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Brazing method for turbine rotor assembly of engine

A technology of turbine rotor and brazing method, applied in welding equipment, auxiliary devices, metal processing equipment, etc., can solve problems such as difficulty in welding, and achieve the effects of brazing quality assurance, making up for difficult welding, and enhancing gap filling.

Active Publication Date: 2013-02-13
CHINA HANGFA SOUTH IND CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to provide a brazing method for an engine turbine rotor assembly to solve the technical problem that the mating surfaces of the turbine rotor disk and the sealing sleeve of the engine turbine rotor assembly are tapered and the welding is difficult

Method used

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  • Brazing method for turbine rotor assembly of engine
  • Brazing method for turbine rotor assembly of engine
  • Brazing method for turbine rotor assembly of engine

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Embodiment Construction

[0021] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings, but the present invention can be implemented in many different ways defined and covered by the claims.

[0022] see figure 1 with figure 2 , the preferred embodiment of the present invention provides a brazing method for an engine turbine rotor assembly, the turbine rotor assembly includes a turbine rotor disk 20 with a U-shaped groove 21 and a sealing sleeve 10 matched with the turbine rotor disk 20, the turbine rotor The brazing surface of the disk 20 and the brazing surface of the sealing shaft sleeve 10 are tapered after matching; the brazing method includes the following steps: Step S2: Brazing the brazing surface of the turbine rotor disk 20 and the sealing shaft sleeve 10 The surface is plated with easy-to-weld metal; step S4: wrap sheet-shaped solder on the brazing surface of the sealing shaft sleeve 10; step S6: assemble the turbine rotor di...

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Abstract

The invention provides a brazing method for a turbine rotor assembly of an engine, which comprises the following steps: step 2, plating weldable metal on a brazing surface of a turbine rotor disc and a brazing surface of a sealed shaft sleeve; step 4, wrapping flake-like brazing filler metal on the brazing surface of the sealed shaft sleeve; step 6: assembling and coordinating the turbine rotor disc and the sealed shaft sleeve, with a feed tank arranged between the turbine rotor disc and the sealed shaft sleeve; step 8, adding powdered brazing filler metal in the feed tank and a U-shaped groove; step 10, arranging a leakproof fixture for preventing the powdered brazing filler metal from flowing away in the U-shaped groove; step 12, placing the rotor assembly subjected to the step 10 for brazing; and step 14, taking out the rotor assembly subjected to the step 12 for detecting a welding line. According to the brazing method for the turbine rotor assembly of the engine provided by the invention, the leakproof fixture for preventing the powder brazing filter metal from flowing away is arranged in the U-shaped groove, so that the brazing filler metal is prevented from flowing away and is not accumulated randomly after the brazing, and the brazing quality is ensured.

Description

technical field [0001] The invention relates to the field of welding, in particular to a brazing method for an engine turbine rotor assembly. Background technique [0002] The gas generator turbine rotor assembly of an aero-engine is usually composed of a turbine rotor disk and a sealing sleeve. The rotor assembly of the domestic XX66 series power auxiliary engine has a special structure, and the mating surface of the turbine rotor disk and the sealing sleeve is in the shape of The conical shape makes welding more difficult; and it is required that the combined brazing joint area of ​​the turbine rotor disk and the sealing sleeve is greater than 80% of the total area to be brazed, and the radial load that the two can withstand is greater than or equal to 45000N. The preparation material of the turbine rotor disk is K424 cast superalloy, the preparation material of the sealing sleeve is 1C11Ni2W2MoV stainless steel, and the turbine rotor disk is made of a material that is not...

Claims

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Application Information

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IPC IPC(8): B23K1/008B23K3/08
Inventor 邹旸
Owner CHINA HANGFA SOUTH IND CO LTD
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