An assembly structure and method for a hollow turbine shaft and an axial ventilation pipe of an aircraft engine

Abstract

The present application belongs to the technical field of assembly design of hollow turbine shafts and axial ventilation pipes of aircraft engines, and specifically relates to an assembly structure and method of hollow turbine shafts and axial ventilation pipes of aircraft engines, wherein the assembly structure includes: a hollow turbine shaft; an axial ventilation pipe, which is axially arranged in the hollow turbine shaft; a bushing, which is sleeved on the axial ventilation pipe, and its outer wall has a guide protrusion; a support ring, which has a notch and is sleeved on the bushing, and its inner wall has a guide groove; the guide protrusion is stuck in the guide groove, and the top of the guide protrusion is beveled with the bottom wall of the guide groove; a nut, which is screwed on the bushing and pressed tightly against the support ring to expand the support ring and support it in the hollow turbine shaft.

Description

Technical Field

[0001] The present application belongs to the technical field of assembly design of a hollow turbine shaft and an axial ventilation pipe of an aircraft engine, and specifically relates to an assembly structure and method of a hollow turbine shaft and an axial ventilation pipe of an aircraft engine. Background Art

[0002] An axial ventilation pipe is led out from the hollow turbine shaft of an aircraft engine, and a support ring is used to support the axial ventilation pipe in the hollow turbine shaft. This technical solution has the following defects:

[0003] 1) The hollow turbine shaft is slender. To facilitate the installation of the support ring inside it, the hollow turbine shaft is designed to have the same diameter at all locations, resulting in low strength.

[0004] 2) During the process of installing the support ring into the hollow turbine shaft, the support ring is prone to axial movement or circumferential movement along the hollow turbine shaft, thereby scratching the inner wall surface of the hollow turbine shaft.

[0005] This application is proposed in view of the above-mentioned technical defects.

[0006] It should be noted that the disclosure of the above background technology content is only used to assist in understanding the inventive concept and technical solution of the present invention, and it does not necessarily belong to the prior art of this patent application. In the absence of clear evidence that the above content has been disclosed on the filing date of this application, the above background technology should not be used to evaluate the novelty and creativity of this application. Summary of the Invention

[0007] The purpose of the present application is to provide an assembly structure and method for a hollow turbine shaft and an axial ventilation pipe of an aircraft engine, so as to overcome or alleviate at least one of the technical defects of the known ones.

[0008] The technical solution of this application is:

[0009] On the one hand, an assembly structure of a hollow turbine shaft and an axial ventilation pipe of an aircraft engine is provided, comprising:

[0010] Hollow turbine shaft;

[0011] An axial ventilation pipe is arranged axially inside the hollow turbine shaft;

[0012] The bushing is sleeved on the axial ventilation pipe and has a guide protrusion on its outer wall;

[0013] The support ring has a notch and is sleeved on the bushing. The inner wall of the support ring has a guide groove. The guide protrusion is stuck in the guide groove, and the top of the guide protrusion is inclined with the bottom wall of the guide groove.

[0014] The nut is screwed onto the bushing and tightened onto the support ring, causing the support ring to expand and be supported in the hollow turbine shaft.

[0015] According to at least one embodiment of the present application, in the above-mentioned assembly structure of the hollow turbine shaft and the axial ventilation pipe of the aircraft engine, there are multiple guide protrusions and their corresponding guide grooves, which are distributed along the circumferential direction.

[0016] According to at least one embodiment of the present application, in the above-mentioned assembly structure of the hollow turbine shaft and the axial ventilation pipe of the aircraft engine, the bushing is located at one end of the nut and has a serrated shape;

[0017] The end of the nut facing away from the support ring is serrated.

[0018] According to at least one embodiment of the present application, in the above-mentioned assembly structure of the hollow turbine shaft and the axial ventilation pipe of the aircraft engine, the radial dimension of the middle portion of the hollow turbine shaft is greater than the dimension at both ends;

[0019] The support ring has a pair of first cutting edges parallel to each other;

[0020] L 2 +H 2 <4R 2 ;

[0021] in,

[0022] L is the distance between the two first cutting edges;

[0023] H is the axial dimension of the support ring;

[0024] R is the radius of the inner wall of one end of the hollow turbine shaft.

[0025] According to at least one embodiment of the present application, in the above-mentioned aircraft engine hollow turbine shaft and axial ventilation pipe assembly structure, the support ring has a pair of mutually parallel second cut edges, and the pair of second cut edges are perpendicular to the two first cut edges.

[0026] According to at least one embodiment of the present application, in the above-mentioned assembly structure of the hollow turbine shaft and the axial ventilation pipe of the aircraft engine, the outer walls of both ends of the axial ventilation pipe have annular bosses, and the two annular bosses are supported in the hollow turbine shaft;

[0027] The outer wall of the middle part of the axial ventilation pipe is provided with an annular boss, and the annular boss is supported in the bushing.

[0028] According to at least one embodiment of the present application, in the above-mentioned assembly structure of the hollow turbine shaft and the axial ventilation pipe of the aircraft engine, the three annular bosses are provided with annular sealing grooves;

[0029] The assembly structure of the hollow turbine shaft and the axial ventilation pipe of the aircraft engine also includes:

[0030] There are three sealing rings, each of which is correspondingly arranged in an annular sealing groove.

[0031] Another aspect provides a method for assembling a hollow turbine shaft of an aircraft engine and an axial vent pipe, comprising:

[0032] Slip the bushing onto the support ring and screw the nut onto the bushing;

[0033] The two first cutting edges of the support ring are arranged parallel to the axis of the hollow turbine shaft, and the support ring is placed into the hollow turbine shaft from the corresponding ends thereof, and the axis of the support ring is adjusted so that the axis of the support ring is parallel to the axis of the hollow turbine shaft;

[0034] Press the end of the support ring facing away from the nut, clamp the serrations on the bushing and nut, turn the nut to tighten it against the support ring, so that the support ring expands and is supported in the hollow turbine shaft;

[0035] Arrange the three sealing rings in the corresponding annular sealing grooves;

[0036] The axial ventilation pipe is arranged axially in the hollow turbine shaft so that the annular bosses on the outer walls at both ends of the axial ventilation pipe are supported in the hollow turbine shaft, and the annular boss on the outer wall of the middle part is supported in the bushing. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] Figure 1 This is a schematic diagram of an assembly structure of a hollow turbine shaft and an axial ventilation pipe of an aircraft engine provided by an embodiment of the present application;

[0038] Figure 2 is a schematic diagram of a hollow turbine shaft provided in an embodiment of the present application;

[0039] Figure 3 is a schematic diagram of a bushing provided in an embodiment of the present application;

[0040] Figure 4 yes Figure 3 A-direction view;

[0041] Figure 5 is a schematic diagram of a support ring provided in an embodiment of the present application;

[0042] Figure 6 yes Figure 5 BB cross-sectional view;

[0043] Figure 7 is a schematic diagram of a nut provided in an embodiment of the present application;

[0044] in:

[0045] 1-hollow turbine shaft; 2-axial vent pipe; 3-bushing; 4-support ring; 5-nut; 6-sealing ring;

[0046] L is the distance between the two first cutting edges;

[0047] H is the axial dimension of the support ring;

[0048] R is the radius of the inner wall of one end of the hollow turbine shaft.

[0049] In order to better illustrate this embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be understood as limitations on this patent. DETAILED DESCRIPTION

[0050] To make the technical solution and its advantages of the present application clearer, the technical solution of the present application will be described in further detail below in conjunction with the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of the present application and are only used to explain the present application, not to limit the present application. It should be noted that, for ease of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design. In the absence of conflict, the embodiments of the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0051] In addition, unless otherwise defined, the technical or scientific terms used in the description of this application should have the ordinary meanings understood by those of ordinary skill in the art to which this application belongs. The words "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer" used in the description of this application are only used to indicate relative directions or positional relationships, and do not imply that the device or component must have a specific orientation, be constructed, or operate in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. Therefore, they should not be understood as limitations on this application. The words "first," "second," "third," and similar terms used in the description of this application are used only for descriptive purposes to distinguish different components and should not be understood to indicate or imply relative importance. The words "one," "an," or "the" used in the description of this application should not be understood as absolute limitations on quantity, but should be understood as meaning the presence of at least one. The words "include" or "comprises" used in the description of this application mean that the element or object listed before the word includes the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0052] In addition, it should be noted that, unless otherwise clearly stipulated and limited, the words "install", "connect", "connect" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, an indirect connection through an intermediate medium, or a connection between two components. Technical personnel in the field can understand their specific meanings in this application according to the specific circumstances.

[0053] The following is combined with Figures 1 to 7 This application is described in further detail.

[0054] On the one hand, an assembly structure of a hollow turbine shaft and an axial ventilation pipe of an aircraft engine is provided, comprising:

[0055] Hollow turbine shaft 1;

[0056] The axial ventilation pipe 2 is arranged axially inside the hollow turbine shaft 1;

[0057] The bushing 3 is sleeved on the axial ventilation pipe 2, and its outer wall has a guide protrusion;

[0058] The support ring 4 has a notch and is sleeved on the bushing 3. The inner wall of the support ring 4 has a guide groove. The guide protrusion is stuck in the guide groove, and the top of the guide protrusion is inclined with the bottom wall of the guide groove.

[0059] The nut 5 is screwed onto the bushing 3 and is pressed against the support ring 4 , causing the support ring 4 to expand and be supported in the hollow turbine shaft 1 .

[0060] As for the assembly structure of the hollow turbine shaft and the axial ventilation pipe of the aircraft engine disclosed in the above embodiment, it can be understood by those skilled in the art that its design supports the axial ventilation pipe 2 in the hollow turbine shaft 1 with the combined structure of the bushing 3, the support ring 4 and the nut 5. During assembly, the end of the support ring 4 facing away from the nut 5 can be pressed to clamp the bushing 3 and limit the circumferential rotation of the bushing 3. The nut 5 is rotated to make the bushing 3 move axially relative to the support ring 4 along the hollow turbine shaft 1. The nut 5 is tightened on the support ring 4 to make the support ring 4 expand, thereby supporting the hollow turbine shaft 1. In the shaft 1, during this process, since the end of the support ring 4 facing away from the nut 5 is resisted, the support ring 4 can be prevented from moving axially along the hollow turbine shaft 1. In addition, since the bushing 3 is restricted from circumferential rotation, under the restriction of the guide groove and the guide protrusion, the support ring 4 will not rotate circumferentially along the hollow turbine shaft 1, thereby avoiding scratching the inner wall surface of the hollow turbine shaft 1. For the assembly process of the assembly structure of the hollow turbine shaft of the aircraft engine and the axial breather pipe, specific reference can be made to the assembly method of the hollow turbine shaft of the aircraft engine and the axial breather pipe disclosed in the embodiment of the present application.

[0061] In some optional embodiments, in the above-mentioned assembly structure of the hollow turbine shaft of the aircraft engine and the axial ventilation pipe, there are multiple guide protrusions and their corresponding guide grooves, which are distributed along the circumferential direction.

[0062] In some optional embodiments, in the above-mentioned assembly structure of the hollow turbine shaft and the axial vent pipe of the aircraft engine, the bushing 3 is located at one end of the nut 5 and has a serrated shape, so as to facilitate clamping the bushing 3 at this end during structural assembly, thereby limiting the bushing 3 from rotating circumferentially along the hollow turbine shaft 1 and preventing the support ring 4 from rotating circumferentially along the hollow turbine shaft 1;

[0063] One end of the nut 5 facing away from the support ring 4 is serrated, so that the nut 5 can be easily clamped at this end and rotated during structural assembly.

[0064] In some optional embodiments, in the above-mentioned assembly structure of the hollow turbine shaft and the axial vent pipe of the aircraft engine, the radial dimension of the middle portion of the hollow turbine shaft 1 is larger than the dimensions at both ends. The dimensions of the two ends of the hollow turbine shaft 1 are determined by the assembly boundaries of the hollow turbine shaft 1 at both ends in the aircraft engine. Designing the radial dimension of the middle portion of the hollow turbine shaft 1 to be larger than the dimensions at both ends can enhance the strength of the hollow turbine 1.

[0065] The support ring 4 has a pair of first cutting edges parallel to each other;

[0066] L 2 +H 2 <4R 2 ; Wherein, L is the distance between the two first cut edges; H is the axial dimension of the support ring 4; R is the radius of the inner wall of one end of the hollow turbine shaft 1, thereby ensuring that when the structure is assembled, the support ring 4 can at least be placed into the hollow turbine shaft 1 from that end of the hollow turbine shaft 1. The specific process can refer to the method for assembling the hollow turbine shaft and the axial ventilation pipe of an aircraft engine disclosed in the embodiment of the present application.

[0067] In some optional embodiments, in the above-mentioned assembly structure of the hollow turbine shaft and axial vent pipe of the aircraft engine, the support ring 4 has a pair of second cut edges parallel to each other, and the pair of second cut edges are perpendicular to the two first cut edges to facilitate the alignment of the bushing 3, the support ring 4, and the nut 5 in the hollow turbine shaft 1. The specific process can refer to the assembly method of the hollow turbine shaft and axial vent pipe of the aircraft engine disclosed in the embodiment of the present application.

[0068] In some optional embodiments, in the above-mentioned assembly structure of the hollow turbine shaft and the axial ventilation pipe of the aircraft engine, the outer walls of both ends of the axial ventilation pipe 2 have annular bosses, and the two annular bosses are supported in the hollow turbine shaft 1;

[0069] The outer wall of the middle portion of the axial ventilation tube 2 has an annular boss, which is supported in the bushing 3 .

[0070] In some optional embodiments, in the above-mentioned assembly structure of the hollow turbine shaft and the axial ventilation pipe of the aircraft engine, the three annular bosses are provided with annular sealing grooves;

[0071] The assembly structure of the hollow turbine shaft and the axial ventilation pipe of the aircraft engine also includes:

[0072] There are three sealing rings 6, and each sealing ring 6 is correspondingly arranged in an annular sealing groove.

[0073] Another aspect provides a method for assembling a hollow turbine shaft of an aircraft engine and an axial vent pipe, comprising:

[0074] Sleeve the bushing 3 onto the support ring 4, and screw the nut 5 onto the bushing 3;

[0075] Set the two first cutting edges of the support ring 4 parallel to the axis of the hollow turbine shaft 1, place the support ring 4 into the hollow turbine shaft 1 from the corresponding end of the hollow turbine shaft 1, and adjust the support ring 4 so that the axis is parallel to the axis of the hollow turbine shaft 1, that is, align the bushing 3, support ring 4, and nut 5 in the hollow turbine shaft 1;

[0076] Press the end of the support ring 4 facing away from the nut 5, clamp the serrations on the bushing 3 and the nut 5, and turn the nut 5 to tighten it against the support ring 4, so that the support ring 4 expands and is supported in the hollow turbine shaft 1;

[0077] The three sealing rings 6 are arranged in the corresponding annular sealing grooves;

[0078] The axial ventilation pipe 2 is axially arranged in the hollow turbine shaft 1 so that the annular bosses on the outer walls at both ends of the axial ventilation pipe 2 are supported in the hollow turbine shaft 1 and the annular bosses on the outer wall of the middle part are supported in the bushing 3.

[0079] To facilitate the assembly of the aircraft engine hollow turbine shaft and axial ventilation tube assembly structure disclosed in the above embodiment, technicians in the field can refer to the aircraft engine hollow turbine shaft and axial ventilation tube assembly method disclosed in the above embodiment to design or select corresponding assembly tools.

[0080] The assembly method of the hollow turbine shaft and axial ventilation tube of an aircraft engine disclosed in the above embodiment is used to realize the assembly of the assembly structure of the hollow turbine shaft and axial ventilation tube of an aircraft engine disclosed in the above embodiment. The description is relatively simple. For specific related matters, please refer to the relevant description of the assembly structure of the hollow turbine shaft and axial ventilation tube of an aircraft engine. Its technical effects can also refer to the technical effects of the relevant parts of the assembly structure of the hollow turbine shaft and axial ventilation tube of an aircraft engine, which will not be repeated here.

[0081] The various embodiments in the specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to in detail.

[0082] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or replacements to the relevant technical features, and the technical solutions after these changes or replacements will fall within the scope of protection of the present application.

Claims

1. A method for assembling a hollow turbine shaft and an axial ventilation pipe of an aircraft engine, characterized in that: The invention is based on an assembly structure of a hollow turbine shaft and an axial ventilation pipe of an aircraft engine, and the assembly structure of the hollow turbine shaft and the axial ventilation pipe of the aircraft engine comprises: Hollow turbine shaft (1); An axial ventilation pipe (2) is axially arranged inside the hollow turbine shaft (1); A bushing (3) is sleeved on the axial ventilation pipe (2), and its outer wall has a guide protrusion; The support ring (4) has a notch thereon and is sleeved on the bushing (3), and the inner wall of the support ring (4) has a guide groove; the guide protrusion is stuck in the guide groove, and the top of the guide protrusion is beveled with the bottom wall of the guide groove; A nut (5) is screwed onto the bushing (3) and is pressed against the support ring (4), so that the support ring (4) expands and is supported within the hollow turbine shaft (1); The radial dimension of the middle portion of the hollow turbine shaft (1) is larger than that of the two ends; The support ring (4) has a pair of first cutting edges parallel to each other; L 2 +H 2 <4R 2 ; in, L is the distance between the two first cutting edges; H is the axial dimension of the support ring (4); R is the radius of the inner wall of one end of the hollow turbine shaft (1); There are multiple guide protrusions and corresponding guide grooves, distributed along the circumferential direction; The bushing (3) is located at one end of the nut (5) and is serrated; The end of the nut (5) facing away from the support ring (4) is serrated; The outer walls of both ends of the axial ventilation pipe (2) are provided with annular bosses, and the two annular bosses are supported inside the hollow turbine shaft (1); The outer wall of the middle portion of the axial ventilation pipe (2) has an annular boss, and the annular boss is supported in the bushing (3); The three annular bosses are provided with annular sealing grooves; The aero-engine hollow turbine shaft and axial ventilation pipe assembly structure further includes: Three sealing rings (6), each of the sealing rings (6) being correspondingly arranged in one of the annular sealing grooves; The method for assembling the hollow turbine shaft of an aero-engine and the axial ventilation pipe comprises: Sleeve the bushing (3) onto the support ring (4), and screw the nut (5) onto the bushing (3); The two first cutting edges of the support ring (4) are arranged parallel to the axis of the hollow turbine shaft (1), and the corresponding ends of the hollow turbine shaft (1) are placed into the hollow turbine shaft (1), and the axis of the support ring (4) is adjusted so that the axis is parallel to the axis of the hollow turbine shaft (1); Press against the end of the support ring (4) facing away from the nut (5), clamp the bushing (3) and the serrations on the nut (5), rotate the nut (5) to press against the support ring (4), so that the support ring (4) expands and is supported in the hollow turbine shaft (1); Arranging three sealing rings (6) in corresponding annular sealing grooves; The axial ventilation pipe (2) is axially arranged in the hollow turbine shaft (1), so that the annular bosses on the outer walls at both ends of the axial ventilation pipe (2) are supported in the hollow turbine shaft (1), and the annular boss on the outer wall of the middle portion is supported in the bushing (3).

2. The method for assembling a hollow turbine shaft and an axial ventilation pipe of an aircraft engine according to claim 1, characterized in that: In the assembly structure of the hollow turbine shaft and the axial ventilation pipe of the aircraft engine, the support ring (4) has a pair of second cut edges that are parallel to each other, and the pair of second cut edges are perpendicular to the two first cut edges.

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