Turbine disc rotation test device

Abstract

The invention belongs to the technical field of aero-engines, and provides a turbine disc rotation test device which comprises an adapter mandrel, an elastic pressing structure and a locking piece. The adapter core shaft comprises a core shaft body, a positioning sleeve is arranged at the front end of the core shaft body, an annular area is defined by the outer circumferential wall of the core shaft body and the inner circumferential wall of the positioning sleeve, the core shaft body penetrates through a central hole of the turbine disc, and the outer cylindrical end of a shaft neck of the turbine disc is inserted into the annular area. The elastic pressing structure is positioned at the other end of the turbine disc and is matched with the switching core shaft to clamp the turbine disc; the locking piece is arranged at the tail end of the core shaft, makes contact with the elastic pressing structure and presses the elastic pressing structure, and the turbine disc is clamped and fixed. According to the device, through the design of the elastic pressing structure, the locking piece and the positioning sleeve on the mandrel, the technical problems that vibration is caused by unreliable positioning of the wheel disc, cracks are generated in advance due to large test stress and the like can be solved.

Description

Technical Field

[0001] The present invention belongs to the technical field of aeroengines and relates to a turbine disk rotation test device. Background Art

[0002] In an aeroengine, an arc-end tooth has unique automatic centering characteristics, especially good thermal centering characteristics under severe temperature changes, and has wide applications. In small and medium-sized gas turbine engines, more and more turbine disks adopt arc-end tooth centering and torque transmission to achieve disk-shaft connection. This design has the advantages of compact structure, convenient assembly and disassembly, and light weight. For the assessment of the structural integrity of the turbine disk, a static strength test of the aeroengine turbine disk is required. The disk test should be carried out on a rotation test device, and it is required that all connecting parts of the disk test piece should be reliably connected and have little vibration.

[0003] At present, the operating speed of small aeroengines is high. When conducting a disk rotation test, it is necessary to connect it through an adapter section with an arc-end tooth connection structure to achieve circumferential torque transmission and radial centering. Under the action of centrifugal force, each part of the rotor generates radial elongation, which will cause axial contraction. Therefore, in order to ensure the normal and safe operation of the rotor, an appropriate axial pre-tightening force needs to be applied. However, the existing adapter sections are usually machined with arc-end teeth, which have high process requirements and long processing cycles, resulting in high processing costs and time costs of the adapter sections, bringing difficulties to the disk rotation test.

[0004] In addition, under the action of centrifugal force, each part of the rotor generates radial elongation, which will cause axial contraction. To ensure the normal and safe operation of the rotor, an appropriate axial pre-tightening force needs to be applied. If the tightening torque of the compression nut is not large enough, there will be a problem of large vibration caused by unreliable disk positioning during the test; if the tightening torque of the compression nut is too large, the turbine disk will bear an axial force that it does not bear under the engine condition, which is not only inconvenient for assembly and disassembly, but also will cause large stress at positions where the turbine disk should not have large stress, and there is a risk of early cracks in the test. Summary of the Invention

[0005] In order to solve technical problems such as vibration problems caused by unreliable disk positioning and early crack generation due to large test stress, the present invention discloses a turbine disk rotation test device, which includes: an adapter mandrel, an elastic pressing structure, and a locking member.

[0006] Wherein, the adapter mandrel includes a mandrel, a positioning sleeve is provided at the front end of the mandrel, an annular region is formed between the outer peripheral wall of the mandrel and the inner peripheral wall of the positioning sleeve, the mandrel passes through the central hole of the turbine disk, and the outer cylindrical end of the journal of the turbine disk is inserted into the annular region;

[0007] The elastic pressing structure is located at the other end of the turbine disk and cooperates with the adapter mandrel to clamp the turbine disk; the locking member is arranged at the end of the mandrel, contacts and presses against the elastic pressing structure to clamp and fix the turbine disk.

[0008] Furthermore, the adapter mandrel further includes a dynamic balance structure, and the dynamic balance structure includes balance screws and an annular boss located at the front end of the mandrel. A plurality of threaded holes for installing the first balance screws are evenly formed in the annular boss.

[0009] Furthermore, the elastic pressing structure includes a gland and an annular elastic member. The annular elastic member is located between the gland and the turbine disk. One end of the annular elastic member is connected to the gland, and the other end is in contact with the turbine disk surface.

[0010] The annular elastic member includes a water droplet portion and a U-shaped portion. One end of the water droplet portion is connected to the gland, the other end of the water droplet portion is connected to one end of the U-shaped portion, and the other end of the U-shaped portion is in contact with the turbine disk surface.

[0011] Still further, the U-shaped portion includes a first vertical wall ring surface, a first semi-circular ring surface, and a first inclined wall ring surface that are connected in sequence. The first vertical wall ring surface is connected to the water droplet portion, and the first vertical wall ring surface is in contact with the turbine disk surface; <{

[0012] The water droplet portion includes a second semi-circular ring surface, a second inclined wall ring surface, and the first inclined wall ring surface.

[0013] Preferably, an annular clamping platform is provided on the surface of the gland facing the annular elastic member. The water droplet portion includes a horizontal wall ring surface connected to the second inclined wall ring surface. The horizontal wall ring surface and the second inclined wall ring surface form a clamping groove for positioning the annular clamping platform to clamp and connect the water droplet portion and the gland.

[0014] Still further, a plurality of connection holes are circumferentially provided on the surface of the gland facing away from the annular elastic member, and second balance screws are installed in the connection holes.

[0015] Furthermore, a plurality of limiting teeth are evenly arranged circumferentially at the tail end of the mandrel, and a plurality of clamping heads facing the axial center direction are evenly arranged circumferentially on the locking member. One of the limiting teeth is inserted between adjacent two of the clamping heads.

[0016] Compared with the prior art, the beneficial effects that can be achieved by at least one of the above technical solutions adopted in the embodiments of this specification at least include:

[0017] The invention mainly aims at a turbine disk with an integrated structure of a disk and a shaft, and provides a rotary test device for connecting it to a test equipment. First, a positioning sleeve is designed at the connection between the adapter mandrel and the journal of the turbine disk to radially position the turbine disk, so as to simulate the extrusion force received by the outer cylindrical surface of the journal of the turbine disk under the engine state. Secondly, an elastic pressing structure and a locking part are designed. The axial deformation generated by the turbine disk under the centrifugal action is absorbed by compressing its deformation. The elastic component is pressed and fixed by a gland, and the locking part is sleeved on the mandrel to apply a pressing force towards the turbine disk to axially press the turbine disk 2, making the axial positioning of the whole device reliable. [[ID=I]] BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required to be used in the embodiments will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the present application. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0019] Figure 1 Schematic diagram of the turbine disk rotary test device disclosed in the embodiment of the present invention;

[0020] Figure 2 Schematic diagram of the adapter mandrel disclosed in the embodiment of the present invention;

[0021] Figure 3 Schematic diagram of the annular elastic member disclosed in the embodiment of the present invention;

[0022] Figure 4 Schematic diagram of the gland disclosed in the embodiment of the present invention;

[0023] Figure 5 Schematic diagram of the locking part disclosed in the embodiment of the present invention;

[0024] Among them, 1. Adapter mandrel; 2. Turbine disk; 3. Annular elastic member; 4. Gland; 5. Locking part; 6. First balance screw; 7. Second balance screw; 8. Locking piece; 10. Mandrel; 11. Positioning sleeve; 12. Annular boss; 13. Limiting tooth; 14. Annular area; 31. First vertical wall ring surface; 32. First semi-circular ring surface; 33. First inclined wall ring surface; 34. Second semi-circular ring surface; 35. Second inclined wall ring surface; 36. Horizontal wall ring surface; 37. Second vertical wall ring surface; 41. Annular clamping platform; 42. Connecting hole; 51. Chuck. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0025] The embodiments of the present application will be described in detail below with reference to the drawings.

[0026] The following describes the implementation manners of the present application through specific examples. Those skilled in the art can easily understand other advantages and effects of the present application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all embodiments. The present application can also be implemented or applied through other different specific implementation manners. Various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, without conflict, the following embodiments and the features of the embodiments can be combined with each other. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present application without creative efforts belong to the scope protected by the present application.

[0027] An embodiment of the present invention discloses a turbine disk rotation test device. Refer to Figure 1 and Figure 2 As shown, the device includes a transfer mandrel 1, an elastic pressing structure, and a locking member 5. The transfer mandrel 1 includes a mandrel 10. A positioning sleeve 11 is provided at the front end of the mandrel 10. An annular region 14 is formed between the outer peripheral wall of the mandrel 10 and the inner peripheral wall of the positioning sleeve 11. The mandrel 10 passes through the central hole of the turbine disk 2, and the outer cylindrical end of the journal of the turbine disk 2 is inserted into the annular region 14. The elastic pressing structure is located at the other end of the turbine disk 2 and cooperates with the transfer mandrel 1 to clamp the turbine disk 2; the locking member 5 is provided at the end of the mandrel 10, contacts and presses the elastic pressing structure, and clamps and fixes the turbine disk 2.

[0028] The design of the positioning sleeve 11 on the mandrel 10 can simulate the radial extrusion force of adjacent parts on the outer cylindrical surface of the journal of the turbine disk 2 under the engine state. In the design, the positioning sleeve 11 mainly has two parameters: thickness and sleeve length. By changing the sizes of the two parameters, the magnitude of the radial extrusion force on the turbine disk 2 can be adjusted.

[0029] Furthermore, the transfer mandrel 1 further includes a dynamic balance structure. Refer to Figure 1 and Figure 2 As shown, the dynamic balance structure includes balance screws and an annular boss 12 located at the front end of the mandrel 10. A plurality of threaded holes for installing the first balance screws 6 are evenly formed on the annular boss 12. Before the test, the dynamic balance of the entire device is adjusted by installing several first balance screws 6 on the annular boss 12.

[0030] Furthermore, refer to Figure 1As shown, the elastic pressing structure includes a gland 4 and an annular elastic member 3. The annular elastic member 3 is located between the gland 4 and the turbine disk 2. One end of the annular elastic member 3 is connected to the gland 4, and the other end is in surface contact with the turbine disk 2. During the test, the axial pressing of the end face at the center of the turbine disk 2 can be ensured through the deformation of the annular elastic member 3.

[0031] Further, the annular elastic member 3 includes a water-drop part and a U-shaped part. One end of the water-drop part is connected to the gland 4, the other end of the water-drop part is connected to one end of the U-shaped part, and the other end of the U-shaped part is in surface contact with the turbine disk 2.

[0032] Even further, as shown in Figure 3 The U-shaped part includes a first vertical wall ring surface 31, a first semi-circular ring surface 32, and a first inclined wall ring surface 33 that are connected in sequence. The first vertical wall ring surface 31 is connected to the water-drop part and is in surface contact with the turbine disk 2. The water-drop part includes a second semi-circular ring surface 34, a second inclined wall ring surface 35, and the first inclined wall ring surface 33, which are enclosed by the second semi-circular ring surface 34, the second inclined wall ring surface 35, and the first inclined wall ring surface 33. Preferably, the angles of the first inclined wall ring surface 33 and the second inclined wall ring surface 35 relative to the first vertical wall ring surface 31 are both acute angles, which can effectively increase the elastic deformation range of the annular elastic member 3.

[0033] When designing the circumferential profile of the annular elastic member 3, its design parameters include parameters such as thickness, axial length, radial length, and radius. By adjusting the magnitudes of several parameters, the axial compression amount of the annular elastic member 3 can be changed to ensure the axial pressing of the entire device during operation.

[0034] Preferably, as shown in Figure 3 and Figure 4 The water-drop part includes a horizontal wall ring surface 36 connected to the second inclined wall ring surface 35. On the surface of the gland 4 facing the annular elastic member 3, there is an annular snap ring 41. The horizontal wall ring surface 36 and the second inclined wall ring surface 35 form a clamping groove for positioning the annular snap ring 41, and the water-drop part is clamped to the gland 4. By designing the annular snap ring 41 on the gland 4, the outer cylindrical surface of the annular snap ring 41 can be used as a stop for the annular elastic member 3 and be clamped and positioned with it. The angle between the axial end face and the outer cylindrical surface of the annular snap ring 41 can be designed as an acute angle to avoid interference with the deformation of the annular elastic member 3.

[0035] Even more preferably, as shown in Figure 3 A second vertical wall ring surface 37 is connected to the horizontal wall ring surface 36. The second vertical wall ring surface 37 is in surface contact with the surface of the gland 4 facing the annular elastic member 3, and can cooperate with the annular snap ring 41 during operation to achieve the axial pressing of the gland 4.

[0036] Further, referring to Figure 1 and Figure 4 as shown, on the side of the gland 4 facing away from the annular elastic member 3, a plurality of connecting holes 42 are provided circumferentially. A second balance screw 7 is installed on the connecting hole 42. Preferably, a lock washer 8 is provided on the second balance screw 7. Before the test, the dynamic balance of the entire device is adjusted by installing several second balance screws 7 on the gland 4.

[0037] Furthermore, referring to Figure 2 and Figure 5 as shown, a plurality of limiting teeth 13 are evenly provided circumferentially at the tail end of the mandrel 10. A plurality of chucks 51 facing the axial center direction are evenly provided circumferentially on the locking member 5. One of the limiting teeth 13 is inserted between adjacent two of the chucks 51. By designing several chucks 51 in the circumferential direction of the locking member 5 and cooperating with the mandrel 10 for circumferential locking, this structure utilizes the characteristic of high pre-tightening force accuracy of the rotation angle method to ensure the accurate control of the pre-tightening force, and solves the problem of large vibration caused by unreliable positioning of the turbine disk 2 due to improper control of the pre-tightening force, enabling the smooth implementation of the rotation test of the turbine disk 2.

[0038] During implementation, through the elastoplastic calculation and analysis of the annular elastic member 3, the range of the pre-tightening torque of the locking member 5 (a fastening nut can be selected for use) can be determined, and then the range of the tightening rotation angle of the locking member 5 can be obtained according to the relationship between the pre-tightening torque and the rotation angle. By clamping the chuck 51 within the tightening rotation angle range of the locking member 5 between two adjacent limiting teeth 13 of the mandrel 10, the accurate control of the pre-tightening torque of the locking member 5 can be achieved, ensuring that the annular elastic member 3 has a certain elastic deformation within the working range.

[0039] The invention mainly aims at the turbine disk 2 with a disk-shaft integrated structure, and provides a rotation test device for connecting with a test equipment. First, by designing a positioning sleeve 11 at the connection between the adapter mandrel and the journal of the turbine disk to radially position the turbine disk 2, so as to simulate the extrusion force received by the outer cylindrical surface of the journal of the turbine disk under the engine state; secondly, by designing an elastic pressing structure and a locking member 5, the axial deformation generated by the turbine disk 2 under the centrifugal force is absorbed through its deformation, the elastic member is pressed and fixed by the gland, and the locking member 5 is sleeved on the mandrel 10 to apply a pressing force towards the turbine disk 2 direction to the elastic pressing structure, axially pressing the turbine disk 2 to make the axial positioning of the entire device reliable.

[0040] Obviously, the above are only the preferred embodiments of the present invention and are not used to limit the present invention. For those skilled in the art, various changes and modifications can be made to the embodiments of the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. A turbine disk rotation test device, characterized in that, Comprising: An adapter mandrel (1), the adapter mandrel (1) includes a mandrel (10), a positioning sleeve (11) is provided at the front end of the mandrel (10), an annular region (14) is formed between the outer peripheral wall of the mandrel (10) and the inner peripheral wall of the positioning sleeve (11), the mandrel (10) passes through the central hole of the turbine disk (2), and the outer cylindrical end of the journal of the turbine disk (2) is inserted into the annular region (14); An elastic pressing structure, the elastic pressing structure is located at the other end of the turbine disk (2) and cooperates with the adapter mandrel (1) to clamp the turbine disk (2); A locking member (5), the locking member (5) is arranged at the end of the mandrel (10), contacts and presses against the elastic pressing structure, and clamps and fixes the turbine disk (2).

2. The turbine disk rotation test device according to claim 1, wherein The adapter mandrel (1) further includes a dynamic balance structure, the dynamic balance structure includes a balance screw and an annular boss (12) located at the front end of the mandrel (10), and a plurality of threaded holes for installing the first balance screw (6) are evenly formed on the annular boss (12).

3. The turbine disk rotation test device according to claim 1, characterized in that, The elastic pressing structure includes a gland (4) and an annular elastic member (3), the annular elastic member (3) is located between the gland (4) and the turbine disk (2), one end of the annular elastic member (3) is connected to the gland (4), and the other end is in surface contact with the turbine disk (2).

4. The turbine disk rotation test device according to claim 3, characterized in that: The annular elastic member (3) includes a water droplet portion and a U-shaped portion, one end of the water droplet portion is connected to the gland (4), the other end of the water droplet portion is connected to one end of the U-shaped portion, and the other end of the U-shaped portion is in surface contact with the turbine disk (2).

5. The turbine disk rotation test device according to claim 4, characterized in that The U-shaped portion includes a first vertical wall ring surface (31), a first semi-circular ring surface (32) and a first inclined wall ring surface (33) connected in sequence, the first vertical wall ring surface (31) is connected to the water droplet portion, and the first vertical wall ring surface (31) is in surface contact with the turbine disk (2); The water droplet portion includes a second semi-circular ring surface (34), a second inclined wall ring surface (35) and the first inclined wall ring surface (33).

6. The turbine disk rotation test device according to claim 5, wherein, An annular clamping platform (41) is provided on the surface of the gland (4) facing the annular elastic member (3), the water droplet portion includes a horizontal wall ring surface (36) connected to the second inclined wall ring surface (35), and the horizontal wall ring surface (36) and the second inclined wall ring surface (35) form a clamping groove for positioning the annular clamping platform (41), and the water droplet portion is clamped to the gland (4).

7. The turbine disk rotation test device according to claim 3, characterized in that A plurality of connection holes (42) are provided on the surface of the gland (4) facing away from the annular elastic member (3) in the circumferential direction, and second balance screws (7) are installed on the connection holes (42).

8. The turbine disk rotation test device according to claim 1, characterized in that A plurality of limiting teeth (13) are evenly arranged on the circumferential direction of the tail end of the mandrel (10), a plurality of clamping heads (51) facing the axial center direction are evenly arranged on the circumferential direction of the locking member (5), and one of the limiting teeth (13) is inserted between adjacent two of the clamping heads (51).

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