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
CN110370201AActive Publication Date: 2019-10-25CHENGDU ENGINE GROUP
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
CHENGDU ENGINE GROUP
Publication Date
2019-10-25

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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.
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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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