Continuous V-shaped rib flow guide structure applied to turbine blade trailing edge half slit

Abstract

The invention relates to a continuous V-shaped rib flow guide structure and method applied to a turbine blade trailing edge half slit. The structure comprises a blade trailing edge pressure face, a blade trailing edge suction face, a trailing edge half slit wall face, a slit downstream wall face, separation ribs and V-shaped ribs. Part of the wall face, close to the trailing edge, of the turbine blade pressure face is cut off, then the turbine blade pressure face and the partition ribs form a plurality of trailing edge half slit structures, cooling gas flows out of an outlet and then forms cooling gas films on the half slit wall face and the downstream wall face, high-temperature main flow gas is isolated, and the wall face temperature is reduced. The V-shaped ribs are arranged on the downstream wall face of the half slit to generate a turbulence effect on the cooling air films, so that the distribution nonuniformity of the downstream air films of the half slit is remarkably weakened,the spanwise covering effect and the cooling efficiency of the cooling air films are improved, and the highest temperature and the temperature gradient of the trailing edge are reduced. According to the continuous V-shaped rib flow guide structure and method applied to the turbine blade trailing edge half slit, the V-shaped rib structures are arranged on the downstream wall face of the half slit,the characteristics of simple structure, convenience in machining and good cooling effect are achieved, and the continuous V-shaped rib flow guide structure can be applied to various turbine blade trailing edge half slit structures.

Description

technical field [0001] The invention belongs to the technical field of gas turbine turbine blade cooling, and in particular relates to a continuous V-shaped rib flow guide structure applied to a half-split slit at the trailing edge of a turbine blade. Background technique [0002] Gas turbine engine is a thermal power plant based on Brayton cycle, which has been widely used in modern military and industry due to its strong output power and high thermal efficiency. Experience shows that under the premise of the same engine size, the thrust of the gas turbine can be increased by 8-13% and the cycle efficiency can be increased by 2-4% for every 56K increase in the turbine inlet temperature. At present, the temperature before the turbine of the advanced aero-engine has exceeded 2000K, while the temperature resistance limit of the turbine blade material is far less than the turbine inlet temperature, so efficient cooling technology must be adopted to ensure its normal operation. ...

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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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