Offset hole row and cylindrical hole row combined cooling structure for corrugated heat shield

Abstract

The invention discloses an offset hole row and cylindrical hole row combined cooling structure for a corrugated heat shield, and belongs to the technical field of cooling of aero-engine combustion chambers. The cooling structure comprises a corrugated heat shield plate, and offset gas film hole rows and cylindrical hole rows which are arranged on the corrugated heat shield plate, wherein the corrugated heat shield plate is of a cylinder structure, a fuel gas channel is formed in the corrugated heat shield plate, an annular channel composed of the cylindrical corrugated heat shield plate and acombustion chamber outer cylinder forms a cold air channel, each corrugation of the corrugated heat shield plate comprises a windward side and a leeward side, 2-3 rows of offset air film hole rows areuniformly distributed on the windward side along the axial direction of the cylindrical corrugated heat shield plate, 3-4 rows of cylindrical hole rows are uniformly distributed on the leeward side along the axial direction of the cylindrical corrugated heat shield plate, the structure is formed by arranging a plurality of offset air film hole rows on the mainstream leeward side of a corrugated plate and arranging a plurality of cylindrical air film hole rows on the windward side, and the structure can be used for a turbofan engine afterburner or a ramjet engine combustor.

Description

technical field [0001] The invention belongs to the technical field of cooling of an aero-engine combustion chamber, and in particular relates to a combined cooling structure of an offset hole row and a cylindrical hole row for a corrugated heat shield. Background technique [0002] In order to meet the needs of short-distance take-off and fast maneuvering, modern military aero-engines are often equipped with afterburners. As the simplest type of air-breathing engine, the ramjet engine has attracted the attention of many countries in the performance research of its combustion chamber due to its simple structure and superiority in the supersonic range. The structures of the above two combustion chambers are similar, but their harsh working conditions have brought challenges to the design research. Specifically, on the one hand, the temperature of the gas in the combustion chamber rises rapidly to 2100K or even higher after ignition, which greatly exceeds the temperature resi...

AI Technical Summary

Problems solved by technology

At present, most of the research is still in the form of uniform and densely distributed holes on the corrugated board. A large amount of cold air fails to exert its due performance. The air film holes on the corrugated surface have not been optimized, and there is room for optimization.

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