A turbine guide vane with internal cooling channel of complex fin structure
A turbine guide and cold channel technology, applied in the direction of machine/engine, engine function, stator, etc., can solve the problems of high investment casting cost, cumbersome and complicated process, high time and labor costs, etc.
Active Publication Date: 2021-04-09
BEIJING SNECMA SAIC TURBOTECH CO LTD
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Problems solved by technology
[0002] Existing aero-engine turbine guide blades work under high temperature and high pressure conditions, and the temperature of the gas flowing through the blade exceeds the tolerance of its material. In order to make it meet the working requirements, the blade needs to be cooled. Fins and spoiler columns are added to the internal cooling channel of the blade. The best manufacturing method of the existing turbine blade is investment casting without margin. The process mainly includes the design and manufacture of core molds. , the time and labor costs are very high, and due to the limitation of the technological level, the fins usually adopt simple and regular structures such as semicircles and triangles, and are limited to individual orientations, and the effect of disturbing the cooling airflow is poor
With the development of high-thrust and high-efficiency turbine engines, it is necessary to continuously increase the inlet temperature of the turbine, and the structure of the internal cooling passage is becoming more and more complex. The simple and regular fin structure can no longer meet the needs, and the complex shape of the Die casting is expensive and difficult to meet its precision requirements
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[0036] Certain terms are used, for example, in the description and claims to refer to particular components. Those skilled in the art should understand that hardware manufacturers may use different terms to refer to the same component. The specification and claims do not use the difference in name as a way to distinguish components, but use the difference in function of components as a criterion for distinguishing. As mentioned throughout the specification and claims, "comprising" is an open term, so it should be interpreted as "including but not limited to". "Plurality" means equal to or more than two; in addition, the terms "first" and "second" are only used for descriptive purposes, and cannot be interpreted as indicating or implying relative importance or implicitly indicating the indicated technical features quantity. The subsequent description of the specification is a preferred implementation mode for implementing the application, but the description is for the purpos...
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The invention relates to a turbine guide vane with an internal cooling channel of a complex fin structure, which includes a blade body containing a cavity, and the cavity is arranged along the flow direction of the cooling air flow to divide the cavity into a plurality of connected cooling air flow channels The cooling air flow channel is provided with several fins perpendicular to the air flow direction, and the cross section of the fins is polygonal to disturb the cooling air flow, so as to improve the heat exchange efficiency and reduce the blade surface temperature. The present invention forms blades with irregular polygonal or complex regular polygonal rib structure internal cooling passages by using additive manufacturing technology, so that the effect of disturbing the cooling air flow is greatly enhanced, the heat exchange efficiency is improved, the surface temperature of the blades is effectively reduced, and the The service life of the blade and even the whole engine is extended, and at the same time, the manufacturing and use costs are greatly reduced.
Description
technical field [0001] The invention relates to the technical field of aero-engines, in particular to a turbine guide vane with internal cooling passages in complex fin structures. Background technique [0002] Existing aero-engine turbine guide blades work under high temperature and high pressure conditions, and the temperature of the gas flowing through the blade exceeds the tolerance of its material. In order to make it meet the working requirements, the blade needs to be cooled. Fins and spoiler columns are added to the internal cooling channel of the blade. The best manufacturing method of the existing turbine blade is investment casting without margin. The process mainly includes the design and manufacture of core molds. , the time and labor costs are high, and due to the limitation of the technological level, the fins usually adopt simple and regular structures such as semicircles and triangles, and are limited to individual orientations, and the effect of disturbing ...
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IPC IPC(8): F01D9/02F01D25/12
CPCF01D9/02F01D25/12F05D2260/221F05D2260/22141
Inventor 濮睿德李文宇
Owner BEIJING SNECMA SAIC TURBOTECH CO LTD