Preparation process of high-temperature alloy multigang hollow turbine blade

A high-temperature alloy and turbine blade technology, which is applied in the field of precision casting, can solve the problems of difficulty in preparing wax patterns, low success rate of wax patterns, and fractures, and achieve the effects of avoiding incomplete strict consistency, improving success rate, and simplifying the manufacturing process
CN101992268AInactive Publication Date: 2011-03-30SHENYANG POLYTECHNIC UNIV
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Patent Information

Authority / Receiving Office
CN · China
Current Assignee / Owner
SHENYANG POLYTECHNIC UNIV
Publication Date
2011-03-30
Estimated Expiration
Not applicable · inactive patent
Patent Text Reader

Abstract

The invention relates to a preparation process of a high-temperature alloy multigang hollow turbine blade. The process comprises the following steps of: (1) partitioning the multigang blade into a plurality of blade units and manufacturing a blade body wax mold for each unit blade, wherein a blade body is provided with a ceramic mold core, the unit blade body wax mold with the ceramic mold core is molded in an injection molding way, injection temperature is between 63 and 68 DEG C, the pressure is between 0.3 and 0.5 MPa, the injection time is between 10 and 30 seconds and the pressure is preserved for 10 to 30 seconds; (2) putting each unit blade body wax mold with the ceramic mold core into a multigang mold and injecting wax for primary molding so as to obtain a multigang hollow blade wax mold; and (3) coating, dewaxing, sintering, pouring, clearing and stripping the multigang hollow blade wax mold so as to obtain a high-temperature alloy multigang hollow turbine blade casting.
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Description

Technical field

[0001] The invention is a precision casting field, especially a high -temperature alloy turbine blade casting process. Background technique

[0002] With the continuous improvement of the forward import temperature of aviation engines and gas turbine turbine, the turbine blades of key thermal components have also changed dramatically.At present, the forward import temperature of the military aviation engine turbine is close to 2200K, and the front import temperature of the turbine of the gas turbine is also increasing.The ability of turbine blades to rely on the material itself to resist high temperature is far from meeting actual needs, and the large amount of composite cooling methods can make turbine blades be able to withstand higher temperatures, but this also makes the internal cooling channels of the leaves extremely complicated and prepared to prepare.The difficulty of the blades, coupled with the double -connected or multi -linked heart turbine blades des...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
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