Multistage compressor aerodynamic matching design method

Abstract

The invention relates to a multistage compressor aerodynamic matching design method, which is based on the principle of equal-outlet conversion flow and under the condition of keeping'constant isentropic efficiency ', an equal-outlet conversion flow line passing through a single-stage design working point is calculated and obtained; after a single-stage equal-outlet conversion flow line is obtained, a corrected single-stage design target is obtained along the equal-outlet conversion flow line through design system deviation correction, and then single-stage iterative design is carried out; when the three-dimensional design work of a certain specific level is specifically carried out, the two-dimensional total temperature, total pressure and airflow angle profile obtained in the design link S2 is used for the inlet condition of the level, so that the three-dimensional design result is consistent with the one-dimensional and two-dimensional design results, namely, all design links of the gas compressor are kept consistent. On the premise that the pneumatic layout design target of the whole compressor is met, single-stage design can be effectively stripped from multi-stage design work, pneumatic design of the single-stage compressor is completed on the premise that the whole pneumatic layout of the compressor is not affected, and therefore the design process of the compressor is optimized.

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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