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A kind of compressor stator blade assembly replacement blade repair method

A stator vane and repair method technology, which is applied in the field of aero-engine component repair, can solve the problems of large sealing plate locking, difficult removal, and oxide film in the hole, so as to control welding deformation, prevent deformation, and save costs Effect

Active Publication Date: 2017-09-12
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the component structure is complex and the blades are connected to the inner and outer rings by brazing. It is difficult to replace the blades of the faulty parts and repair many problems. The copper-aluminum coating on the installation part of the outer ring is difficult to decompose due to the high locking degree of the sealing plate, and it is difficult to effectively remove the coating by mechanical grinding and chemical methods; secondly, after removing the faulty blades on the inner and outer rings by electrical machining, There is an oxide film in the hole and it is not easy to remove; third, when the blade is replaced by brazing, the component is welded in a state of no margin, once the deformation is too large, it will not be able to meet the assembly requirements; in addition, the performance and coating of the component must be checked after welding. restore

Method used

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  • A kind of compressor stator blade assembly replacement blade repair method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0030] (1) Faulty parts status:

[0031] The faulty parts are 4th to 6th stage stator vane assemblies of compressors, a total of 20 pieces. The blades are GH4169 alloy rolled parts, and the inner and outer rings are respectively GH600 alloy forgings or strips; the blades at both ends of the assembly and in the middle are damaged Or block defects, need to replace the blade repair, the number of replacement blades of the module is 2 or 3 pieces, and the faulty blades are not adjacent.

[0032] (2) Repair method, comprising the following steps:

[0033] Step 1: Decompose and decompose the sealing board figure 1 The inner ring sealing plate shown specifically includes the following steps:

[0034] Step A: When the sealing plate with small locking degree is disassembled, place the assembly on the fixture, put the open end of the inner ring against the fixture, and clamp the inner and outer rings from both sides;

[0035] Step B: Press the sealing plate with a copper rod from the...

Embodiment 2

[0054] (1) Faulty parts status:

[0055] The faulty parts are 7th to 8th stage stator blade assemblies of compressors, a total of 15 pieces. The blades are GH4169 alloy rolled parts, and the inner and outer rings are respectively GH600 alloy forgings or strips; the blades at both ends of the assembly and in the middle are damaged Or block defects, need to replace the blade repair, the number of replacement blades of the module is 3 to 5 pieces, and there are 2 or 3 adjacent faulty blades.

[0056] (2) Repair method, comprising the following steps:

[0057] Step 1: Decompose and decompose the sealing board figure 1 The inner ring sealing plate shown specifically includes the following steps:

[0058] Step A: When the sealing plate with small locking degree is disassembled, place the assembly on the fixture, put the open end of the inner ring against the fixture, and clamp the inner and outer rings from both sides;

[0059] Step B: Press the sealing plate from the sealing end...

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Abstract

The invention provides a blade replacement and repair method for stator blade assemblies of gas compressors, and belongs to the technical field of component repair of aero-engines. The blade replacement and repair method comprises the steps of 1, disassembling a sealing plate; 2, removing a copper-aluminum coating at the installation part of an outer ring through a sand blowing method; 3, removing a faulted blade through an electric spark forming and machining method and eliminating oxidation films on the inner surface of a forming hole and on the ambient surface of the forming hole; 4, assembling a new blade in the forming hole, inserting the blade into the forming hole from a forming hole in one side of the outer ring, enabling the tail of the blade to be assembled into a forming hole of an inner ring, welding the blade to the inner ring and the outer ring through the spot welding method after the size meets the requirement and coating the to-be-welded head part of the newly-installed blade with brazing filler metal along the peripheries of the forming holes; 5, placing a to-be-welded assembly and a brazing clamp into a vacuum furnace for brazing; 6, after brazing is qualified, recovering the structure according to the heat treatment process of the blade, re-spraying a coating at the installation part of the outer ring according to the technology requirement after heat treatment and re-installing a sealing plate for the assemblies.

Description

technical field [0001] The invention belongs to the technical field of aero-engine component repair, and in particular relates to a method for repairing blade replacement of a compressor stator blade assembly. Background technique [0002] The compressor stator vane assembly is divided into 5 levels, installed in the 4th to 8th level of the high-pressure compressor casing of the engine, and cooperates with the rotor blades to provide the stable high-pressure airflow required for the engine to work. The 4th to 8th stage stator vane assemblies are composed of inner rings, outer rings, blades of different numbers and sealing plates, such as figure 1 shown. The blades are connected with the inner and outer rings by brazing, and the sealing plate is assembled in the flange groove of the component. Due to the impact of high-pressure airflow and vibration fatigue during the working process of the components, after a service cycle, individual blades on different numbers of compone...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B23P6/00
CPCB23P6/002
Inventor 孔庆吉杜静曲伸张磊先杨烁
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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