Efficient cooling blade for gas turbine engine

Abstract

The invention discloses an efficient cooling blade for a gas turbine engine. The efficient cooling blade comprises a blade body, an end wall and a tenon head, wherein the blade body is a hollow cylinder, and comprises a pressure surface and a force absorbing surface; first to third bridging beams are sequentially arranged from the front edge of the blade to the tail edge of the blade in the blade body for dividing the inner part of the blade body into a gas cavity, and first to third channels; a first abnormally formed gas film hole which communicates with the gas cavity is formed in the force absorbing surface; a second abnormally formed gas film hole which communicates with the gas cavity, a third abnormally formed gas film hole which communicates with the second channel and a fourth abnormally formed gas film hole which communicates with third channel are formed in the pressure surface; an impact jet hole is formed in the first bridging seam; a spraying hole is formed in the front edge of the blade; and a heat exchange structure is arranged in each of the gas cavity, a connecting channel for the second channel and the third abnormally formed gas film hole, and a connecting channel for the third channel and the fourth abnormally formed gas film hole. While efficient inner cooling is performed on the blade, the disturbance effect, on cooling gas-flow disturbance, of the heat exchange structure is brought into play, and the protective effect of gas film cooling is strengthened.

Description

technical field [0001] The invention relates to the field of local heat exchange with high heat flux density in aviation, aerospace, power machinery, etc., and in particular to a high-efficiency cooling blade of a gas turbine engine. Background technique [0002] In modern high-performance gas turbine engines, increasing the turbine inlet temperature is an effective measure to increase the thrust-to-weight ratio and reduce fuel consumption. However, as the gas temperature at the turbine inlet increases, the heat load on the turbine blades will continue to increase. The temperature at the turbine inlet of a modern gas turbine engine can reach 1900K, which has exceeded the allowable temperature of the existing metal materials. Therefore, only by effectively cooling the turbine blades to reduce the temperature of the turbine blades in the working state can it be used normally and safely. Work, and meet certain life requirements. In addition, turbine blades (rotor blades) are ...

AI Technical Summary

Problems solved by technology

[0005] The technical problem to be solved by the present invention is to provide a high-efficiency cooling blade for a gas turbine engine in view of the defects in the background technology that the heat load on the surface of the turbine blade is too high and threatens the safe and stable operation of the gas turbine engine

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