CN218137040U

CN218137040U - Device for machining turbine blades of an aircraft engine

Info

Publication number: CN218137040U
Application number: CN202222796786.5U
Authority: CN
Inventors: 徐培胜; 白焕霞; 林广森; 王安普; 梁肖; 梁腾渊; 朱晋永; 朱伟强; 王越; 杨帅; 王冰
Original assignee: Haixiang Machinery Factory Yongnian District Handan City
Current assignee: Haixiang Machinery Factory Yongnian District Handan City
Priority date: 2022-10-24
Filing date: 2022-10-24
Publication date: 2022-12-27
Anticipated expiration: 2032-10-24

Abstract

The utility model discloses a device for processing aeroengine's turbine blade, include: a face grinder fixture, the face grinder fixture comprising: a body, a lower surface of which is inclined and placed above a surface grinder; a locating block placed above the body to support the turbine blade; a clamp plate placed above the body for clamping one end of the turbine blade; a positioning assembly disposed above the body for clamping the other end of the turbine blade, the turbine blade being secured to the face grinder fixture by the clamp plate and the positioning assembly; and the grinding wheel is positioned on the side surface of the surface grinding machine clamp, and the processing surface is parallel to the processing surface of the turbine blade. The device can stabilize the processing quality, reduce the manufacturing and maintenance cost, and realize the processing of the turbine blade of the engine by using flat grinding without purchasing a special grinding machine.

Description

Device for machining turbine blades of an aircraft engine

Technical Field

The utility model relates to a technical field of aeroengine maintenance generally especially relates to a device for processing aeroengine's turbine blade.

Background

The abradable layer of a blade shroud of a turbine rotor of an aircraft engine, where the rotor blade is an engine high temperature turbine rotor blade, typically needs to be repaired for continued use. The engine assembly state is that 75 pieces of blade circumference mesh, and the mating surface is zero clearance meshing, and its in use receives high temperature, vibrations etc. and influences, and the mating surface wearing layer is very easy wearing and tearing. The wear-resistant layer of the meshing surface cannot meet the use requirement of an assembling machine after being worn, so the wear-resistant layer needs to be repaired, and the blades are long and involve complex profiles such as space torsion. The prior art utilizes the numerical control creep feed grinding machine to restore, and the utility model discloses a device utilizes flat grinder to restore.

SUMMERY OF THE UTILITY MODEL

In one aspect of the present disclosure, there is provided an apparatus for machining a turbine blade of an aircraft engine, characterized by comprising: a face grinder fixture, the face grinder fixture comprising: a body, a lower surface of which is inclined and placed above a surface grinder; a locating block placed above the body to support the turbine blade; a clamp plate placed above the body for clamping one end of the turbine blade; a positioning assembly disposed above the body for clamping the other end of the turbine blade, the turbine blade being secured to the face grinder fixture by the clamp plate and the positioning assembly; and the grinding wheel is positioned on the side surface of the surface grinding machine clamp, and the processing surface of the grinding wheel is parallel to the processing surface of the turbine blade.

In some embodiments, the positioning assembly is a bolt.

In some embodiments, the height of the locating block is adjusted based on the wear of the turbine blade.

In some embodiments, the clamp plate further comprises a handle, the degree of clamping of the turbine blade being controlled by use of the handle.

In some embodiments, the turbine blade machined surface is angled 35 ° 30' from horizontal.

In some embodiments, the turbine blade clamping and positioning surface is at an angle of 74 ° 30' to the horizontal.

In some embodiments, the machined surface of the turbine blade is machined using a machined surface of a grinding wheel.

In some embodiments, the flat grinder is model No. MM7120.

Compared with the prior art, the beneficial effects of the disclosure are: the device can stabilize the processing quality, reduce the manufacturing and maintenance cost, realize the processing of the turbine blade of the engine by using the flat grinding processing without purchasing a special grinding machine, and solve the problem of repairing the blade by using the flat grinding machine.

Drawings

The novel features of the invention are set forth with particularity in the appended claims. A better understanding of the features and advantages of the present invention will be obtained by reference to the following detailed description that sets forth illustrative embodiments, in which the principles of the invention are utilized, and the accompanying drawings. The drawings are only for purposes of illustrating embodiments and are not to be construed as limiting the invention. Also, in the drawings, wherein like reference numerals refer to like elements throughout:

fig. 1 shows a schematic view of a face grinder fixture according to an exemplary embodiment of the present disclosure.

FIG. 2 shows a side view of a face grinder fixture according to an exemplary embodiment of the present disclosure.

Description of the reference numerals

The device comprises a body 1, a positioning block 2, a clamping plate 3 and a positioning assembly 4.

Detailed Description

Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art. Nothing in the following detailed description is intended to indicate that any particular component or feature is essential to the invention. Those skilled in the art will appreciate that various features may be substituted for or combined with one another without departing from the scope of the present disclosure.

In the description of the present invention, it is to be understood that the terms "upper", "lower", "center", "inner", "outer", "top", "bottom", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention.

In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected" and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.

There is provided herein an apparatus for machining a turbine blade of an aircraft engine, comprising: provided is a surface grinding machine clamp. Fig. 1 shows a schematic view of a face grinder fixture according to an exemplary embodiment of the present disclosure. FIG. 2 shows a side view of a face grinder fixture according to an exemplary embodiment of the present disclosure. The surface grinder fixture may include a body 1, a locating block 2, a clamping plate 3, and a locating assembly 4. The lower surface of the body 1 may be inclined and placed above the surface grinder. The positioning block 2 is placed above the body 1 to support the turbine blade. The clamping plate 3 may be placed above the body 1 for clamping one end of the turbine blade. In some embodiments, the clamp plate 3 may also include a handle that an operator can use to control the extent of clamping of the turbine blades. Specifically, the operator can further tighten the splint 3 by rotating the handle clockwise, or further loosen the splint 3 by rotating the handle counterclockwise. The positioning block 2 is arranged above the support to support the turbine blade, and the height of the positioning block 2 is adjusted according to the actual wear condition of the turbine blade. Specifically, the height of the positioning block 2 may be further increased according to the height of the worn turbine blade from the surface grinding machine, that is, the worn part of the turbine blade is compensated by the positioning block 2, so that the height of the turbine blade from the surface grinding machine is fixed, and the machining surface of the turbine blade is parallel to the machining surface of the grinding wheel. The positioning component 4 is placed above the body and used for clamping the other end of the turbine blade, and the turbine blade is fixed to the surface grinder clamp through the clamping plate 3 and the positioning component 4. In some embodiments, the positioning assembly 4 may include a positioning ball pin and a positioning block, and the turbine blade may be clamped and positioned by adjusting the positions of the positioning ball pin and the positioning block. In some embodiments, the positioning assembly 4 is preferably a bolt. In some embodiments, the positioning component 4 may also be any one of a screw, a nut, a stud, a pin. The positioning assembly 4 may also be any type of positioning or fastening assembly deemed appropriate by a person skilled in the art. Preferably, the machined surface of the turbine blade may be at 35 ° 30 'from the horizontal plane, and the clamping locating surface of the turbine blade may be at an angle of 74 ° 30' from the horizontal plane, so that the machined surface of the turbine blade to be repaired may be substantially parallel to the working surface of the grinding wheel. In some embodiments, the locating assembly 4 may include a mortise locating device above the mount and cooperating with a clamp plate to clamp and locate the mortise of the turbine blade, and a tip shroud locating device above the mount and spaced apart from the clamp plate to clamp and locate the tip shroud of the turbine blade. The device for machining turbine blades of aircraft engines may also comprise a grinding wheel. The grinding wheel is positioned on the side surface of the surface grinding machine clamp, and the processing surface of the grinding wheel is parallel to the processing surface of the turbine blade. In some embodiments, the grinding wheel may be 40mm thick and 300mm in diameter. The thickness and diameter of the grinding wheel may also be any other dimension deemed appropriate by those skilled in the art. In some embodiments, the machined surface of the turbine blade may be machined using a machined surface of a grinding wheel. In some embodiments, the grinding wheel may have a first machined surface at a first angle to a transverse axis of the grinding wheel and a second machined surface at a second angle to the transverse axis of the grinding wheel (i.e., the working surface of the grinding wheel), and the intersection of the first machined surface and the second machined surface may be the same distance from both sides of the grinding wheel. In some embodiments, the first included angle may be 35 ° 30'. In some embodiments, the second included angle may be 74 ° 30'. The horizontal axis of the grinding wheel is in the horizontal plane. In some embodiments, the device for machining the turbine blade of the aircraft engine of the exemplary embodiment of the disclosure can be placed on a surface grinder MM7120 for use in machining the turbine blade. However, the turbine blades may be machined using any type of face grinder deemed appropriate by those skilled in the art. The bowl-wise (forward) machined surface and the back-to-machined surface of the turbine blade to be repaired (machined) may be substantially parallel to the working surface of the grinding wheel (parallel to the first machined surface and the second machined surface of the grinding wheel, respectively). By adjusting the clamp and trimming the profile of the grinding wheel, the working surface of the grinding wheel can not interfere with the non-repairing surface of the blade. The wheels of the exemplary embodiments of the present disclosure may be obtained by dressing a standard wheel using a wheel dresser. In some embodiments, when the basin-facing processing surface of the turbine blade is processed, the basin-facing fixture is aligned and straightened and fixed on a magnetic disk of a surface grinder, the blade is clamped and positioned by a clamping plate, and a formed grinding wheel is deeply inserted into the basin of the blade for grinding within an acute angle of 75 degrees. In some embodiments, when the back face of the turbine blade is machined, the clamp and the base are aligned and straightened and fixed on a magnetic disc of a surface grinder, the blade is clamped and positioned by a pressure plate, and the formed grinding wheel is ground into an acute angle of 75 degrees back to the blade.

The technical scheme of the utility model adopt foretell device, it can stabilize processingquality, reduces manufacturing and cost of maintenance, has solved the interference problem of flat grinder acute angle grinding, has especially realized using the flat grinding processing to process the turbine blade of engine and need not to purchase special purpose grinder.

In the description provided herein, numerous specific details are set forth. However, it is understood that embodiments of the disclosure may be practiced without these specific details. In some instances, well-known structures and techniques have not been shown in detail in order not to obscure an understanding of this description.

While exemplary embodiments of the present invention have been shown and described herein, it will be readily understood by those skilled in the art that such embodiments are provided by way of example only. Numerous modifications, changes, and substitutions will now occur to those skilled in the art without departing from the invention. It should be understood that various alternatives to the embodiments of the invention described herein may be employed in practicing the invention. It is intended that the following claims define the scope of the invention and that structures within the scope of these claims and their equivalents be covered thereby.

Claims

1. An apparatus for machining a turbine blade of an aircraft engine, comprising:

a face grinder fixture, the face grinder fixture comprising:

a body, a lower surface of which is inclined and placed above a surface grinder;

a locating block placed above the body to support the turbine blade;

a clamp plate placed above the body for clamping one end of the turbine blade; and

a positioning assembly disposed above the body for clamping the other end of the turbine blade, the turbine blade being secured to the face grinder fixture by the clamp plate and the positioning assembly; and

and the grinding wheel is positioned on the side surface of the surface grinding machine clamp, and the processing surface of the grinding wheel is parallel to the processing surface of the turbine blade.

2. The apparatus of claim 1, wherein the positioning assembly is a bolt.

3. The apparatus of claim 1, wherein the height of the locating block is adjusted based on wear of the turbine blade.

4. The apparatus of claim 1, wherein the clamp plate further comprises a handle, the grip being used to control the extent of clamping of the turbine blade.

5. The apparatus of claim 1, wherein said machined surface of said turbine blade is angled 35 ° 30' from horizontal.

6. The apparatus of claim 1, wherein the turbine blade clamping and positioning surface is at an angle of 74 ° 30' from horizontal.

7. The apparatus according to claim 1, wherein the machined surface of the turbine blade is machined using the machined surface of the grinding wheel.

8. The apparatus of claim 1, wherein the flat grinder is model No. MM7120.

9. The apparatus of claim 1, wherein the grinding wheel has a thickness of 40mm and a diameter of 300mm.