Method for predicting characteristics of gas compressor according to design indexes

Abstract

The invention relates to a method for predicting characteristics of a gas compressor according to design indexes, and belongs to the field of gas compressor characteristic prediction. The method comprises prediction of characteristic parameters of peak efficiency points of all the isotactic speed lines and prediction of continuation of all the isotactic speed lines towards a near surge area and a near blockage area. Data input in the prediction process is only compressor design indexes (design point pressure ratio and efficiency), and compressor blade profile data are not needed. According to the design point pressure ratio, three coefficients are constructed, firstly, the peak efficiency point characteristics of each isorotation speed line are predicted, and then characteristic lines are expanded to a surge boundary and a blockage boundary respectively. The formulas and parameters used in the method are derived from mining of historical gas compressor characteristic data. The prediction method provided by the invention can be used for predicting the performance of an axial flow compressor and a centrifugal compressor, is particularly suitable for predicting the performance of the compressor when no blade profile data exists in the initial stage of the overall design of a gas turbine and an aero-engine, and is simple and convenient in calculation and relatively high in precision.

Description

technical field [0001] The invention belongs to the field of compressor characteristic prediction, and relates to a compressor performance prediction method, in particular to a compressor characteristic prediction method under the condition of only relying on design indexes without compressor blade profile information. Background technique [0002] The compressor is an important part of the gas turbine, used to compress the incoming gas, and is widely used in the fields of aviation power, ship power and thermal power generation. The characteristic diagram of the compressor is the main representation of the aerodynamic performance of the compressor in the full operating range, and is the key basis for the actual operation of the aero-engine and the gas turbine. The relationship between the dimensionless normalized flows is generally drawn as two graphs containing several constant speed lines, each constant speed line takes the converted flow rate as the independent variable, ...

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Problems solved by technology

[0004]Currently, compressor performance prediction is mostly based on the interpolation value of the existing characteristic map or extrapolation to the speed range not included in the characteristic map, or based on the The positive and negative design of the airfoil is carried out, and then the characteristics are obtained through the numerical calculation of the flow field, which requires a large amount of calculation

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