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Machining method of internal flow passage of impeller cover applied to aero-engine

A technology of aero-engine and processing method, which is applied in the direction of engine components, machines/engines, mechanical equipment, etc. It can solve the problems affecting the working efficiency of the engine, the degree of machining deformation contour, and the installation error of parts, so as to overcome the low turning precision and improve the contour Accuracy, the effect of ensuring machining accuracy

Active Publication Date: 2016-02-24
HARBIN DONGAN ENGINE GRP
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Problems solved by technology

The traditional processing method of the inner flow channel of the impeller cover is CNC turning. During the processing, due to factors such as tool clearance, tool wear, tool setting error, part installation error, and machining deformation, it is easy to cause out-of-tolerance contours, which affects the working efficiency of the engine.

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  • Machining method of internal flow passage of impeller cover applied to aero-engine

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Embodiment Construction

[0014] A method for processing an inner flow channel of an aeroengine impeller cover includes the following steps:

[0015] 1. Process the outer surface and lower end surface of the impeller cover to the final size, process the inner surface to a margin of 0.8-1mm, and process the upper end surface to a margin of 0.3-0.5mm;

[0016] 2. Grind the upper end surface to a margin of 0.05-0.1mm;

[0017] 3. Install the part on the lathe to turn the inner flow channel. Based on the above end face, and consider the margin of the end face, turn the inner flow channel to the size required by the drawing;

[0018] 4. Place the upper end surface of the part on the detection platform of the three-coordinate measuring machine and use the upper end surface as the detection reference, use the three-coordinate measuring machine to detect 200-300 points in the flow channel in the impeller cover and fit them into an actual curve;

[0019] 5. Comparing the fitted actual curve with the theoretica...

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Abstract

The invention relates to a machining method of an internal flow passage of an impeller cover applied to an aero-engine. The method comprises the following steps: firstly machining the internal flow passage to a specified size; subsequently, machining a reference surface. The machining precision of the internal flow passage is guaranteed; practical machining proves that the profile tolerance of the internal flow passage, machined by the method, of the impeller cover is up to 0.03mm. The method disclosed by the invention can be used for effectively improving the precision of the profile tolerance of the internal flow passage of the impeller cover by ways of optimization of the process route and combination of lathe turning, grinding and inspection, so the percent of pass of components is increased and the machining quality is improved.

Description

technical field [0001] The invention relates to a processing method, in particular to a processing method for an inner flow passage of an aeroengine impeller cover, which realizes precise machining of an aeroengine impeller cover inner flow passage through turning and grinding. Background technique [0002] With the development of the aviation industry, the requirements for the accuracy of parts are getting higher and higher. The impeller covers for aero-engines are rotary parts, such as figure 1 As shown, the marked H surface is the inner flow channel, and the inner flow channel is included on the outside of the centrifugal impeller. When the engine is running, the centrifugal impeller rotates at a high speed, and there is a certain gap with the inner flow channel of the impeller cover, and the uniformity of the gap is directly related to It affects the working efficiency of the engine, so the precision of the inner flow channel of the impeller cover is relatively high, tha...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B23P15/00
CPCB23P15/00F01D25/24
Inventor 王增强孙绪保杨晓光陈红霞吴泽刚赵强田丽波梁传宇何佳张静宇
Owner HARBIN DONGAN ENGINE GRP
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