Aero-engine front turbine disk side wall and driving shaft front journal connecting structure

Abstract

The application belongs to the technical field of non-variable displacement engine design, and particularly relates to a front-stage turbine disc side wall and driving shaft front shaft neck connecting structure of an aero-engine, which comprises a front-stage turbine disc, a driving shaft, and a connecting part between the driving shaft front shaft neck and the front-stage turbine disc side wall.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of non-variable displacement engine design, and particularly relates to a connecting structure of a front turbine disc side wall and a front shaft neck of a driving shaft of an aero-engine. BACKGROUND

[0002] The connecting structure of the front turbine disc side wall and the front shaft neck of the driving shaft in the aero-engine is connected by a plurality of bolt fasteners, as shown in the figure, and the technical scheme has the following defects: Figure 1

[0003] 1) A large number of bolt fasteners are involved, the assembly process is complicated, and it is difficult to ensure the uniformity of the connection force everywhere;

[0004] 2) Bolt holes need to be provided on the front turbine disc side wall and the front shaft neck of the driving shaft, which will seriously weaken the strength reserve of the front turbine disc and the driving shaft;

[0005] 3) Under the conditions of high temperature, high pressure and high speed in the engine, the connection part is prone to looseness, which affects the safety of the engine operation;

[0006] 4) The corresponding mounting edge needs to be configured on the front turbine disc side wall and the front shaft neck of the driving shaft for the connection of the bolt, which increases the overall mass of the aero-engine.

[0007] The present application is proposed in view of the existence of the above technical defects.

[0008] It should be noted that the disclosure of the above background art is only used to assist in understanding the inventive concept and technical solutions of the present application, and it does not necessarily belong to the prior art of the present patent application. In the absence of explicit evidence that the above content has been disclosed on the filing date of the present application, the above background art should not be used to evaluate the novelty and inventiveness of the present application. SUMMARY

[0009] The purpose of the present application is to provide a connecting structure of a front turbine disc side wall and a front shaft neck of a driving shaft of an aero-engine to overcome or alleviate at least one aspect of the known technical defects.

[0010] The technical scheme of the present application is:

[0011] A connecting structure of a front turbine disc side wall and a front shaft neck of a driving shaft of an aero-engine, comprising:

[0012] a front turbine disc;

[0013] a driving shaft, the front shaft neck of which is integrally formed on the front turbine disc side wall;

[0014] The connecting part of the front shaft neck of the driving shaft and the front turbine disc side wall is 0.1-0.15 times the distance from the outer edge of the front turbine disc.​

[0015] According to at least one of the embodiments of the present application, in the aero-engine front turbine disk side wall and drive shaft front journal connecting structure, the outer side of the drive shaft front journal and the front turbine disk side wall are connected by a large round corner.

[0016] According to at least one of the embodiments of the present application, in the aero-engine front turbine disk side wall and drive shaft front journal connecting structure, the inner side of the drive shaft front journal and the front turbine disk side wall are connected by a small round corner.

[0017] According to at least one of the embodiments of the present application, in the aero-engine front turbine disk side wall and drive shaft front journal connecting structure, the angle between the inner side of the drive shaft front journal and the front turbine disk side wall is 45°-60°.

[0018] The present application has at least the following beneficial technical effects:

[0019] The present application provides an aero-engine front turbine disk side wall and drive shaft front journal connecting structure, in which the drive shaft front journal is integrally formed on the front turbine disk side wall, the connection force is uniform, the strength reserve of the front turbine disk and the drive shaft is not weakened, the connection part is not prone to loosen under the conditions of high temperature, high pressure and high speed in the engine, and the overall mass of the aero-engine is not additionally increased.

[0020] In the aero-engine front turbine disk side wall and drive shaft front journal connecting structure, the distance between the connecting part of the drive shaft front journal and the front turbine disk side wall and the edge of the front turbine disk center is 0.1-0.15 times the distance from the outer edge of the front turbine disk, that is, the connecting part of the drive shaft front journal and the front turbine disk side wall is close to the edge of the front turbine disk center relative to the outer edge of the front turbine disk. On the one hand, the radial dimension of the connecting part of the drive shaft front journal and the front turbine disk side wall can be reduced, the overall mass of the aero-engine can be reduced, the stress level can be reduced, the strength reserve can be improved, and on the other hand, the depth of the space formed between the inner side of the drive shaft front journal and the front turbine disk side wall can be reduced, and the integral machining of the drive shaft front journal and the front turbine disk side wall can be facilitated. BRIEF DESCRIPTION OF DRAWINGS

[0021] Figure 1 is a schematic diagram of the prior aero-engine front turbine disk side wall and drive shaft front journal connecting structure;

[0022] Figure 2 is a schematic diagram of the aero-engine front turbine disk side wall and drive shaft front journal connecting structure provided by the embodiments of the present application;

[0023] Wherein:

[0024] 1-front turbine disk; 2-drive shaft.

[0025] In order to better illustrate the present embodiment, some components in the drawings can be omitted, enlarged or reduced, and do not represent the actual size of the product. In addition, the drawings are only used for illustrative description and cannot be understood as a limitation on the present patent. DETAILED DESCRIPTION

[0026] In order to make the technical solutions of the present application and its advantages clearer, the technical solutions of the present application will be further clearly and completely described in detail below in combination with the drawings. It should be understood that the specific embodiments described herein are only part of the embodiments of the present application, which are only used to explain the present application, but not to limit the present application. It should be noted that, for the purpose of description, only parts related to the present application are shown in the drawings, and other related parts can be referred to the general design. In the case of no conflict, the embodiments in the present application and the technical features in the embodiments can be combined to obtain new embodiments.

[0027] In addition, unless otherwise defined, the technical terms or scientific terms used in the present application description should be the general meaning understood by the general technical personnel in the field to which the present application belongs. The words indicating the direction or position relationship such as "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer" and the like used in the present application description are only used to indicate the relative direction or position relationship, and not to imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation, and the relative position relationship may also change accordingly when the absolute position of the described object changes, therefore it cannot be understood as a limitation on the present application. The "first", "second", "third" and similar terms used in the present application description are only for the purpose of description, to distinguish different components, and cannot be understood as indicating or implying relative importance. The "one", "an" or "the" and similar terms used in the present application description should not be understood as an absolute limitation on the quantity, but should be understood as the existence of at least one. The "includes" or "contains" and similar terms used in the present application description mean that the elements or objects appearing before the word cover the elements or objects listed after the word and their equivalents, and do not exclude other elements or objects.

[0028] In addition, it should be further noted that, unless otherwise explicitly specified and limited, the "installation", "connection", "connection" and similar terms used in the present application description should be understood in a broad sense, for example, the connection can be a fixed connection, or a detachable connection, or an integral connection; can be a mechanical connection, or an electrical connection; can be directly connected, or indirectly connected through an intermediate medium, or the internal communication of two elements, and the person skilled in the art can understand the specific meaning of the present application according to the specific circumstances.

[0029] The following will be described in combination with the drawings Figures 1 to 2The application is further described in detail.

[0030] The application relates to an aero-engine front turbine disc side wall and driving shaft front journal connecting structure.

[0031] The aero-engine front turbine disc side wall and driving shaft front journal connecting structure comprises the following parts.

[0032] The driving shaft 2 is integrally formed on the side wall of the front turbine disc 1.

[0033] The connecting position of the driving shaft 2 front journal and the side wall of the front turbine disc 1 is 0.1-0.15 times the distance from the outer edge of the front turbine disc 1 to the edge of the disc core.

[0034] For the aero-engine front turbine disc side wall and driving shaft front journal connecting structure disclosed in the above embodiment, the driving shaft 2 front journal is integrally formed on the side wall of the front turbine disc 1, the connecting force is uniform, the strength reserve of the front turbine disc and the driving shaft is not weakened, the connecting position is not prone to loosening under the conditions of high temperature, high pressure and high speed in the engine, and the overall mass of the aero-engine is not additionally increased.

[0035] For the aero-engine front turbine disc side wall and driving shaft front journal connecting structure disclosed in the above embodiment, the connecting position of the driving shaft 2 front journal and the side wall of the front turbine disc 1 is 0.1-0.15 times the distance from the outer edge of the front turbine disc 1 to the edge of the disc core, that is, the connecting position of the driving shaft 2 front journal and the side wall of the front turbine disc 1 is close to the edge of the disc core relative to the outer edge of the front turbine disc 1, which can reduce the radial size of the connecting position of the driving shaft 2 front journal and the side wall of the front turbine disc 1, reduce the overall mass of the aero-engine, reduce the stress level, improve the strength reserve, and facilitate the integrated machining of the driving shaft 2 front journal and the side wall of the front turbine disc 1.

[0036] In some optional embodiments, the aero-engine front turbine disc side wall and driving shaft front journal connecting structure disclosed above is characterized in that the driving shaft 2 front journal outer side and the side wall of the front turbine disc 1 are connected through a large round corner.

[0037] For the aero-engine front turbine disc side wall and driving shaft front journal connecting structure disclosed in the above embodiment, the driving shaft 2 front journal outer side and the side wall of the front turbine disc 1 are connected through a large round corner, which can reduce the stress between the driving shaft 2 front journal outer side and the side wall of the front turbine disc 1, and ensure the bearing capacity of the connecting position between the driving shaft 2 front journal and the side wall of the front turbine disc 1.

[0038] In some alternative embodiments, the aero-engine front turbine disk side wall and drive shaft front journal connecting structure disclosed in the above embodiments is designed to have a small fillet transition between the inner side of the drive shaft 2 front journal and the side wall of the front turbine disk 1.

[0039] For the aero-engine front turbine disk side wall and drive shaft front journal connecting structure disclosed in the above embodiments, those skilled in the art can understand that the design of the small fillet transition between the inner side of the drive shaft 2 front journal and the side wall of the front turbine disk 1 can reduce the stress between the inner side of the drive shaft 2 front journal and the side wall of the front turbine disk 1, and ensure the load bearing capacity of the connecting part between the drive shaft 2 front journal and the side wall of the front turbine disk 1.

[0040] In some alternative embodiments, the aero-engine front turbine disk side wall and drive shaft front journal connecting structure disclosed in the above embodiments is designed to have an angle of 45°-60° between the inner side of the drive shaft 2 front journal and the side wall of the front turbine disk 1.

[0041] For the aero-engine front turbine disk side wall and drive shaft front journal connecting structure disclosed in the above embodiments, those skilled in the art can understand that the design of the angle of 45°-60° between the inner side of the drive shaft 2 front journal and the side wall of the front turbine disk 1, i.e., the design of the angle of 45°-60° between the inner side of the drive shaft 2 front journal and the side wall of the front turbine disk 1 with a larger included angle, can facilitate the integrated machining of the drive shaft 2 front journal and the side wall of the front turbine disk 1.

[0042] Each of the embodiments in the specification is described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the embodiments can be referred to each other.

[0043] So far, the technical solution of the present application has been described in combination with the preferred embodiments shown in the drawings. Those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments. Those skilled in the art can make equivalent changes or replacements to the related technical features without deviating from the principles of the present application, and the technical solutions after the changes or replacements will fall within the protection scope of the present application.

Claims

1. An aero-engine front turbine disk side wall and drive shaft forward journal connection structure, characterized in that, Comprise: The front turbine disk (1); Driving shaft (2), its front axle neck integral molding on the side wall of the front turbine disk (1); The connecting part of the front axle neck of the driving shaft (2) and the side wall of the front turbine disk (1) is 0.1-0.15 times the distance from the outer edge of the front turbine disk (1) to the edge of the disk core; The large round corner transition between the outer side of the front axle neck of the driving shaft (2) and the side wall of the front turbine disk (1); The small round corner transition between the inner side of the front axle neck of the driving shaft (2) and the side wall of the front turbine disk (1).

2. The connecting structure of the side wall of the front turbine disk and the front axle neck of the driving shaft of the aero-engine according to claim 1, wherein the angle between the inner side of the front axle neck of the driving shaft (2) and the side wall of the front turbine disk (1) is 45°-60°. ​

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