Design Method of Pneumatic Matching for Multistage Compressor

Abstract

A multi-stage compressor aerodynamic matching design method, which is based on the principle of equivalent outlet conversion flow rate and under the condition of keeping "isentropic efficiency unchanged", calculates and obtains the equivalent outlet conversion flow line passing through the single-stage design working point; After the equal-outlet conversion flow line of the stage, through the deviation correction of the design system, along the equal-outlet conversion flow line, the revised single-stage design target is obtained, and then the single-stage iterative design is carried out; when carrying out the 3D design work of a specific stage, the The two-dimensional total temperature, total pressure, and air flow angle profiles obtained in the S2 design process are used for the stage inlet conditions, so that the three-dimensional design is consistent with the one-dimensional and two-dimensional design results, that is, the design links of the compressor are consistent. The present invention can effectively separate the single-stage design from the multi-stage design work on the premise of meeting the aerodynamic layout design target of the whole compressor, and complete the aerodynamic design of the single-stage compressor without affecting the overall aerodynamic layout of the compressor , thus optimizing the compressor design process.

Description

technical field [0001] The invention relates to the technical field of aero-engines, in particular to the aerodynamic field of high-pressure compressors of aero-engines, and more particularly to an aerodynamic matching design method for multi-stage compressors based on the principle of equivalent outlet conversion flow. Background technique [0002] The gas turbine uses continuous flowing gas as the working medium to drive the impeller to rotate at high speed, so as to convert the energy of the fuel into useful work. It is an internal combustion power machine that is essentially a rotating impeller heat engine. The air is inhaled from the external atmosphere, and compressed step by step by the axial flow compressor to increase the pressure, and the air temperature is also increased accordingly; the compressed air is sent to the combustion chamber and mixed with the injected fuel to generate high-temperature and high-pressure gas; then Then enter the turbine to expand and do ...

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Problems solved by technology

Obviously, above-mentioned existing literature all can't effectively solve the technical difficult problem existing at present

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