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Precision machining method for multi-tooth turbine blade of aero-engine

An aero-engine and turbine blade technology, applied in electric processing equipment, air transportation, metal processing equipment, etc., can solve problems such as restricting the processing efficiency of turbine blades and reducing processing stability, shortening processing time, increasing flow rate, and preventing short circuits. effect of the phenomenon

Active Publication Date: 2021-07-09
JIANGSU JIANGHANGZHI AIRCRAFT ENGINE COMPONENTS RES INST CO LTD
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Problems solved by technology

In practice, the higher the processing voltage, the higher the electrolysis efficiency. However, due to the large amount of heat generated in the processing gap and the formation of a large number of products, the processing stability is reduced, which restricts the processing efficiency of turbine blades. Therefore, how to operate at high voltage It is a technical problem that needs to be overcome at present to obtain a stable processing state

Method used

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  • Precision machining method for multi-tooth turbine blade of aero-engine
  • Precision machining method for multi-tooth turbine blade of aero-engine
  • Precision machining method for multi-tooth turbine blade of aero-engine

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Embodiment Construction

[0039] In order to make the technical means, creative features, goals and effects achieved by the present invention easy to understand, the present invention will be further described below in conjunction with specific embodiments.

[0040] Such as Figure 1 to Figure 11 As shown, the present invention discloses a precision machining method for multi-tooth turbine blades of an aero-engine, which specifically includes the following steps:

[0041] Step 1. Take the rough blank of the turbine blade and clean the surface. After cleaning, use the positioning mechanism to perform multi-point positioning of the turbine blade;

[0042] Step 2. Machining the mortise teeth, the mortise teeth exhaust side and the mortise teeth intake side by using the CNC machining center;

[0043] Step 3, using the electric discharge process to process air film holes and light holes radially distributed along the blade body on the blade body;

[0044] Step 4: Take the tool cathode 3 and install the supp...

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Abstract

The invention discloses a precision machining method for a multi-tooth turbine blade of an aero-engine, and relates to the technical field of turbine blade machining. The method comprises the steps of pretreatment of the turbine blade, machining of tenon teeth, the tenon tooth exhaust side and the tenon tooth air inlet side, machining of an air film hole and an unthreaded hole, assembling of a tool cathode, electrolytic machining of a bamboo joint hole, cleaning, packaging, warehousing and the like. According to the method, the defects of a traditional method are overcome, the stability of the machining process can still be guaranteed under the condition of high voltages, and therefore the electrolytic machining efficiency is improved, the machining time is shortened, and when the temperature of electrolyte rises, the flow speed of the electrolyte can be adjusted through an adjusting module so as to accelerate heat dissipation of an electrolytic machining area. And stable control of the temperature of the electrolyte is achieved.

Description

technical field [0001] The invention belongs to the technical field of turbine blade processing, and in particular relates to a precision machining method for multi-tooth turbine blades of an aero-engine. Background technique [0002] For an aero engine, the turbine blade is a very critical component, and its temperature tolerance greatly affects the performance of the engine. In order to improve the temperature resistance of turbine blades, research is currently being carried out from two aspects, one is the material properties of the blade itself, and the other is the manufacturing process. [0003] In terms of manufacturing process, at present, the cooling of blades mainly adopts the design of circulation channels (that is, cooling channels) with different shapes inside the blades to increase the heat dissipation of the blades. It is applied on the leading edge of the turbine blade, the blade pot, and the blade back, and is usually called "bamboo hole". During the heat ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B23P15/02B23H9/16B23H3/00B23H3/10B23H11/00
CPCB23P15/02B23H9/16B23H3/00B23H3/10B23H11/00Y02T50/60
Inventor 吴江严小琳曹春晓
Owner JIANGSU JIANGHANGZHI AIRCRAFT ENGINE COMPONENTS RES INST CO LTD
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