Prediction method for dynamic stall process of aviation axial flow compressor under complex inlet distortion

Abstract

The invention discloses a method for predicting the dynamic stall process of an aviation axial flow compressor under complex intake distortion. The method describes the wall-solid effect of the blade through a distributed force source, and effectively constructs the force source of the flow path of the local blade element based on the concept of loss coefficient and lagging angle. The dynamic correlation with air flow parameters has the ability to quantitatively describe the dynamic stall evolution process of multi-stage axial flow compressors under complex intake distortion. Compared with the traditional two-dimensional calculation method and the high-order three-dimensional CFD calculation method, this method can effectively reflect the complex air intake distortion disturbance including swirling flow and radial / circumferential spatial combination distortion characteristics while taking into account the calculation efficiency. The characteristics of the aerodynamic instability of the flow compressor provide technical support for the high-fidelity aerodynamic stability design of advanced aero-engines.

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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