An Advanced Turbine Cooling Method Based on Porous Media and Supercritical State Fluid Circulation

Abstract

The invention discloses an advanced turbine cooling method based on porous media and super-critical state fluid circulation. According to the method, cooling channels in turbine blades are filled with porous media materials to increase the effective heat exchange area, and the effective heat exchange area depends on the shape, size and arraying direction of micro-pore structures; super-critical state fluid which is small in flowing resistance and high in heat exchange capacity serves as heat exchange media, so that the actual heat exchange amount is larger than the heat exchange amount in a conventional heat exchange model according to actual heat exchange requirements, and the number of cooling channels in the blades and the number of rib plates in the blades can be designed; according to the actual heat exchange requirements, the size, shape and arraying direction of the porous media can be designed; the blades can be machined integrally through a laser rapid forming technology or other high-energy-beam rapid forming technologies. The advanced turbine cooling method achieves direct and rapid forming, the technology is simple, and the structure, shape and position designability is high.

Description

technical field [0001] The invention relates to an advanced turbine cooling method based on porous media and supercritical state fluid circulation, which is mainly used to reduce the heat load of turbine blades and improve the working life of the turbine, and belongs to the technical field of aeroengines and high-speed rotating machinery. Background technique [0002] The temperature before the turbine determines the thermal efficiency of the aero-engine. The increase in the temperature before the turbine can improve the efficiency of the aero-engine, which can reduce the fuel consumption rate for civil aircraft and bring economic benefits, and can increase the thrust per unit area for military aircraft to obtain better maneuverability. However, the temperature in front of the turbine cannot increase infinitely, which is mainly limited by the material of the turbine. Excessive temperature will affect the strength, toughness and service life of the material. At present, the ...

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Problems solved by technology

The disadvantage of this cooling method is that the heat transfer area is small, and it can only be used in such as figure 1 The cooling channel shown in (b)① performs heat exchange around, and the effective heat exchange area is small; in addition, since the cold air comes from the air in the compressor, this will inevitably reduce the efficiency of the engine

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