Microchannel heat exchanger core applicable to gas turbine system

Abstract

The invention provides a microchannel heat exchanger core applicable to a gas turbine system. Heat exchange core plate sheets of the microchannel heat exchanger core are annular and are provided withflow channels formed by etching or machining; the shape of each flow channel is elliptical; the depth of each flow channel is in millimeter level; the equivalent diameter of each flow channel is 1-2 mm; the two heat exchange core plate sheets are assembled into a heat exchange unit; and the microchannel heat exchanger core applicable to the gas turbine system is formed by fixedly connecting a plurality of the heat exchange units through diffusion welding. The microchannel heat exchanger core applicable to the gas turbine system solves the technical problems that the unit thrust of a traditional gas turbine increases along with the increase of the compressor pressure ratio, the increase of the compressor pressure ratio under a high-load condition can lead to overheating of an air inlet system, and even the temperature of the system exceeds the material limit of the existing gas turbine. According to the microchannel heat exchanger core applicable to the gas turbine system, on the basisof an original printing plate-type heat exchanger art, the circular plate sheets are adopted, and a cold and hot side plate sheet flow channel structure is redesigned, so that a cylindrical microchannel heat exchanger suitable for the gas turbine system is manufactured through diffusion welding.

Description

technical field [0001] The invention specifically relates to a microchannel heat exchanger core that can be used in a gas turbine system, and belongs to the technical field of heat exchange devices. Background technique [0002] The unit thrust of a traditional gas turbine increases with the increase of the compressor pressure ratio, but increasing the compressor pressure ratio under high load conditions will lead to overheating of the intake system, and even the problem that the system temperature exceeds the limit of existing gas turbine materials. Therefore, arranging high-efficiency heat exchangers in the air inlet to pre-cool to obtain ideal inlet air temperature and density has become a solution to break through the thrust bottleneck of gas turbines. Since the current typical layout of gas turbines mostly adopts shafting arrangement, the design and Manufacture a high-efficiency heat exchanger that is suitable for the shafting arrangement and can work stably under high ...

AI Technical Summary

Problems solved by technology

[0002] The unit thrust of a traditional gas turbine increases with the increase of the compressor pressure ratio, and increasing the compressor pressure ratio under high load conditions will cause the intake system to overheat, and even cause the system temperature to exceed the limit of existing gas turbine materials

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