A continuous V-shaped rib guide structure applied to the semi-slit of the trailing edge of the turbine blade

Abstract

The invention relates to a continuous V-shaped rib diversion structure and a diversion method applied to the half-slit of the trailing edge of a turbine blade. Slit downstream wall, partition ribs, V-shaped ribs. The pressure surface of the turbine blade close to the trailing edge cuts off a part of the wall and forms multiple trailing edge half-slit structures with the partition ribs. After the cooling gas flows out from the outlet, a cooling gas film is formed on the half-slit wall and the downstream wall to isolate the high-temperature mainstream gas and reduce wall temperature. By arranging the V-shaped ribs on the downstream wall of the half-slit to create a turbulence effect on the cooling air film, the unevenness of the distribution of the air film downstream of the half-slit is significantly reduced, and the span-wise coverage and cooling efficiency of the cooling air film are improved to achieve the highest trailing edge. Reduction of temperature and temperature gradient. The present invention arranges a V-shaped rib structure on the downstream wall of the half-slit, has the characteristics of simple structure, convenient processing and good cooling effect, and can be applied to various half-slit structures of the trailing edge of turbine blades.

Description

Technical field [0001] The present invention belongs to the field of gas turbine blade cooling technology, and in particular, there is a consecutive V-type rib extension structure applied to the tail edge of the turbine blade. Background technique [0002] Gas turbine engine is a thermal power device based on Bretton cycle, relying widely in modern military and industrial depending on its powerful output power and high heat efficiency. Experience shows that under the premise of the engine size, the turbine import temperature is increased by 56K, and the thrust of the gas turbine can increase by 8-13%, and the cycle efficiency can be increased by 2-4%. At present, the turbine temperature of the advanced air engine has exceeded 2000K, while the temperature limit of the turbine blade material is much smaller than the turbine inlet temperature, so high efficiency cooling techniques must be used to ensure its normal operation. Both sides of the tail of the turbine blade are affected b...

AI Technical Summary

Problems solved by technology

The mechanism of the above two existing technologies is to enhance the convective heat transfer coefficient and heat transfer area at the wall through the spoiler structure, thereby increasing the heat transfer between the upstream air film and the blade wall to reduce the temperature of this part of the wall. , however, for the downstream blade wall of the turbine blade trailing edge half-slit, this part of the blade wall is not covered by air film due to the blocking effect of the upstream half-slit rib

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