CN219310748U

CN219310748U - Machining tool for test holes of rectifier blades of interstage casing of aero-engine

Info

Publication number: CN219310748U
Application number: CN202223075446.XU
Authority: CN
Inventors: 剧亚东; 厉福海; 贾婷; 王艳平; 王佳伟
Original assignee: Suzhou Hanwei Material Technology Co ltd
Current assignee: Suzhou Hanwei Material Technology Co ltd
Priority date: 2022-11-21
Filing date: 2022-11-21
Publication date: 2023-07-07
Anticipated expiration: 2032-11-21

Abstract

The utility model provides a processing tool for testing holes of rectifier blades of an interstage casing of an aeroengine, which comprises the following components: the automatic test device comprises a hydraulic cylinder, an active push plate and a jogged plate, wherein the left end of the hydraulic cylinder is provided with the active push plate, an upper closing hole is formed in the active push plate, a push pad is arranged at the left end of the active push plate, a sliding block is arranged at the middle position of the lower end of the active push plate, a sliding groove is formed outside the sliding block, a lower test hole is formed in the sliding groove, the jogged plate is arranged at the left end of the sliding block, a base plate is arranged at the outer side of the sliding groove, a fixing seat is arranged at the left side of the base plate, and a buffer is arranged at the right side of the lower end of the fixing seat. Through using initiative push pedal and slider, can two-layer blade carry out the centre gripping respectively, through using buffer, clamp lining and gomphosis board, can protect the rectification blade.

Description

Machining tool for test holes of rectifier blades of interstage casing of aero-engine

Technical Field

The utility model belongs to the technical field of aero-engines, and relates to a processing tool for testing holes of rectifier blades of an interstage casing of an aero-engine.

Background

In an aeroengine, a rectifying blade is a key part in an aeroengine compressor, the quality of the rectifying blade determines the quality and performance of the engine, the rectifying blade is assembled in a casing of the engine through a blade edge plate mounting part, stable compressed air flow with a determined direction and flow rate is provided for the compressor rotor blade, the compressor rotor blade is enabled to obtain stable working conditions, stable high-pressure and temperature air is provided for a combustion chamber, and the combustion chamber is enabled to work normally.

The method has the advantages that the size precision of the rectifying vane test hole is high, the angle is multiple, the conventional processing method needs to clamp for many times, the angle of the test hole of the rectifying vane of the interstage casing of the aeroengine is multiple, each interstage casing of the aeroengine is of a structure with two layers of vanes, each layer of mounting hole is numerous, a plurality of test holes are arranged between the two layers of vanes, but when the rectifying vane test hole is actually processed, the characteristics are found to be not integrated in the same equipment, the traditional processing flow needs to use a plurality of equipment in a combined mode, the operation flow is troublesome, the working efficiency is reduced, and meanwhile, the maintenance cost of the equipment is increased.

Disclosure of Invention

Aiming at the defects in the prior art, the utility model aims to provide a processing tool for testing holes of rectifier blades of an interstage casing of an aero-engine, which solves the problems in the prior art.

The utility model is realized by the following technical scheme: machining frock in aeroengine interstage receiver rectification blade test hole includes: the device comprises a hydraulic cylinder, an active push plate, an upper combining hole, a push pad, a base plate, a sliding chute, a fixed seat, a lower testing hole, a sliding block, a buffer, a clamping liner and an embedded plate, wherein the active push plate is arranged at the left end of the hydraulic cylinder;

an upper closing hole is formed in the active push plate, a push pad is arranged at the left end of the active push plate, a sliding block is arranged at the middle position of the lower end of the active push plate, a sliding groove is formed in the outer portion of the sliding block, and a lower testing hole is formed in the sliding groove;

the embedded plate is arranged at the left end of the sliding block, a base plate is arranged at the outer side of the sliding groove, a fixing seat is arranged at the left side of the base plate, and a buffer is arranged at the right side of the lower end of the fixing seat.

As a preferred implementation mode, the hydraulic cylinder comprises a pump body and telescopic columns, wherein two groups of telescopic columns are installed and are respectively connected with the right side of the driving push plate and the right side of the sliding block.

As a preferable implementation mode, the cross section of the driving pushing plate is of a convex structure, the sliding block is not connected with the driving pushing plate, and the sliding block and the sliding groove are movably embedded with each other, so that the clamping area of the rectifying blade can be increased.

As a preferred implementation mode, the pushing pad is fixedly connected with the active pushing plate, two groups of pushing pads are installed in a connecting mode, and the left side of the fixing seat is fixedly connected with the pushing pad.

As a preferred implementation mode, the processing groove is arranged at the middle position of the base plate, when the rectifying blade is clamped and fixed with the base plate, the upper combined hole and the inner axis of the lower test hole are positioned on the same longitudinal line, and the working personnel can conveniently process the test holes.

As a preferable implementation mode, the inside of the fixing seat is fixedly connected with the buffer, the clamping liner is fixedly connected with the right end of the buffer, and the clamping liner and the embedding plate are made of rubber materials.

After the technical scheme is adopted, the utility model has the beneficial effects that: through using initiative push pedal and slider, can two-layer blade carry out the centre gripping respectively, through using buffer, clamp lining and gomphosis board, can protect the rectification blade.

Drawings

In order to more clearly illustrate the embodiments of the utility model or the technical solutions of the prior art, the drawings which are used in the description of the embodiments or the prior art will be briefly described, it being obvious that the drawings in the description below are only some embodiments of the utility model, and that other drawings can be obtained according to these drawings without inventive faculty for a person skilled in the art.

FIG. 1 is a schematic structural view of a tooling for machining test holes of rectifier blades of an interstage casing of an aeroengine;

FIG. 2 is a left-view structural diagram of an active push plate and a sliding block in a processing tool for testing holes of rectifier blades of an interstage casing of an aeroengine;

FIG. 3 is a bottom view structural diagram of a fixing seat and a backing plate in a processing tool for testing holes of rectifier blades of an interstage casing of an aeroengine;

in the figure: 1-hydraulic cylinder, 2-initiative push pedal, 3-go up and close the hole, 4-push pad, 5-backing plate, 6-spout, 7-fixing base, 8-test hole down, 9-slider, 10-buffer, 11-clamp lining, 12-plywood.

Detailed Description

The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.

Referring to fig. 1-3, a tooling for machining test holes of rectifier blades of an interstage casing of an aero-engine includes: the device comprises a hydraulic cylinder 1, an active push plate 2, an upper combining hole 3, a push pad 4, a base plate 5, a sliding chute 6, a fixed seat 7, a lower test hole 8, a sliding block 9, a buffer 10, a clamping liner 11 and a jogged plate 12, wherein the active push plate 2 is arranged at the left end of the hydraulic cylinder 1;

an upper closing hole 3 is formed in the driving push plate 2, a push pad 4 is arranged at the left end of the driving push plate 2, a sliding block 9 is arranged at the middle position of the lower end of the driving push plate 2, a sliding groove 6 is formed in the outer side of the sliding block 9, and a lower testing hole 8 is formed in the sliding groove 6;

the embedded plate 12 is installed at the left end of the sliding block 9, the base plate 5 is arranged on the outer side of the sliding groove 6, the fixing seat 7 is installed on the left side of the base plate 5, and the buffer 10 is installed on the right side of the lower end of the fixing seat 7.

The hydraulic cylinder 1 comprises a pump body and a telescopic column, wherein the telescopic column is provided with two groups and is respectively connected with the right side of the driving push plate 2 and the right side of the sliding block 9, so that the whole-flow blade can be clamped.

The cross section of the driving push plate 2 is of a convex structure, the sliding block 9 is not connected with the driving push plate 2, and the sliding block 9 and the sliding groove 6 are movably embedded with each other, so that the clamping area of the rectifying vane can be increased.

The pushing pad 4 is fixedly connected with the driving pushing plate 2, two groups of pushing pads 4 are fixedly connected with the pushing pad 4, and the left side of the fixing seat 7 is fixedly connected with the pushing pad 4.

The processing groove has been seted up to backing plate 5 intermediate position, and when rectification blade and backing plate 5 centre gripping were fixed, it was gone up and is closed hole 3 and lower test hole 8 inside axis and is in same vertical line, can make things convenient for the staff to process the test hole.

The inside of fixing base 7 is connected fixedly with buffer 10, presss from both sides lining 11 and is connected fixedly with buffer 10 right-hand member, presss from both sides lining 11 and embedding board 12 and is made for a rubber material, can effectively protect the rectification blade.

As a first embodiment of the present utility model: in order to solve the problem that each aeroengine interstage casing rectifying vane is of a structure with two layers of vanes, the existing processing flow needs a plurality of devices to be combined for use, the operation flow is troublesome, the working efficiency is reduced, and meanwhile the maintenance cost of the devices is increased, firstly, workers place the rectifying vane in a processing groove in a backing plate 5, then a hydraulic cylinder 1 is started, an active push plate 2 and a sliding block 9 are moved from right to left through telescopic columns, so that the outer side of the rectifying vane is clamped, and meanwhile, two groups of pushing and pressing pads 4, a lining 11, a jogging plate 12 and a buffer 10 can carry out protective clamping on the double-layer structure of the rectifying vane.

As a second embodiment of the present utility model: in order to solve the problem that a plurality of test holes are formed between two layers of blades, a plurality of devices are required to be combined for use in the existing processing flow, and the operation flow is troublesome, firstly, the problems are described in the first embodiment, and when the rectifying blades are clamped and fixed with the backing plate 5, the internal axes of the upper combined hole 3 and the lower test hole 8 are positioned on the same longitudinal line, so that the working staff can conveniently process the inside of the test holes.

The foregoing description of the preferred embodiments of the utility model is not intended to be limiting, but rather is intended to cover all modifications, equivalents, alternatives, and improvements that fall within the spirit and scope of the utility model.

Claims

1. Machining frock in aeroengine interstage receiver rectification blade test hole includes: the hydraulic cylinder (1), initiative push pedal (2), and gomphosis board (12), its characterized in that: the left end of the hydraulic cylinder (1) is provided with an active push plate (2);

the automatic test device is characterized in that an upper closing hole (3) is formed in the active push plate (2), a push pad (4) is arranged at the left end of the active push plate (2), a sliding block (9) is arranged in the middle of the lower end of the active push plate (2), a sliding groove (6) is formed in the outer side of the sliding block (9), and a lower test hole (8) is formed in the sliding groove (6);

the embedded plate (12) is installed at the left end of the sliding block (9), the base plate (5) is arranged on the outer side of the sliding groove (6), the fixing seat (7) is installed on the left side of the base plate (5), and the buffer (10) is installed on the right side of the lower end of the fixing seat (7).

2. The tooling for testing the hole of the rectifier blade of the interstage casing of the aircraft engine according to claim 1, wherein: the hydraulic cylinder (1) comprises a pump body and telescopic columns, wherein two groups of telescopic columns are installed and are respectively connected with the right side of the driving push plate (2) and the right side of the sliding block (9).

3. The tooling for testing the hole of the rectifier blade of the interstage casing of the aeroengine according to claim 2, wherein: the cross section of the driving push plate (2) is of a convex structure, the driving push plate (2) is not connected with the sliding block (9), and the sliding block (9) and the sliding groove (6) are movably embedded with each other.

4. The tooling for testing the test holes of the rectifier blades of the interstage casing of the aeroengine according to claim 3, wherein: the driving push plate (2) is fixedly connected with the pushing and pressing pad (4), two groups of pushing and pressing pads (4) are connected and installed, and the pushing and pressing pad (4) on the left side is fixedly connected with the fixing seat (7).

5. The tooling for testing the hole of the rectifier blade of the interstage casing of the aircraft engine according to claim 4, wherein: the processing groove is formed in the middle of the base plate (5), and when the rectifying blade is clamped and fixed with the base plate (5), the inner axes of the upper combined hole (3) and the lower test hole (8) are located on the same longitudinal line.

6. The tooling for testing the hole of the rectifier blade of the interstage casing of the aircraft engine according to claim 5, wherein: the inside of the fixing seat (7) is fixedly connected with the buffer (10), the clamping liner (11) is fixedly connected with the right end of the buffer (10), and the clamping liner (11) and the embedded plate (12) are made of rubber materials.