Turbine blade with step gap cooling structure on pressure surface

Abstract

The invention discloses a novel gas air film cooling structure for an aircraft engine and a turbine guide blade of a gas turbine. The cooling structure comprises a blade basal body, an air film gap, a connecting rib and a step surface, and is characterized in that a step-shaped gap air film flow outlet structure is formed by an inner blade and an outer blade on the blade pressure surface basal body and the connecting rib, so that cooling air flows out in the tangential direction of the blade surface. The cooling flow outlet structure of a novel blade can form a uniform and consistent cooling air film on the blade surface; the air outlet air film is higher in stability; the vortex effect of cold air flowing out is weakened; the cooling air film is large in covering area and high in cooling efficiency; and meanwhile, the cooling air in the tangential direction is mixed with a high-temperature main flow, so that the pneumatic loss of the blade is reduced, and the blade has both high cooling efficiency and high-efficiency pneumatic performance. The structure also can enable the blade to be produced by a piece connecting structure, and can simplify the blade processing and maintenance process.

Description

technical field [0001] The invention relates to a novel cooling structure for high-temperature components of an aero-engine, in particular to a cooling structure suitable for blades of a turbine deflector. This structure not only has better cooling performance for the turbine guide blade, but also has higher aerodynamic efficiency than the traditional smooth blade shape in terms of aerodynamic performance. The gas turbine engine turbine guide adopting this cooling aerodynamic structure The blade can have a large performance advantage over conventional blades in terms of cooling performance and aerodynamic performance. Background technique [0002] Turbine blades are important hot-end parts of aero-engines, especially the guide blades are directly washed by the high-temperature gas at the outlet of the combustion chamber. At present, the temperature of the front inlet of advanced engines has reached about 2000K, which is 400K higher than the melting point of the metal materi...

AI Technical Summary

Problems solved by technology

Since the existing air film holes need to flow out from the cold air cavity through the cooling holes on the wall surface to the outside of the high temperature wall surface, they must pass through holes of a certain diameter on the high temperature wall surface, which means that the use of this structure will inevitably The outflow of the gas film has a flow perpendicular to the normal direction of the high-temperature wall surface, which will definitely generate a horseshoe vortex that causes cooling and gas mixing, which reduces the cooling effect of the cold air

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