Method for predicting dynamic stall process of aviation axial flow compressor under complex air inlet distortion

Abstract

The invention discloses a method for predicting dynamic stall process of an aviation axial flow compressor under complex air inlet distortion. The method comprises the steps that a blade wall fixing effect is described through a distributed force source, and a dynamic relation between a local blade element runner force source and an airflow parameter is effectively constructed based on a loss coefficient and a backward angle concept. The method has the capability of quantitatively describing the dynamic stall evolution process of the multi-stage axial flow compressor under complex air inlet distortion. Compared with a traditional two-dimensional calculation method and a high-order three-dimensional CFD calculation method, the method has the advantages that the calculation efficiency can be considered, and meanwhile, the aerodynamic instability characteristics of the aviation axial flow compressor under complex air inlet distortion disturbance including rotational flow and radial / circumferential space combination distortion characteristics are effectively reflected, and a technical support is provided for high-fidelity aerodynamic stability design of an advanced aero-engine.

Description

technical field [0001] The invention belongs to the technical field of numerical simulation of aero-engines, in particular to a method for predicting a dynamic stall process under complex intake distortion of an aero-axial flow compressor. Background technique [0002] The compressor is the basic component of the compression system of the gas turbine engine. The reverse pressure gradient of the viscous gas inside determines that it has the characteristics of aerodynamic instability, which directly affects the working reliability of the engine. With the gradual application of advanced technologies such as boundary layer intake engine layout and large-curvature S-curved inlet in the propulsion system of modern aircraft, the distortion of the flow field at the engine inlet is increasingly presented in the form of swirling flow and radial / circumferential space. Combination distortion is the characteristic three-dimensional unsteadiness, and its negative impact on the aerodynamic...

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Problems solved by technology

Scholars at home and abroad have developed various physical force models to analyze the initial process of aerodynamic instability of an aviation axial flow compressor under uniform air intake. The application potential of the

Chima has preliminarily constructed a three-dimensional unsteady numerical model for analyzing the dynamic stall process under compressor intake distortion based on the concept of the full body force model, but limited by the limitation of its source term modeling method, it can only simulate single-stage shaft Flow Compressor Simple Circumferential Total Pressure Distortion Intake Problem (Chima R V.A Three-Dimensional Unsteady CFD Model of Compressor Stability[R].ASME Paper, GT2006-90040.)

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