A curved double-wall double-swirl cooling structure for a high-temperature turbine blade leading edge

By designing a curved double-walled double-swirling cooling structure at the leading edge of the gas turbine blade, the problems of uneven cooling and excessive thermal stress at the blade leading edge are solved by utilizing swirling cooling and the double-walled structure, thus achieving efficient temperature control and improved safety.

CN116335770BActive Publication Date: 2026-06-26JIANGSU UNIV OF SCI & TECH
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
JIANGSU UNIV OF SCI & TECH
Filing Date
2023-02-17
Publication Date
2026-06-26

AI Technical Summary

Technical Problem

Existing cooling technologies cannot meet the increasing gas temperature requirements of the leading edge of gas turbine blades. Uneven cooling leads to excessive local thermal stress, reducing safe operating time.

Method used

A curved double-walled double-swirling cooling structure for the leading edge of a high-temperature turbine blade is designed, comprising inner and outer cooling chambers with a semi-cylindrical structure and a U-shaped connecting pipe. Combined with micro-flow channels and heat transfer-enhancing turbulence, a double-walled double-swirling cooling structure is formed, which utilizes swirling cooling to improve heat transfer intensity and temperature distribution uniformity.

Benefits of technology

It significantly improves the cooling performance of the blade leading edge, enhances heat transfer intensity and temperature distribution uniformity, reduces the amount of cooling air, and extends safe operating time.

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Abstract

The application discloses a curved surface double-layer wall double-cyclone cooling structure of a high-temperature turbine blade leading edge, which comprises an inlet nozzle, an outer cooling chamber, a U-shaped connecting pipeline, an inner cooling chamber and an outlet. A cooling medium is tangentially injected into the outer cooling chamber through the nozzle, forms a tangential outer cyclone flow along the wall surface to perform primary cooling, then the cooling gas is tangentially injected into the inner cooling chamber through the U-shaped connecting pipeline, forms a large-scale inner cyclone flow to perform secondary cooling, and the cooled medium flows out from the outlet arranged in the inner cooling chamber. The application applies the double-layer wall cooling structure to the high-temperature turbine blade leading edge, fully utilizes the space structure of the leading edge, generates the inner and outer layer two kinds of cyclone flows, has the advantages of high double-layer wall cooling and heat exchange intensity, flexible arrangement, uniform cyclone cooling and heat exchange distribution and high heat exchange intensity, and greatly improves the cooling performance of the turbine blade leading edge of the gas turbine and the aero-engine turbine.
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