Composite processing method for grinding vane apex of rotor vane of aeroengine at high speed

An aero-engine and rotor blade technology, applied in the field of grinding processing, can solve the problems of unstable quality, burns, low efficiency, etc., and achieve the effect of improving processing efficiency and improving manufacturing level

Active Publication Date: 2010-06-09
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] Aiming at the problems of low efficiency, unstable quality and burns of existing aero-engine rotor blade processing methods, the present invention provides a composite processing method for aero-engine rotor blade tip high-speed grinding

Method used

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  • Composite processing method for grinding vane apex of rotor vane of aeroengine at high speed
  • Composite processing method for grinding vane apex of rotor vane of aeroengine at high speed
  • Composite processing method for grinding vane apex of rotor vane of aeroengine at high speed

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0041] Step 1: Pre-Balance the Rotor

[0042] Install the rotor on the balancing machine, adopt single-stage balancing of turntables at all levels, group and combine balancing, and repeat balancing. The specific steps are as follows:

[0043] 1) The final dynamic balance of the primary and secondary rotors: the initial unbalance of each correction plane of the initial primary and secondary rotors is 513.8g.mm and 357.5g.mm respectively. By adjusting the position of the primary and secondary rotor blades, each The unbalance amounts of the two correction planes are 186.7g.mm and 150.4g.mm respectively.

[0044] 2) Balance the third-stage disc assembly: statically balance the third-stage disc assembly, and adjust the position of the third-stage blades so that the unbalance of the correction plane is 184.3g.mm.

[0045] 3) Rotor initial leveling: The high-pressure compressor rotor installed with 1-3 blades is dynamically balanced, and the initial unbalance of each correction plan...

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Abstract

The invention relates to a composite processing method for grinding the vane apex of a rotor vane of an aeroengine at a high speed, which comprises the following steps of: firstly, balancing a rotor in advance, controlling unbalance quantity which is permitted to be used for balancing the rotor in advance to be within 254g.mm, then installing the rotor on a fixture, enabling the rotor to be in a stretching state and grinding at a high speed. In the grinding process, the rotational speed of a processing part is 1600-2000r / min, the linear speed of a grinding wheel is 33-36m / s, the rotational speed of a scrubbing brush is 1500-1900r / min, and the control temperature during grinding is 20+ / -5 DEG C.

Description

technical field [0001] The invention relates to a grinding processing method, in particular to a composite processing method for high-speed grinding of blade tips of an aeroengine rotor blade. Background technique [0002] The rotor assembly structure of the new generation of aero-engine is completely different from the first and second generation engines, and higher requirements are put forward for the grinding of rotor blade tips. The new structure of the high-pressure compressor rotor blade and the circumferential assembly structure of the drum results in a large gap between the blade and the tongue and groove. In order to keep the outer diameter of the blade in a stretched state, it is necessary to ensure the tolerance of the outer diameter of the blade and the diameter of the blade. The goal pursued by the jump. Over the years, the outer diameter of the rotor blades has been processed by installing each blade on a simulation disc, jacking up the blades one by one with ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B24B19/14
Inventor 刘丛辉翟淳巩孟祥杨国鹏杜宝玉张大双陈玲玲
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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