Coupling structure and turbine engine
By using the circumferential fit of internal and external splines and the axial limiting structure, the problem of assembly collision between the low-pressure turbine shaft and the fan shaft in the gas turbine engine is solved, achieving reliable torque transmission and concentric positioning, and improving the reliability of the coupling structure.
Patent Information
- Application Number
- CN202520270943.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-02-19
- Publication Date
- 2025-11-25
- Estimated Expiration
- 2035-02-19
AI Technical Summary
In existing gas turbine engines, the coupling structure between high-speed rotating shafts is not reliable enough and is prone to collision damage, especially when the low-pressure turbine shaft and fan shaft are not aligned, leading to damage during assembly.
The coupling structure employs internal and external splines, combined with circumferential fit and axial limiting structure, to ensure that the low-pressure turbine shaft and fan shaft are on the same axis. Torque transmission is achieved through spline connection, and concentric positioning during assembly is ensured through rounded structure and limiting nut.
It effectively avoids collision damage between the low-pressure turbine shaft and the fan shaft during assembly, achieves reliable torque transmission and concentric positioning, and improves the reliability and stability of the coupling structure.
Smart Images
Figure CN223594775U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model relates to turbine engine field especially relates to a shaft coupling structure and turbine engine. BACKGROUND
[0002] The gas turbine engine usually includes a fan, a compressor, a combustion chamber and a turbine. Air enters the compressor for compression and is then sent to the combustion chamber to mix with fuel to ignite and produce high-temperature and high-pressure gas. The high-temperature and high-pressure gas expands in the turbine to drive the compressor and the fan. The high-pressure turbine and the low-pressure turbine drive the corresponding high-pressure compressor and the low-pressure compressor to rotate at high speed through the inner shaft and the outer shaft respectively.
[0003] The inner shaft and the outer shaft are high-speed rotating shafts, and the high-speed rotating shafts need to be coupled to transmit torque. However, the coupling structure between the high-speed rotating shafts involved in the gas turbine engine is not reliable enough, and the problem of collision damage between the high-speed rotating shafts is prone to occur. SUMMARY
[0004] The utility model discloses at least one purpose to provide a kind of coupling structure, realize the coupling between low-pressure turbine shaft and fan shaft, realize the torque transmission between the two, solve the problem of collision damage of low-pressure turbine shaft in the assembly process of low-pressure turbine shaft and fan shaft in turbine engine due to the misalignment of low-pressure turbine shaft and fan shaft.
[0005] The following gives a brief summary of one or more aspects to provide a basic understanding of these aspects. This summary is not an exhaustive overview of all contemplated aspects, and is neither intended to identify key or critical elements of all aspects nor to delineate the scope of any or all aspects. Its only purpose is to present some concepts of one or more aspects in a simplified form as a prelude to the more detailed description given later.
[0006] One of the utility model embodiments provides a kind of coupling structure, applied to turbine engine, coupling structure is used for the coupling between low-pressure turbine shaft and fan shaft;Coupling structure includes inner spline and outer spline, inner spline is sleeved on fan shaft, outer spline is sleeved on low-pressure turbine shaft, fan shaft is connected by the cooperation of inner spline and outer spline with low-pressure turbine shaft;Low-pressure turbine shaft has first axis, fan shaft has second axis, and circumferential cooperation is arranged between low-pressure turbine shaft and fan shaft, and the circumferential cooperation is used to make the first axis of low-pressure turbine shaft coincide with the second axis of fan shaft.
[0007] In some embodiments, the circumferential cooperation includes first circumferential cooperation and second circumferential cooperation, and the first circumferential cooperation and the second circumferential cooperation are respectively arranged on the two sides of the inner spline and the outer spline in the axial direction.
[0008] In some embodiments, the first and second circumferential fittings are gap fittings, and the outer spline has a diameter smaller than a maximum diameter of the first or second circumferential fitting.
[0009] In some embodiments, the first and second circumferential fittings are protruding structures extending in the circumferential direction, and the first and second circumferential fittings limit the relative position of the low-pressure turbine shaft and the fan shaft in the circumferential direction.
[0010] In some embodiments, the first circumferential fitting is arranged on the fan shaft and protrudes radially towards the low-pressure turbine shaft, and the second circumferential fitting is arranged on the low-pressure turbine shaft and protrudes radially towards the fan shaft.
[0011] In some embodiments, the first and second circumferential fittings are arranged on the fan shaft or the low-pressure turbine shaft and protrude in the circumferential direction towards the opposite side of the fan shaft or the low-pressure turbine shaft.
[0012] In some embodiments, the first and second circumferential fittings each have a protruding end, and the protruding end is a circular arc transition.
[0013] In some embodiments, during the spline fitting of the low-pressure turbine shaft and the fan shaft, a fillet structure is arranged along the length on the mutually close circumferential surfaces of the low-pressure turbine shaft and the fan shaft, and the fillet angle of the fillet structure is 0.5°-3°.
[0014] In some embodiments, an axial limiting structure is arranged between the low-pressure turbine shaft and the fan shaft, a limiting nut is arranged on the low-pressure turbine shaft, and the limiting nut is clamped in the axial limiting structure to limit the axial position of the low-pressure turbine shaft and the fan shaft.
[0015] One of the embodiments of the utility model further provides a turbine engine, which comprises the shaft coupling structure according to any one of the above embodiments.
[0016] The shaft coupling structure disclosed by the utility model enables the low-pressure turbine shaft and the fan shaft to be connected through splines, realizes torque transmission, and enables the fan shaft and the low-pressure turbine shaft to be centered through the circumferential fitting arranged therebetween in the circumferential direction. BRIEF DESCRIPTION OF DRAWINGS
[0017] The above features and advantages of the utility model can be better understood after reading the detailed description of the embodiments of the utility model in combination with the following drawings. In the drawings, various components are not necessarily drawn to scale, and components having similar related properties or features can have the same or similar reference numerals. Among them:
[0018] Figure 1 is a structural schematic view of a turbine engine according to some embodiments;
[0019] Figure 2is a schematic view of a coupling structure according to some embodiments;
[0020] Figure 3 is a schematic view of a fan shaft according to some embodiments;
[0021] Figure 4 is a schematic view of a low pressure turbine shaft according to some embodiments.
[0022] BRIEF DESCRIPTION OF DRAWINGS
[0023] turbine engine 10, fan 12, compressor 14, combustor 16, turbine 18, low pressure compressor 20, high pressure compressor 22, high pressure turbine 24, low pressure turbine 26, low pressure turbine shaft 28, high pressure turbine shaft 30, bearing system 32;
[0024] coupling structure 42, fan shaft 44, limit nut 48, first circumferential fit 50, spline structure 51, second circumferential fit 52;
[0025] rounded structures 50-1, 50-2, 50-3, 51-1, 51-2, 51-3, 51-4, 52-1, 52-2, 52-3, 52-4. DETAILED DESCRIPTION
[0026] The utility model will be described in detail below in combination with the drawings and specific embodiments. It should be noted that the aspects described below in combination with the drawings and specific embodiments are only exemplary and should not be understood as limiting the scope of protection of the utility model.
[0027] It can be understood that the technical terms involved in the description of the present specification, such as "center", "longitudinal", "transverse", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the embodiments, and do not indicate or imply that the devices or elements referred to must have a particular orientation or be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the scope of protection of the utility model.
[0028] It should be noted that the words "first", "second" and the like used in the text to limit the features are only for the convenience of distinguishing the corresponding features, and the above words have no special meaning unless otherwise stated, and therefore cannot be understood as limiting the scope of protection of the utility model.
[0029] In the description of the specification, it also needs to be explained that, unless otherwise explicitly specified or limited, the terms "mount", "connect", "connection" should be understood broadly, for example, it can be fixed connection, it can be integrally connected, or it can be detachably connected; it can be mechanical connection, or it can be electrical connection; it can be directly connected, or it can be indirectly connected through an intermediate medium, or the connection between two elements, etc. For those skilled in the art, the specific meaning of the above terms in the specification can be understood according to the specific circumstances.
[0030] The embodiment of the specification proposes a shaft coupling structure, which is applied to a turbine engine and is used for the connection between a low-pressure turbine shaft and a fan shaft. It should be noted that the shaft coupling structure is not only applicable to the connection between the low-pressure turbine shaft and the fan shaft, but also applicable to the connection between other high-speed rotating shafts in the turbine engine, and also applicable to the connection between high-speed rotating shafts in other devices. For the sake of understanding, the shaft coupling structure is taken as an example for the connection between the low-pressure turbine shaft and the fan shaft, and the shaft coupling structure can be applied to other high-speed rotating shafts in the turbine engine or other high-speed rotating shafts in other devices.
[0031] Figure 1 is a structural schematic diagram of a turbine engine according to some embodiments.
[0032] As shown in Figure 1 , the turbine engine 10 includes a fan 12, a compressor 14, a combustor 16 and a turbine 18. The fan 12 discharges air along a bypass path B, the compressor 14 is connected to the combustor 16 along a core engine path C, the compressor 14 includes a low-pressure compressor 20 and a high-pressure compressor 22, the low-pressure compressor 20 and the high-pressure compressor 22 compress air, the compressed air is mixed with fuel and burned in the combustor 16, generating high-temperature and high-pressure gas, and expanding in the turbine 18 to do work, driving the fan 12 and the compressor 14.
[0033] The turbine engine 10 further includes a low-pressure turbine shaft 28 and a high-pressure turbine shaft 30. The low-pressure turbine shaft 28 connects the fan 12, the low-pressure compressor 20 and the low-pressure turbine 26, and the high-pressure turbine shaft 30 connects the high-pressure compressor 22 and the high-pressure turbine 24. The low-pressure turbine shaft 28 and the high-pressure turbine shaft 30 are mounted on the engine center axis A by a bearing system 32, and the low-pressure turbine shaft 28 and the high-pressure turbine shaft 30 rotate around the center axis A. The axial direction in the specification refers to the direction along the center axis A, and the circumferential direction refers to the direction around the center axis A.
[0034] The shaft coupling structure 42 is used to connect the fan shaft 44 and the low-pressure turbine shaft 28.
[0035] Figure 2 is a schematic diagram of a shaft coupling structure according to some embodiments. As Figure 2As shown, the coupling structure 42 comprises a spline structure 51. The spline structure 51 comprises an inner spline and an outer spline, the inner spline is sleeved on the inner circumferential surface of the fan shaft 44, and the outer spline is sleeved on the outer circumferential surface of the low-pressure turbine shaft 28. After the fan shaft 44 and the low-pressure turbine shaft 28 are assembled, the inner spline and the outer spline are engaged, the fan shaft 44 and the low-pressure turbine shaft 28 are connected through the cooperation of the inner spline and the outer spline, the low-pressure turbine shaft 28 transmits torque through the cooperation of the inner spline and the outer spline, and drives the fan shaft 44 to rotate to drive the fan 12.
[0036] In some embodiments, the spline structure 51 is a cylindrical straight-tooth involute spline, and the spline pressure angles are all set to 30°. In some embodiments, one of the inner spline and the outer spline is set to a flat tooth root, and the other is set to a round tooth root.
[0037] In some embodiments, since the low-pressure turbine shaft 28 drives the fan shaft 44 through the spline structure 51, the low-pressure turbine shaft 28 and the fan shaft 44 need to be assembled on the same axis, that is, the central axis A. The low-pressure turbine shaft 28 has a first axis, the fan shaft 44 has a second axis, and a circumferential fit is provided between the low-pressure turbine shaft 28 and the fan shaft 44, which is used to make the first axis of the low-pressure turbine shaft 28 coincide with the second axis of the fan shaft 44. The low-pressure turbine shaft 28 and the fan shaft 44 are centered through the circumferential fit, so that the low-pressure turbine shaft 28 and the fan shaft 44 remain concentric during assembly and disassembly, so as to avoid collision between the low-pressure turbine shaft 28 and the fan shaft 44.
[0038] In some embodiments, the circumferential fit comprises a first circumferential fit 50 and a second circumferential fit 52, which are respectively arranged on the spline structure 51, that is, the inner spline and the outer spline, on both sides in the axial direction, so as to facilitate the centered installation of the spline structure 51. In some embodiments, considering the assembly of the fan shaft 44 and the low-pressure turbine shaft 28, the first circumferential fit 50 and the second circumferential fit 52 are both gap fits, and the maximum diameter of the outer spline is smaller than the maximum diameter of the first circumferential fit 50 or the second circumferential fit 52. In some embodiments, the gaps of the first circumferential fit 50 and the second circumferential fit 52 are the same.
[0039] In some embodiments, the first circumferential fit 50 and the second circumferential fit 52 are protruding structures extending in the circumferential direction, to limit the relative position of the low pressure turbine shaft 28 and the fan shaft 44 in the circumferential direction. The protruding structures protrude in the radial direction of the engine. In some embodiments, the first circumferential fit 50 and the second circumferential fit 52 can be provided on the outer circumferential surface of the low pressure turbine shaft 28, on the inner circumferential surface of the fan shaft 44, or on both the outer circumferential surface of the low pressure turbine shaft 28 and the inner circumferential surface of the fan shaft 44. The present specification takes the example of the first circumferential fit 50 and the second circumferential fit 52 being provided on the inner circumferential surface of the fan shaft 44 and the outer circumferential surface of the low pressure turbine shaft 28 respectively.
[0040] In some embodiments, referring to Figure 2 , the first circumferential fit 50 is provided on the fan shaft 44, protruding in the radial direction towards the low pressure turbine shaft 28, and the second circumferential fit 52 is provided on the low pressure turbine shaft 28, protruding in the radial direction towards the fan shaft 44. In some embodiments, the protruding heights of the first circumferential fit 50 and the second circumferential fit 52 in the radial direction are different. A recess in the radial direction is provided on the outer circumferential surface of the low pressure turbine shaft 28 corresponding to the first circumferential fit 50, to provide space for the fit of the first circumferential fit 50. A recess in the radial direction is provided on the inner circumferential surface of the fan shaft 44 corresponding to the second circumferential fit 52, to provide space for the fit of the second circumferential fit 52.
[0041] In some embodiments, axial limiting structures are provided between the low pressure turbine shaft 28 and the fan shaft 44. Specifically, as shown in Figure 2 , the axial limiting structures include a first limiting block extending in the radial direction of the fan shaft 44 on the low pressure turbine shaft 28, and a second limiting block extending in the radial direction of the low pressure turbine shaft 28 on the fan shaft 44, the first limiting block and the second limiting block are spaced apart in the axial direction, defining an axial spacing. A limiting nut 48 is provided on the low pressure turbine shaft 28, the limiting nut 48 is clamped in the axial limiting structures, that is, clamped in the axial spacing defined by the first limiting block and the second limiting block, to limit the axial position between the low pressure turbine shaft and the fan shaft, to determine the fit position of the shaft coupling structure in the axial direction. In the assembly process, the limiting nut 48 is first provided on the low pressure turbine shaft 28, the limiting nut 48 abuts against the first limiting block in the axial direction, and the fan shaft 44 is assembled with the low pressure turbine shaft 28 in the axial direction until the second limiting block abuts against the limiting nut 48, to determine the fit position of the shaft coupling structure in the axial direction.
[0042] Figure 3 is a structural schematic diagram of a fan shaft according to some embodiments. Figure 4 is a structural schematic diagram of a low pressure turbine shaft according to some embodiments.
[0043] In some embodiments, as Figure 3 andFigure 4 As shown, to avoid the protruding structures of the first and second circumferential fittings 50 and 52 from scratching the low-pressure turbine shaft 28 or the fan shaft 44 during assembly, the first and second circumferential fittings 50 and 52 each have a protruding end that is a circular arc transition. In some embodiments, there are edges on the outer circumferential surface of the low-pressure turbine shaft 28 and the inner circumferential surface of the fan shaft 44 due to the first and second circumferential fittings 50 and 52 and the relief recesses. During assembly, i.e., during the process of achieving the spline fitting of the low-pressure turbine shaft 28 and the fan shaft 44, the outer circumferential surface of the low-pressure turbine shaft 28 and the inner circumferential surface of the fan shaft 44 are close to each other, to avoid the edges from scratching the outer circumferential surface of the low-pressure turbine shaft 28 and the inner circumferential surface of the fan shaft 44, a rounding structure is arranged along the path of the outer circumferential surface of the low-pressure turbine shaft 28 and the inner circumferential surface of the fan shaft 44 that are close to each other, i.e., the edges on the outer circumferential surface of the low-pressure turbine shaft 28 and the inner circumferential surface of the fan shaft 44 that are close to each other are arranged as a rounding structure. Here, along the path refers to the outer circumferential surface of the low-pressure turbine shaft 28 and the inner circumferential surface of the fan shaft 44 that are close to each other on the assembly path of the low-pressure turbine shaft 28 and the fan shaft 44. The position of the rounding structure arranged on the inner circumferential surface of the fan shaft 44 is shown in FIG. 5. Figure 3 As shown, the rounding structures 50-1, 50-2, 51-1, 51-2, 52-1, and 52-2 are arranged along the path of the inner circumferential surface of the fan shaft 44. The position of the rounding structure arranged on the outer circumferential surface of the low-pressure turbine shaft 28 is shown in FIG. 6. Figure 4 As shown, the rounding structures 50-3, 51-3, 51-4, 52-3, and 52-4 are arranged along the path of the outer circumferential surface of the low-pressure turbine shaft 28.
[0044] The foregoing description has been set forth merely to illustrate the basic concepts of the present application, and it is apparent to those skilled in the art that the foregoing detailed disclosure is merely illustrative of the present application and is not intended to limit the present application to the disclosed embodiments. In addition, the order of the process elements and sequences, the use of numerical notations, or the use of other names in the present specification are not intended to limit the order of the processes and methods of the present application. Although some presently preferred embodiments of the present application have been discussed through various examples in the foregoing disclosure, it is understood that such details are merely by way of example and the appended claims are not limited to the disclosed embodiments, but rather intended to cover all modifications and equivalent arrangements that are within the spirit and scope of the present application.
Claims
1. A coupling structure used in a turbine engine, characterized in that, The coupling structure is used for connecting the low-pressure turbine shaft and the fan shaft; The coupling structure includes an internal spline and an external spline. The internal spline is sleeved on the fan shaft, and the external spline is sleeved on the low-pressure turbine shaft. The fan shaft and the low-pressure turbine shaft are connected by the engagement of the internal spline and the external spline. The low-pressure turbine shaft has a first axis, the fan shaft has a second axis, and a circumferential fit is provided between the low-pressure turbine shaft and the fan shaft. The circumferential fit is used to make the first axis of the low-pressure turbine shaft coincide with the second axis of the fan shaft.
2. The coupling structure according to claim 1, characterized in that, The circumferential fit includes a first circumferential fit and a second circumferential fit, which are respectively disposed on both sides of the internal spline and the external spline in the axial direction.
3. The coupling structure according to claim 2, characterized in that, The first circumferential fit and the second circumferential fit are clearance fits, and the major diameter of the external spline is smaller than the maximum diameter of the first circumferential fit or the second circumferential fit.
4. The coupling structure according to claim 2, characterized in that, The first circumferential fit and the second circumferential fit are protruding structures extending circumferentially, which restrict the relative position of the low-pressure turbine shaft and the fan shaft in the circumferential direction.
5. The coupling structure according to claim 4, characterized in that, The first circumferential fit is disposed on the fan shaft, and the first circumferential fit protrudes radially toward the low-pressure turbine shaft; The second circumferential fit is disposed on the low-pressure turbine shaft, and the second circumferential fit protrudes radially toward the fan shaft.
6. The coupling structure according to claim 4, characterized in that, The first circumferential fit and the second circumferential fit are disposed on the fan shaft or the low-pressure turbine shaft, and the first circumferential fit and the second circumferential fit protrude toward the opposite side of the fan shaft or the low-pressure turbine shaft along the circumferential direction.
7. The coupling structure according to claim 4, characterized in that, Both the first circumferential fit and the second circumferential fit have protruding ends, and the protruding ends are rounded.
8. The coupling structure according to claim 7, characterized in that, During the splined engagement between the low-pressure turbine shaft and the fan shaft, a rounded structure is provided along the circumferential surfaces of the low-pressure turbine shaft and the fan shaft that are close to each other, and the rounding angle of the rounded structure is 0.5° to 3°.
9. The coupling structure according to claim 1, characterized in that, An axial limiting structure is provided between the low-pressure turbine shaft and the fan shaft. A limiting nut is sleeved on the low-pressure turbine shaft and is engaged in the axial limiting structure to limit the axial position between the low-pressure turbine shaft and the fan shaft.
10. A turbine engine, characterized in that, It includes the coupling structure as described in any one of claims 1-9.