 35 during the assembly process, the position of the second air guide hole 31 on the turbine rotor shaft 3 can be directly observed from the avoidance notch 87, facilitating the installation of the positioning pin 85.

[0053] As Figure 4 shown, in one embodiment, the second positioning member 9 includes a positioning portion 91 and a force - applying portion 92. The two side walls of the positioning portion 91 are arc surfaces corresponding to the shape of the adjusting ring 7, and have a relatively arranged first positioning surface 95 and a second positioning surface 96. A force - applying portion 92 is provided on one side of the first positioning surface 95, and a plurality of guide holes 93 for cooperating with a plurality of guide shafts 83 are formed on the other side, enabling the second positioning member 9 to be axially movable relative to the first positioning member 8; a plurality of first positioning portions 94 for cooperating with the second positioning portion 73 are provided on the second positioning surface 96, and the adjusting ring 7 can be fixedly installed on the second positioning surface 96. A certain space is formed between the first positioning surface 95 and the second positioning surface 96. In the assembled state, by applying a force to the first positioning surface 95, the adjusting ring 7 can be pushed to the bottom of the accommodation space 5 by the second positioning surface 96, realizing the installation of the adjusting ring 7. By providing the force - applying portion 92, it is convenient to apply a force to the first positioning surface 95.

[0054] In one embodiment, the first positioning portion 94 is a positioning boss, the second positioning portion 73 is a positioning hole having the same circumferential position as the third air guide hole 72, and the angular positioning of the adjusting ring 7 is achieved through the cooperation between the first positioning portion 94 and the second positioning portion 73. When the adjusting ring 7 is in this angular position, the third air guide hole 72 can communicate with the first air guide hole 41 and the second air guide hole 31 to form an exhaust passage. In other embodiments, the first positioning portion 94 and the second positioning portion 73 may be other cooperation methods. For example, the first positioning portion 94 is a groove and the second positioning portion 73 is a protrusion, as long as the adjusting ring 7 is circumferentially immovable relative to the second positioning member 9 through the cooperation between the first positioning portion 94 and the second positioning portion 73 in the assembled state, so as to achieve the angular positioning of the adjusting ring 7 to form an exhaust passage.

[0055] Reference Figure 5 , in a specific embodiment, the adjusting ring 7 is installed by the above turbine test piece installation tool. The step of installing the adjusting ring 7 in the accommodation space 5 includes:

[0056] The first positioning member 8 is placed on the end portion 33 of the turbine rotor shaft through the limiting surface 82;

[0057] The first positioning member 8 is rotated to align the mounting hole 84 with the second air guide hole 31;

[0058] The positioning pin 85 is installed in the mounting hole 84 so that the positioning pin 85 protrudes and is inserted into the second air guide hole 31;

[0059] The adjusting ring 7 is placed in the accommodation space 5;

[0060] The second positioning member 9 is installed so that the plurality of guide shafts 83 are disposed in the plurality of guide holes 93;

[0061] The adjusting ring 7 is rotated so that the plurality of second positioning portions 73 cooperate with the plurality of first positioning portions 94.

[0062] When the positioning pin 85 is inserted into the second air guide hole 31 on the turbine rotor shaft 3 in the above installation method, the angular position of the first positioning member 8 can be determined through the cooperation between the positioning pin 85 and the mounting hole 84, the angular position of the second positioning member 9 can be determined through the cooperation between the guide shaft 83 and the guide hole 93, and then the angular position of the adjusting ring 7 can be determined through the cooperation between the first positioning portion 94 and the second positioning portion 73. And when the adjusting ring 7 is in this angular position, since the first air guide hole 41 and the second air guide hole 31 are correspondingly arranged, the third air guide hole 72 can communicate with the first air guide hole 41 and the second air guide hole 31 to form an exhaust passage from the sealing cavity 62 to the outside of the turbine test piece.

[0063] In another embodiment, the positioning pin 85 can be first installed in the mounting hole 84 on the first positioning member 8, and then the assembled first positioning member 8 and the positioning pin 85 are placed into the central shaft hole 35. The first positioning member 8 is rotated so that the positioning pin 85 can protrude and be inserted into the second air guide hole 31.

[0064] In one embodiment, the assembly of the turbine test piece installation tool and the adjusting ring 7 can be completed first. The adjusting ring 7 is pushed into the accommodation space 5 through the installation tool. The second positioning member 9 is rotated to adjust the angular position of the positioning pin 85 so that it can protrude and be inserted into the second air guide hole 31. The angular synchronization between the first positioning member 8 and the second positioning member 9 can be achieved through the cooperation of the guiding shaft 83 and the guiding hole 93, and the angular synchronization between the second positioning member 9 and the adjusting ring 7 can be achieved through the cooperation of the first positioning portion 94 and the second positioning portion 73. Therefore, when the adjusting ring 7 is installed, the angular position of the adjusting ring 7 can be synchronously adjusted by adjusting the angular position of the installation tool. When the positioning pin 85 is determined at a certain angular position, the angular position of the adjusting ring 7 can be determined. And when the adjusting ring 7 is in this angular position, the third air guide hole 72 can communicate with the first air guide hole 41 and the second air guide hole 31 to form an exhaust passage.

[0065] Although the present invention is disclosed above with preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent change and decoration made to the above embodiments based on the technical essence of the present invention without departing from the technical solution of the present invention all fall within the protection scope defined by the claims of the present invention.

Claims

1. Turbine test piece, comprising a load-bearing casing, a turbine rotor shaft and an adapter shaft, wherein the load-bearing casing, the adapter shaft and a sealing structure form a sealing cavity, characterized in that, The turbine test piece further includes: An adjusting ring disposed in the accommodation space between the turbine rotor shaft and the adapter shaft; Wherein, a first air guiding hole is formed on the adapter shaft, a second air guiding hole is formed on the turbine rotor shaft, and a third air guiding hole is formed on the adjusting ring. In the assembled state, the angular position of the adjusting ring is adjusted so that the third air guiding hole communicates with the first air guiding hole and the second air guiding hole, forming an exhaust passage from the sealing cavity to the central shaft hole of the turbine rotor shaft.

2. The turbine test piece according to claim 1, characterized in that, A plurality of the first air guiding holes are formed on the adapter shaft, a plurality of the second air guiding holes are formed on the turbine rotor shaft, and a plurality of the third air guiding holes are formed on the adjusting ring, forming a plurality of the exhaust passages.

3. The turbine test piece according to claim 2, characterized in that, The first air guiding hole, the second air guiding hole, and the third air guiding hole are circumferentially evenly distributed and have the same number.

4. Assembly method of turbine test piece, characterized in that, It includes the following steps: Provide an adapter shaft on which a first air guiding hole is formed; Provide a turbine rotor shaft on which a second air guiding hole is formed; Provide an adjusting ring on which a third air guiding hole is formed; Dock the adapter shaft with the turbine rotor shaft. After docking, the first air guiding hole and the second air guiding hole are correspondingly arranged, and an accommodation space is formed between the adapter shaft and the turbine rotor shaft; Install the adjusting ring in the accommodation space, including: Adjust the angular position of the adjusting ring so that the third air guiding hole communicates with the first air guiding hole and the second air guiding hole; Provide a fastener, and fix the adjusting ring in the accommodation space through the fastener.

5. The turbine test piece assembly method according to claim 4, characterized in that, It further includes: Provide a turbine test piece installation tool, and use the turbine test piece installation tool to install the adjusting ring in the accommodation space. The turbine test piece installation tool includes: A first positioning member, including a positioning seat and one of a plurality of guiding shafts or a plurality of guiding holes. The positioning seat has a limiting surface and a mounting hole; A second positioning member, including the other of the plurality of guiding holes or the plurality of guiding shafts and a plurality of first positioning portions; and A positioning pin; The adjusting ring includes a plurality of second positioning portions. In the assembled state, the plurality of first positioning portions cooperate with the plurality of second positioning portions so that the third air guiding hole communicates with the first air guiding hole and the second air guiding hole; Installing the adjusting ring in the accommodation space includes: Mount the first positioning member on the end of the turbine rotor shaft through the limiting surface; Rotate the first positioning member to align the mounting hole with the second air guiding hole; Install the positioning pin in the mounting hole so that the positioning pin protrudes and inserts into the second air guiding hole; Place the adjusting ring in the accommodation space; Install the second positioning member so that the plurality of guiding shafts are disposed in the plurality of guiding holes; Rotate the adjusting ring so that the plurality of second positioning portions cooperate with the plurality of first positioning portions.

6. The turbine test piece assembly method according to claim 5, characterized in that The second positioning member has a first positioning surface and a second positioning surface which are oppositely arranged. The plurality of guiding holes are formed on the first positioning surface, and the plurality of first positioning portions are arranged on the second positioning surface.

7. The turbine test piece assembly method according to claim 5, characterized in that, The second positioning member further includes a force applying portion.

8. The turbine test piece assembly method according to claim 5, characterized in that, The first positioning portion is a positioning boss, and the second positioning portion is a positioning hole.

9. The turbine test piece assembly method according to claim 5, characterized in that, At least one side of the positioning seat is provided with an avoidance notch.

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