Turbine air cooling blade

Abstract

The invention belongs to the field of an aero engine, in particular to a turbine air cooling blade. An inner cavity is divided into by a front cavity 2 and a rear cavity 3, the front cavity 2 is cooled by air supplied by an upper end 4 and a lower end 5, multiple rows of exhaust membrane holes 7 are reserved on a front edge 6 of the cooling blade, and a plurality of scale-shaped cooling structure units are arranged on the surface of the blade. Compared with a conventional cooling structure, the air cooling blade with the scale-shaped cooling structure units is higher in cooling efficiency, lower in temperature on the outer surface and capable of bearing higher temperature load, and under the same working condition, utilization amount of cooling air can be reduced, and efficiency of an engine can be improved. Since a scale-shaped cooling structure body is separated from scales, the scale-shaped cooling structure body is less influenced by gas, lower in temperature and capable of bearing high mechanical load, and on the other hand, the scale-shaped cooling structure body can be thinner and consume fewer cooling air, so that by the air of the turbine blade in scale-shaped cooling structure, performance and efficiency of the engine can be improved.

Description

technical field [0001] The invention belongs to the field of aero-engines, in particular to a turbine air-cooled blade. Background technique [0002] Improving the gas temperature before the turbine, continuously improving the cooling structure, improving the cooling efficiency of the blades, and reducing the consumption of cooling air have always been an important part of the development plan of foreign aero-engines, and are the key technologies for the development of high thrust-to-weight ratio engines. [0003] The traditional cooling method of modern domestic aero-engine turbine blades is mainly composite cooling composed of air film cooling, impingement cooling, rough ribs and spoiler enhanced cooling. Design requirements, with the development of aero-engine technology, higher requirements are put forward for the development of turbine blade cooling technology, and new high-efficiency cooling structure turbine blades must be adopted. [0004] The United States, the Uni...

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Problems solved by technology

[0004] The United States, the United Kingdom, Russia and other countries have successively developed new types of high-efficiency turbine cooling blades, including new turbine blades such as "ultra-cooled blades", "cast cold blades", and "cast laminate blades". These blades all have a double-wall structure. Features, high cooling efficiency, but the processing is difficult, requiring precision casting technology, but the blade processing and manufacturing department does not yet have this technology

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