Method and device for estimating aerodynamic performance of multistage axial flow compressor

Abstract

The invention provides a method and device for estimating aerodynamic performance of a multistage axial flow compressor. The method comprises the following steps that first characteristic line families and first complete machine characteristic lines of all stages in the design state of the compressor are obtained in advance, and each first characteristic line family comprises a plurality of firstcharacteristic lines under the conversion rotating speed condition; the reserved-stage characteristic line families in the state, deviating from the design state, of hardware in the compressor are obtained, and each characteristic line family comprises a plurality of characteristic lines at a conversion rotating speed; the second complete machine characteristic line in the state, deviating from the design state, of the hardware in the compressor is obtained; and the first complete machine characteristic line is compared with the second complete machine characteristic line to obtain the influence of deviating from the design state of the hardware. The method and the device provided by the invention have higher estimation efficiency and higher estimation accuracy.

Description

technical field [0001] The invention mainly relates to the design and test verification of an aero-engine or a gas turbine, in particular to a method and device for estimating the aerodynamic performance of a multi-stage axial flow compressor. Background technique [0002] The aerodynamic performance of an axial flow compressor is a set of extremely important parameters in the process of design, test verification, and service of an aero-engine or a gas turbine. This set of parameters can be used to evaluate the quality of the design of the compressor, monitor whether the working status of the compressor is normal, and analyze the faults that occur during the working process of the compressor, etc. [0003] In particular, during the development (design and test verification) of an aeroengine or gas turbine axial compressor, in many cases, it is necessary to predict and analyze the influence of certain influencing factors on the aerodynamic performance of the compressor. Thes...

AI Technical Summary

Problems solved by technology

To obtain a complete set of characteristic lines at different speeds, the time-consuming is multiplied

As a result, the estimated results cannot be obtained in time during the actual compressor development or engineering problem handling, which affects work efficiency

[0006] 2. The accuracy of the estimated results is low

In addition, the CFD simulation of the whole machine generally has the situation that the calculation error accumulates step by step, and the distribution relationship of the total pressure ratio of the compressor between the stages is quite different from the test. The more stages of the compressor, this phenomenon is about serious.

[0007] 3. Unable to accurately obtain the initial surge level

However, due to the large error in the distribution relationship of the total pressure ratio between the stages in the CFD simulation of the whole machine, it cannot truly reflect the actual working status and pressure ratio of each stage, and thus cannot accurately obtain the real first surge level.

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