Aero-engine turbine disc and rotor blade connecting structure and assembling method thereof

Abstract

The application belongs to the field of non-variable displacement engine design, and particularly relates to an aero-engine turbine disc and rotor blade connecting structure and an assembling method thereof, wherein the aero-engine turbine disc and rotor blade connecting structure comprises: a turbine disc, which has a plurality of tenon grooves distributed in the circumferential direction on the outer edge, and has an annular groove and an annular protrusion on the side wall of one side; the annular protrusion is located on the inner side of the annular groove, and the outwardly bent part covers the annular groove; a plurality of rotor blades, which have tenon heads and lower edge plates at the roots; each tenon head is correspondingly clamped into a tenon groove; the lower edge plates are spliced with each other to form a whole ring structure; the whole ring structure has an annular clamping groove on the inner side; the annular clamping groove is located on the same side of the annular groove and the annular protrusion of the turbine disc; a blocking ring, which is clamped into the annular clamping groove on the outer edge, covers the gaps of the tenon grooves and the tenon heads, and has an annular folded edge on the inner edge; the annular folded edge part extends into the annular groove, and the part is inwardly bent and adheres to the inner side of the outwardly bent part of the annular protrusion.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of non-variable volume engine design, and particularly relates to an aero-engine turbine disc and rotor blade connecting structure and an assembling method thereof. BACKGROUND

[0002] In an aero-engine, rotor blades are connected to the outer edge of a turbine disc through a tenon and mortise matching structure. In order to realize axial positioning of the rotor blades and avoid leakage of the gas in the aero-engine from the gap between the tenon and mortise, front and rear retaining rings are designed to be connected to the two sides of the turbine disc, clamping the lower edge plate of the rotor blade in the axial direction, so as to realize axial positioning of the rotor blade on the turbine disc and cover the gap between the tenon and mortise, thereby avoiding leakage of the gas in the aero-engine from the gap between the tenon and mortise. This technical solution has the following defects:

[0003] The front and rear retaining rings need to be used in cooperation, which greatly increases the mass of the turbine rotor and makes the turbine disc bear a larger centrifugal load, thereby reducing the reliability.

[0004] The present application is proposed in view of the existence of the above technical defects.

[0005] It should be noted that the disclosure of the above background art content 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

[0006] The purpose of the present application is to provide an aero-engine turbine disc and rotor blade connecting structure and an assembling method thereof, so as to overcome or alleviate at least one aspect of the known technical defects.

[0007] The technical solution of the present application is:

[0008] In one aspect, an aero-engine turbine disc and rotor blade connecting structure is provided, comprising:

[0009] a turbine disc having a plurality of mortises distributed circumferentially on the outer edge thereof, and having an annular groove and an annular protrusion on the side wall thereof; the annular protrusion is located inside the annular groove and covers the annular groove with the outwardly bent portion;

[0010] a plurality of rotor blades having tenons and lower edge plates at the root portions thereof; each tenon is inserted into a corresponding mortise; the lower edge plates are spliced together to form a complete ring structure; the complete ring structure has an annular clamping groove inside; the annular clamping groove, the annular groove and the annular protrusion are located on the same side of the turbine disc;

[0011] The outer edge of the blocking ring is clamped into the annular clamping groove, covering the gaps between the mortises and tenons, and the inner edge has an annular folded edge; the annular folded edge part extends into the annular groove, and the part is inwardly bent and attached to the inner side of the part of the annular protrusion outwardly bent.

[0012] According to at least one embodiment of the present application, in the above-mentioned turbine disc and rotor blade connecting structure of the aero-engine, the bottom of the annular groove is arc-shaped.

[0013] According to at least one embodiment of the present application, in the above-mentioned turbine disc and rotor blade connecting structure of the aero-engine, the side of the blocking ring facing the turbine disc is recessed to form an annular cavity.

[0014] According to at least one embodiment of the present application, in the above-mentioned turbine disc and rotor blade connecting structure of the aero-engine, the blocking ring and the annular clamping groove, the annular groove, and the annular protrusion are located on the back side of the turbine disc.

[0015] In one aspect, a turbine disc and rotor blade connecting structure of an aero-engine is provided, which comprises:

[0016] The outer edge of the blocking ring is clamped into the annular clamping groove;

[0017] The tenon is clamped into the corresponding mortise, the part of the annular folded edge inwardly bent is pressed towards the turbine disc, so that the part is sunk into the annular groove, and the annular folded edge is loosened, so that the part of the annular folded edge inwardly bent is attached to the inner side of the part of the annular protrusion outwardly bent.

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

[0019] In one aspect, a turbine disc and rotor blade connecting structure of an aero-engine is provided, which comprises:

[0020] In the above-mentioned turbine disc and rotor blade connecting structure of the aero-engine, the part of the annular protrusion outwardly bent covering the annular groove is designed to protrude from the side wall of the turbine disc, forming the connecting structure of the blocking ring on the turbine disc, and the part of the annular folded edge inwardly bent on the inner edge of the blocking ring is designed to be attached to the inner side of the part of the annular protrusion outwardly bent, realizing the connection of the blocking ring on the turbine disc, which is convenient for assembling the blocking ring.

[0021] The other aspect provides an assembling method of a turbine disk and rotor blade connecting structure of an aero-engine, which is used to realize the assembling of the turbine disk and rotor blade connecting structure of the aero-engine, and the technical effects can be understood by referring to the technical effects of the turbine disk and rotor blade connecting structure of the aero-engine, which will not be described here. BRIEF DESCRIPTION OF DRAWINGS

[0022] Figure 1 Fig. 1 is a schematic diagram of a turbine disk and rotor blade connecting structure of an aero-engine provided by an embodiment of the present application;

[0023] Wherein:

[0024] 1-turbine disk; 2-annular protrusion; 3-rotor blade; 4-stop ring; 5-annular folded edge.

[0025] In order to better illustrate the embodiments, some components in the drawings may be omitted, enlarged or reduced, and do not represent the actual product size. In addition, the drawings are only used for illustrative description and cannot be understood as a limitation of the 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 below in conjunction with the drawings. It can be understood that the specific embodiments described here 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, in order to facilitate the description, only the parts related to the present application are shown in the drawings, and other related parts can be referred to the usual 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, technical terms or scientific terms used in the description of the present application shall be understood as the general meaning understood by those of ordinary skill in the art to which the present application belongs. The words "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer" and the like used in the description of the present application only indicate relative directions or positional relationships, and do not imply that the device or element must have a particular orientation, be constructed and operated in a particular orientation, and the relative positional 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 the like used in the description of the present application are only for descriptive purposes to distinguish different components, and cannot be understood as indicating or implying relative importance. The "one", "a" or "the" and the like used in the description of the present application should not be understood as an absolute limitation on the quantity, but should be understood as the presence of at least one. The "includes" or "contains" and the like used in the description of the present application means that the elements or objects appearing before the word are covered by the elements or objects listed after the word and their equivalents, without excluding other elements or objects.

[0028] In addition, it should be noted that, unless otherwise specified and limited, the "installation", "connection", "connection" and the like used in the description of the present application should be understood broadly, for example, the connection can be fixed connection, or detachable connection, or integral connection; can be mechanical connection, or electrical connection; can be directly connected, or indirectly connected through intermediate medium, or the connection between two elements, those 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 detail in combination with the accompanying drawings Figure 1 The present application will be further described in detail.

[0030] In one aspect, an aero-engine turbine disc and rotor blade connecting structure is provided, comprising:

[0031] The turbine disc 1 has a plurality of tenon grooves distributed circumferentially on the outer edge, and has an annular groove and an annular protrusion 2 on one side wall; the annular protrusion 2 is located inside the annular groove, and the outwardly bent part covers the annular groove;

[0032] A plurality of rotor blades 3 have tenon heads and lower edge plates at the roots; each tenon head corresponds to a tenon groove; each lower edge plate is spliced to form a whole ring structure; the inside of the whole ring structure has an annular clamping groove; the annular clamping groove, the annular groove and the annular protrusion 2 are located on the same side of the turbine disc 1;

[0033] The outer edge of the blocking ring 4 is clamped into the annular clamping groove, covering the gap between the tenon and the mortise, and the inner edge has an annular folded edge 5; the annular folded edge 5 partially extends into the annular groove, and the inwardly bent part is attached to the inner side of the outwardly bent part of the annular protrusion 2.

[0034] For the aero-engine turbine disc and rotor blade connection structure disclosed in the above embodiments, those skilled in the art can understand that a single blocking ring 4 is matched with the annular groove, the annular protrusion 2 provided on the turbine disc 1, and the annular clamping groove provided in the whole ring structure formed by the lower edge plates of the respective rotor blades 3, to realize the axial positioning of the rotor blade 3 on the turbine disc 1 and avoid the leakage of the gas in the aero-engine from the gap between the tenon and the mortise, the structure is simple, the mass of the turbine rotor is not greatly increased, the centrifugal load borne by the turbine disc 1 is reduced, and the reliability is high.

[0035] For the aero-engine turbine disc and rotor blade connection structure disclosed in the above embodiments, those skilled in the art can further understand that the outwardly bent part of the annular protrusion 2 protruding from the side wall of the turbine disc 1 covers the annular groove to form the connection structure of the blocking ring 4 on the turbine disc 1, and the inwardly bent part of the annular folded edge 5 on the inner edge of the blocking ring 4 is attached to the inner side of the outwardly bent part of the annular protrusion 2, to realize the connection of the blocking ring 4 on the turbine disc 1, which is convenient for assembling the blocking ring 4, and the specific assembly process can be referred to the assembly method of the aero-engine turbine disc and rotor blade connection structure disclosed in the present application.

[0036] In some optional embodiments, in the aero-engine turbine disc and rotor blade connection structure, the bottom of the annular groove is arc-shaped to reduce the local stress on the turbine disc 1, and the inwardly bent part of the annular folded edge 5 on the inner edge of the blocking ring 4 can be designed to be of a suitable shape.

[0037] In some optional embodiments, in the aero-engine turbine disc and rotor blade connection structure, the side of the blocking ring 4 facing the turbine disc 1 is recessed to form an annular cavity, which can further reduce the mass of the turbine rotor, appropriately reduce the rigidity of the blocking ring 4, and separate the main part of the blocking ring 4 from the turbine disc 1, so that the inwardly bent part of the annular folded edge 5 is easily deformed, thereby facilitating the assembly of the blocking ring 4.

[0038] In some optional embodiments, in the aero-engine turbine disc and rotor blade connection structure, the blocking ring 4 and the annular clamping groove, the annular groove, and the annular protrusion 2 are located on the back side of the turbine disc 1, to avoid adversely affecting the aerodynamic performance of the aero-engine.

[0039] On the other hand, an assembly method of an aero-engine turbine disc and rotor blade connection structure is provided, comprising:

[0040] The outer edge of the blocking ring 4 is clamped into the annular clamping groove;

[0041] The tenon is clamped into the corresponding mortise, the annular flange 5 is pressed towards the turbine disc 1, the inner bending part of the annular flange 5 is made to sink into the annular groove, the annular flange 5 is loosened, and the inner bending part of the annular flange 5 is abutted to the inner side of the outer bending part of the annular protrusion 2.

[0042] The assembling method of the turbine disc and the rotor blade connecting structure of the aero-engine disclosed in the above embodiment is used to realize the assembling of the turbine disc and the rotor blade connecting structure of the aero-engine, the description is relatively simple, the specific related parts can be referred to the related description of the turbine disc and the rotor blade connecting structure of the aero-engine, and the technical effects can be referred to the technical effects of the turbine disc and the rotor blade connecting structure of the aero-engine, which will not be described here.

[0043] The embodiments in the specification are described in a progressive manner, each embodiment focuses on the difference from other embodiments, and the same and similar parts between the embodiments can be referred to each other.

[0044] So far, the technical scheme of the application has been described in combination with the preferred embodiments shown in the drawings, and those skilled in the art should understand that the protection scope of the application is obviously not limited to these specific embodiments, and those skilled in the art can make equivalent changes or replacements to the related technical features without departing from the principles of the application, and the technical scheme after the changes or replacements will fall within the protection scope of the application.

Claims

1. An assembling method of a turbine disk and rotor blade connecting structure of an aero-engine, for assembling the turbine disk and rotor blade connecting structure of the aero-engine, the turbine disk and rotor blade connecting structure comprising: a turbine disk (1) having a plurality of tenon grooves distributed circumferentially on an outer edge thereof, and having an annular groove, an annular protrusion (2) on a side wall thereof; the annular protrusion (2) is located inside the annular groove, and an outwardly bent portion thereof covers the annular groove; a plurality of rotor blades (3) having tenons at roots thereof, and having lower edge plates; each tenon is inserted into a corresponding tenon groove; the lower edge plates are spliced together to form a complete annular structure; the complete annular structure has an annular clamping groove inside thereof; the annular clamping groove is located on the same side of the turbine disk (1) as the annular groove and the annular protrusion (2); a retaining ring (4) having an outer edge inserted into the annular clamping groove, covering the gaps between the tenon grooves and the tenons, and having an annular folded edge (5) at an inner edge thereof; the annular folded edge (5) partially extends into the annular groove, and a portion thereof is bent inwardly and abuts against an inner side of an outwardly bent portion of the annular protrusion (2); the assembling method of the turbine disk and rotor blade connecting structure of the aero-engine comprises: inserting the outer edge of the retaining ring (4) into the annular clamping groove; inserting each tenon into a corresponding tenon groove, and pressing an inwardly bent portion of the annular folded edge (5) towards the turbine disk (1) so that the inwardly bent portion is inserted into the annular groove, then releasing the annular folded edge (5) so that the inwardly bent portion abuts against an inner side of an outwardly bent portion of the annular protrusion (2). In the turbine disk and rotor blade connecting structure of the aero-engine, a bottom of the annular groove is arc-shaped. In the turbine disk and rotor blade connecting structure of the aero-engine, a side of the retaining ring (4) facing the turbine disk (1) is recessed to form an annular recess. In the turbine disk and rotor blade connecting structure of the aero-engine, the retaining ring (4), the annular clamping groove, the annular groove, and the annular protrusion (2) are located at a rear side of the turbine disk (1). ​ 2. The method of assembling an aeroengine turbine disk and rotor blade connection structure of claim 1, wherein, ​ 3. The method of assembling an aircraft engine turbine disk and rotor blade connection structure of claim 1, wherein, ​ ​ 4. The method of assembling an aircraft engine turbine disk and rotor blade connection structure of claim 1, wherein, ​ ​

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