Gas compressor stability boundary prediction method and device under air inlet distortion condition and medium

Abstract

The invention provides a method, equipment and medium for predicting the stability boundary of an air compressor under the condition of air inlet distortion, which comprises the following steps: calculating a blade domain by adopting a distributed force source volume force model, calculating a non-blade domain by adopting a Reynolds average method, giving a distortion condition required by a target condition by adopting an inlet boundary condition, and calculating the stability boundary of the air compressor under the condition of air inlet distortion. Therefore, the spatial distribution of the compressor load is obtained. According to the method, the flow stability is analyzed and predicted based on the understanding of the gas compressor load space distribution and the critical load, it is considered that when the load of the gas compressor existing area reaches the local critical load, instability can be triggered, and high prediction precision is achieved; in addition, due to the fact that the calculation method based on the distributed force source volume force model is adopted, rapid obtaining of the air compressor load space distribution under the air inlet distortion condition can be achieved, and therefore the efficiency of stable boundary prediction work can be greatly improved.

Description

technical field [0001] The invention relates to the field of aero-engines, in particular to a method, equipment and medium for predicting the stability boundary of a compressor in the case of intake distortion. Background technique [0002] As one of the core components of an aero-engine, the compressor plays a decisive role in the performance and stability of the engine. If the flow instability of the compressor occurs, the performance of the aero-engine will be reduced at the slightest, and the flight accident will be directly caused at the severest level, which will bring serious consequences. With the continuous pursuit of high thrust-to-weight ratio and high efficiency of the engine, the design load of the compressor part continues to increase, the flow complexity continues to increase, and the problem of flow stability is becoming increasingly prominent. In addition, since the aero-engine does not always work under uniform air intake conditions during actual operation...

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Problems solved by technology

[0004] However, the stability theory model method greatly simplifies the geometry and flow field of the compressor when establishing the model, and the accuracy of its prediction is difficult to guarantee under the requirements of refined design at this stage

For the numerical simulation method, the practice of judging the stability of the flow field through the convergence of the steady calculation lacks a theoretical basis, and often makes an optimistic estimate of the stability boundary. For the prediction problem, it is necessary to carry out the full-circle unsteady numerical simulation of the integration of the inlet port / compressor, and the consumption of computing resources and time for this work is unbearable in engineering applications

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