Turbine blade tail edge turbulence half-crack cooling structure with continuous straight ribs

Abstract

The invention discloses a turbine blade trailing edge turbulence semi-slit cooling structure with continuous straight ribs. The straight rib structure is applied to the wall surface of the trailing edge half-slit. The flow structure improves the convective heat transfer coefficient and heat transfer area of ​​the air film, and enhances the convective heat transfer intensity of the half-slit air film cooling, thereby improving the comprehensive cooling effect of the trailing edge of the blade. The turbulent half-split cooling structure is to cut off part of the wall surface on the pressure surface of the blade trailing edge, and retain the wall surface on the side of the suction side of the blade trailing edge and the spaced partition ribs to form a plurality of half-slit structures. The design is reasonable and the structure is simple; its characteristics are The cooling air flow is ejected from the cold flow outlet and covers the half-slit wall surface to form a cooling air film, which can effectively reduce the maximum and average temperature of the suction surface and avoid high-temperature ablation of the suction surface of the turbine blade. A simple straight rib structure is arranged on the half-slit wall surface, which has good heat transfer characteristics and good processability.

Description

technical field [0001] The invention belongs to the technical field of gas turbine blade cooling, and in particular relates to a turbine blade trailing edge turbulent half-slit cooling structure with continuous straight ribs. Background technique [0002] Increasing the turbine inlet temperature is an effective way to improve the thrust and efficiency of gas turbines, but the increase in turbine inlet temperature will cause the turbine blades to bear a greater heat load, and excessive temperature and thermal stress may cause the turbine blades to fail to work properly. The inlet temperature of modern gas turbine design has far exceeded the temperature resistance limit of the materials used, and complex cooling technology must be used to ensure the normal operation of the turbine under high temperature conditions. The trailing edge of the turbine blade is often a high-temperature part, and it is also most likely to be damaged by thermal corrosion. The design of its cooling st...

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Problems solved by technology

However, its research on film cooling is limited to the pressure surface of the turbine blade. At present, the film cooling efficiency of the pressure surface has reached nearly 0.98, which is close to the limit. It has not proposed a solution to the high temperature on the suction side.

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