Micro-clearance assembling device and micro-clearance assembling method for low pressure turbine blade of aircraft engine

A technology of aircraft engines and low-pressure turbines, applied in the field of aircraft engines, can solve the problems of low assembly efficiency and inconvenient operation of the assembly work structure, and achieve the effects of improving the pass rate, flexible and convenient assembly, and reducing the difficulty of operation

Active Publication Date: 2019-10-25
CHENGDU ENGINE GROUP
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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 an aircraft engine low-pressure turbine blade micro-gap assembly device to solve the problems of inconvenient operation and low assembly efficiency in the existing assembly work structure

Method used

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  • Micro-clearance assembling device and micro-clearance assembling method for low pressure turbine blade of aircraft engine
  • Micro-clearance assembling device and micro-clearance assembling method for low pressure turbine blade of aircraft engine
  • Micro-clearance assembling device and micro-clearance assembling method for low pressure turbine blade of aircraft engine

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Embodiment

[0039] Please refer to figure 1 , the aircraft engine low-pressure turbine blade micro-gap assembly device 10 of the embodiment of the present invention includes: a bearing assembly 101 , and a support assembly 102 and a pressing assembly 103 respectively arranged on the bearing assembly 101 . figure 1 The middle dotted line part is the turbine 20 , including the turbine rotor 201 and the turbine blades 202 . The bearing assembly 101 is used to rotate the turbine rotor 201 to assemble the turbine blades 202 at different positions, which makes the operation very convenient for workers. The support assembly 102 is used for supporting and positioning the turbine rotor 201 and the turbine blade 202 during the assembly process, which is equivalent to an assembly operation platform. The pressing assembly 103 is used to press and fix the turbine rotor 201 during the assembly process, so as to avoid affecting the assembly accuracy due to the movement of the turbine rotor 201 during t...

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Abstract

The invention discloses a micro-clearance assembling device and a micro-clearance assembling method for a low pressure turbine blade of an aircraft engine and belongs to the technical field of aircraft engines. The device comprises a bearing assembly, and a supporting assembly and a compaction assembly separately arranged on the bearing assembly. The bearing assembly comprises a base and a bearingstructure arranged in the middle of the base. The supporting assembly is distributed around the bearing structure and comprises a supporting seat fixed to the base. The compaction assembly comprisesa pressure plate connected to the bearing structure. The device is high in accuracy, can reflect clearance data of the assembled blade by measurement of a feeler gauge, and can guarantee that the gapis with a specified range, so that the assembling percent of pass is improved. The device is good in operability, and operating staff trained simply can take the post, so that the operating difficultyis reduced greatly. The device is high in universality and can be widely applied to micro-clearance assembly of other blades.

Description

technical field [0001] The invention relates to the technical field of aircraft engines, in particular to a micro-gap assembly device and an assembly method for low-pressure turbine blades of an aircraft engine. Background technique [0002] As the core component of the entire engine, the turbine part of the aircraft engine has its main functions: 1. Drive the low-pressure compressor to rotate; 2. Make the airflow flow to the tail nozzle to form thrust. In view of the huge role that the engine turbine plays in the operation of the aircraft, it is particularly important to ensure the fit between the low pressure turbine blades and the low pressure turbine rotor. If it is found that the gap between the blade and the rotor cannot meet the technical requirements, it will inevitably affect the balance of the rotor, thereby causing engine vibration, causing huge economic losses, and even endangering life safety. However, the existing assembly tooling has a huge and complex struct...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B25B11/02
CPCB25B11/02
Inventor 王涛关强徐镱杨霄
Owner CHENGDU ENGINE GROUP
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