A serial rotor blade of a compressor in an aero-engine and an assembling method thereof

Abstract

The application relates to an assembled compressor tandem rotor blade in an aero-engine and an assembling method, wherein the assembled compressor tandem rotor blade in the aero-engine comprises a rotor disc, an annular clamping groove is formed in the outer edge rear side part of the rotor disc, and a pin hole is communicated with the annular clamping groove; a gap is formed in the rear side wall of the annular clamping groove; limit grooves are formed on the two sides of the gap; front-row rotor blades are formed in the outer edge front side part of the rotor disc in the circumferential direction; rear-row rotor blades have lower edge plates; the lower edge plates are sequentially clamped into the annular clamping groove through the gap, and the lower edge plates are abutted against each other in the circumferential direction, wherein the lower edge plate opposite to the gap has an axial stop hole and a circumferential stop protrusion; the circumferential stop protrusion is clamped in the gap, and the circumferential stop protrusion has radial stop lugs on the two sides; the two radial stop lugs are clamped into the two limit grooves; and an axial stop pin is arranged in the pin hole and inserted into the axial stop hole.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of assembly design of aero-engine mid-assembly type compressor tandem rotor blades, and particularly relates to an aero-engine mid-assembly type compressor tandem rotor blade and an assembly method. BACKGROUND

[0002] In the aero-engine mid-assembly type compressor tandem rotor technology, the rotor blades on the rotor disc are divided into two rows of different blade profiles to improve the compressor single-stage pressure ratio, reduce the stage number, and realize high thrust-to-weight ratio of the aero-engine, and the configuration is as shown in Figure 1

[0003] Currently, the aero-engine mid-assembly type compressor tandem rotor blades are integrally formed on the rotor disc, and in order to ensure high performance indicators, the front and rear rows of rotor blades need to be designed to have a small spacing, which is difficult to walk, the walking path is complex, and thus the processing and manufacturing have a low yield.

[0004] The present application is proposed in view 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 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 mid-assembly type compressor tandem rotor blade and an assembly method 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 mid-assembly type compressor tandem rotor blade is provided, comprising:

[0009] The rotor disc has an annular clamping groove formed on the outer edge rear side, and a pin hole communicating with the annular clamping groove; the rear wall of the annular clamping groove has an opening; the two sides of the opening have limiting grooves;

[0010] The front row of rotor blades is formed on the outer edge front side of the rotor disc in the circumferential direction;

[0011] The rear row of rotor blades has a lower edge plate at the root; each lower edge plate is sequentially clamped into the annular clamping groove through the opening, and abuts against each other in the circumferential direction, wherein the lower edge plate opposite to the opening has an axial stop hole and a circumferential stop protrusion; the circumferential stop protrusion is clamped in the opening, and the two sides have radial stop lugs; the two radial stop lugs are clamped into the two limiting grooves; ​

[0012] An axial stop pin is arranged in the pin hole and inserted into the axial stop hole.

[0013] According to at least one embodiment of the present application, in the above-mentioned assembled compressor tandem rotor blade of the aero-engine, the axial stop pin is six-pointedly pressed and fixed on the rotor disc;

[0014] According to at least one embodiment of the present application, in the above-mentioned assembled compressor tandem rotor blade of the aero-engine, the axial stop pin has a small hole in the middle.

[0015] In one aspect, an assembled compressor tandem rotor blade of an aero-engine is provided.

[0016] The lower edge plate of the root of the rear row of rotor blades is sequentially clamped into the annular clamping groove formed on the rear side of the outer edge of the rotor disc, and the lower edge plates of the roots of the rotor blades are circumferentially abutted against each other.

[0017] The circumferential stop protrusion on the lower edge plate of the root of the rear row of rotor blades opposite to the gap is clamped into the gap, and the rear row of rotor blades is circumferentially stopped.

[0018] The radial stop lugs on both sides of the circumferential stop protrusion are clamped into the limiting grooves on both sides of the gap, and the rear row of rotor blades opposite to the gap is radially stopped.

[0019] The axial stop pin is arranged in the pin hole on the rotor disc and inserted into the axial stop hole, and the rear row of rotor blades opposite to the gap is axially stopped.

[0020] The present application has at least the following beneficial technical effects:

[0021] The present application provides an assembled compressor tandem rotor blade of an aero-engine and an assembling method. Only the front row of rotor blades is formed on the rotor disc, and the rear row of rotor blades is assembled and clamped into the annular clamping groove on the outer edge of the rotor disc through the gap. Through the design of the gap, the lower edge plate of the root of the rear row of rotor blades opposite to the gap, and the axial stop pin, the rear row of rotor blades is stopped and positioned. The front and rear rows of rotor blades can have a small spacing, high performance indicators can be ensured, and there is no problem of difficult processing and manufacturing. BRIEF DESCRIPTION OF DRAWINGS

[0022] Figure 1 is a schematic diagram of a compressor tandem rotor blade structure of an aero-engine provided by an embodiment of the present application;

[0023] Figure 2 is a schematic diagram of an assembled compressor tandem rotor blade of an aero-engine provided by an embodiment of the present application;

[0024] Figure 3is a local schematic view of an assembled compressor tandem rotor blade in an aero-engine provided by the embodiment of the present application.

[0025] wherein:

[0026] 1-rotor wheel disc; 2- front row rotor blade; 3- rear row rotor blade; 4- axial stop pin.

[0027] In order to better illustrate the 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 of the present application. DETAILED DESCRIPTION

[0028] 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 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.

[0029] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of the present application should be understood as the general meaning understood by the general technical personnel in the field of the present application. The words such as "up", "down", "left", "right", "center", "vertical", "horizontal", "inner", "outer" and the like used in the description of the present application only indicate the relative direction or positional relationship, and not to imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation. When the absolute position of the described object changes, the relative positional relationship may also change accordingly, so it cannot be understood as a limitation of the present application. The "first", "second", "third" and the like used in the description of the present application are only for the purpose of description, and are used to distinguish different components, and cannot be understood as indicating or implying relative importance. The "one", "an" 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 existence of at least one. The "include" or "contain" and the like used in the description of the present application 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.

[0030] In addition, it needs to be explained that, unless otherwise explicitly specified and limited, the "installation", "connection", "connection" and similar words used in the description of the application should be understood broadly, for example, the connection can be fixed connection, or detachable connection, or integrally connected; can be mechanical connection, or electrical connection; can be directly connected, or indirectly connected through an intermediate medium, or the internal connection of two elements, and those skilled in the art can understand the specific meaning of the application according to the specific circumstances.

[0031] The following will be described in detail in combination with the accompanying drawings Figures 1 to 3 The application is further described in detail.

[0032] In one aspect, a series of assembled compressor rotor blades in an aero-engine is provided, comprising:

[0033] The rotor disc 1 has a ring-shaped clamping groove formed on the outer edge rear side, and a pin hole communicating with the ring-shaped clamping groove; the rear wall of the ring-shaped clamping groove has an opening; the two sides of the opening have limiting grooves;

[0034] The front row of rotor blades 2 is formed on the outer edge front side of the rotor disc 1 in the circumferential direction;

[0035] The rear row of rotor blades 3 has a lower edge plate at the root; each lower edge plate is sequentially clamped into the ring-shaped clamping groove through the opening, and abuts against each other in the circumferential direction, wherein the lower edge plate opposite to the opening has an axial stop hole and a circumferential stop protrusion; the circumferential stop protrusion is clamped in the opening, and the two sides have radial stop lugs; the two radial stop lugs are clamped into the two limiting grooves;

[0036] The axial stop pin 4 is arranged in the pin hole and inserted into the axial stop hole.

[0037] For the series of assembled compressor rotor blades in the aero-engine disclosed in the above embodiment, those skilled in the art can understand that the design is only that the front row of rotor blades 2 is formed on the rotor disc 1, and the rear row of rotor blades 3 is assembled and clamped into the ring-shaped clamping groove on the outer edge of the rotor disc 1 through the opening, and through the design of the opening and the lower edge plate of the rear row of rotor blades 3 opposite to the opening at the root, cooperating with the axial stop pin 4, the rear row of rotor blades 2 is stopped and positioned, the front and rear rows of rotor blades can be designed to have a smaller spacing, the high performance index is ensured, and there is no problem of difficult processing and manufacturing.

[0038] In some optional embodiments, in the series of assembled compressor rotor blades in the aero-engine, the axial stop pin 4 is six-point punched and fixed on the rotor disc 1;

[0039] In some alternative embodiments, the axial stop pin 4 has a small hole in the middle, which is in interference fit with the pin hole and clearance fit with the axial stop hole.

[0040] In another aspect, a method for assembling the assembled compressor tandem rotor blade in the aero-engine is provided, comprising:

[0041] The lower edge plate at the root of the rear row of rotor blades 3 is sequentially clamped into the annular clamping groove formed on the outer edge rear side of the rotor disc 1, and the lower edge plates at the roots of the rear row of rotor blades 3 are in contact with each other in the circumferential direction;

[0042] The circumferential stop protrusion on the lower edge plate at the root of the rear row of rotor blades 3 opposite the gap is clamped into the gap, and the rear row of rotor blades 3 is circumferentially stopped;

[0043] The radial stop lugs on both sides of the circumferential stop protrusion are clamped into the limiting grooves on both sides of the gap, and the rear row of rotor blades 3 opposite the gap is radially stopped;

[0044] The axial stop pin 4 is arranged in the pin hole on the rotor disc 1 and inserted into the axial stop hole, and the rear row of rotor blades 3 opposite the gap is axially stopped.

[0045] The method for assembling the assembled compressor tandem rotor blade in the aero-engine disclosed in the above embodiments is used to realize the assembly of the assembled compressor tandem rotor blade in the aero-engine disclosed in the above embodiments, and the description is relatively simple. For specific related parts, please refer to the related description of the assembled compressor tandem rotor blade in the aero-engine. The technical effects can also be referred to the technical effects of the related parts of the assembled compressor tandem rotor blade in the aero-engine. Here, it is not necessary to repeat it.

[0046] The 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 embodiments can be referred to each other.

[0047] 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. Without deviating from the principles of the present application, those skilled in the art can make equivalent changes or replacements to the related technical features. The technical solutions after the changes or replacements will fall within the protection scope of the present application.

Claims

1. An assembly method of a serial rotor blade of an assembled compressor in an aeroengine, for realizing assembly of a serial rotor blade of an assembled compressor in an aeroengine, characterized in that, The serial rotor blade of the assembled compressor in the aero-engine comprises: a rotor disc (1) with an annular clamping groove formed on the rear side of the outer edge and a pin hole connected with the annular clamping groove; the rear side wall of the annular clamping groove has an opening; the two sides of the opening have limiting grooves; a front row of rotor blades (2) formed on the front side of the outer edge of the rotor disc (1); a rear row of rotor blades (3) with lower edge plates at the roots; each lower edge plate is sequentially clamped into the annular clamping groove through the opening and tightly abuts against each other in the circumferential direction, wherein the lower edge plate opposite to the opening has an axial stop hole and a circumferential stop protrusion; the circumferential stop protrusion is clamped in the opening and has radial stop lugs on both sides; the two radial stop lugs are clamped into the two limiting grooves; an axial stop pin (4) arranged in the pin hole and inserted into the axial stop hole; the axial stop pin (4) is six-pointedly punched and fixed on the rotor disc (1); the axial stop pin (4) has a small hole in the middle; the assembling method of the serial rotor blade of the assembled compressor in the aero-engine comprises: clamping the lower edge plates at the roots of the rear row of rotor blades (3) into the annular clamping groove formed on the rear side of the outer edge of the rotor disc (1) through the opening in sequence and tightly abutting against each other in the circumferential direction; clamping the circumferential stop protrusion on the lower edge plate at the root of the rear row of rotor blades (3) opposite to the opening into the opening to circumferentially stop the rear row of rotor blades (3); clamping the radial stop lugs on both sides of the circumferential stop protrusion into the limiting grooves on both sides of the opening to radially stop the rear row of rotor blades (3) opposite to the opening; arranging the axial stop pin (4) in the pin hole on the rotor disc (1) and inserting it into the axial stop hole to axially stop the rear row of rotor blades (3) opposite to the opening.

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