Gas compressor runner design method based on air entraining rate

Abstract

The invention provides an air-entraining-rate-based air compressor flow channel design method, which is used for adapting to flow channel linear optimization of a multi-stage air compressor of which the air-entraining rate is changed, and comprises the following steps: sequentially executing a round of air compressor flow channel optimization for each air-entraining position in the direction from an inlet to an outlet of the air compressor, comprising the following steps: acquiring an inherent air entraining rate and a target air entraining rate of a current air entraining position; blade end points of all rear-stage blades at the current air entraining position are determined as flow channel control points of current air compressor flow channel optimization; the radial position and the axial position of each flow channel control point are determined according to the inherent air entraining rate, the target air entraining rate and the initial position of each flow channel control point, and the radial position and the axial position of each flow channel control point serve as the initial positions of the corresponding flow channel control points in the next round of gas compressor flow channel optimization; and based on the current radial position and the axial position of each flow channel control point after the flow channel optimization of the gas compressor is executed on all the gas entraining positions, the optimized flow channel line type of the gas compressor is obtained.

Description

technical field [0001] The invention relates to the field of aerodynamic design of a compressor, in particular to the field of design of a flow channel profile of a compressor considering the influence of bleed air. Background technique [0002] The air system of an aircraft engine is critical to the safe and efficient operation of the aircraft and engine. Compressor is a component in aero-engines that uses high-speed rotating blades to do work on the air to increase air pressure. According to the different working states of the aircraft and the engine, the air system bleeds air from different stages of the engine compressor to lead out air with appropriate pressure and temperature for cabin air conditioning and pressurization, wing thermal anti-icing, and engine inlet anti-icing As well as the cooling of engine hot end components such as the combustion chamber and turbine. Bleed air is a necessary link to ensure the normal operation of the engine and meet the needs of air...

AI Technical Summary

Problems solved by technology

When the bleed air volume of the middle stage of the compressor increases, the air flow rate of the front stage will increase, and the flow coefficient will increase accordingly. The flow rate decreases, the flow coefficient decreases, and the bleed air causes circumferential and radial distortions in the total pressure of the intermediate stage of the compressor, which deteriorates the working conditions of the subsequent stage of the compressor, making the latter stage reach the limit load prematurely, resulting in surge, and then Reduced compressor stability margin

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