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桥式槽处理机匣的扩稳机理研究
引用本文:黄书超,袁巍,韩乐.桥式槽处理机匣的扩稳机理研究[J].航空发动机,2018,44(1):44-51.
作者姓名:黄书超  袁巍  韩乐
作者单位:1. 北京航空航天大学航空发动机气动热力国家级重点实验室,北京100191; 2. 先进航空发动机协同创新中心,北京100191
基金项目:北京航空航天大学科研基金(YWF-15-GJSYS-018)资助
摘    要:利用数值模拟的手段对桥式槽处理机匣的失速机制和扩稳机理进行研究。通过与实壁机匣和全通槽处理机匣的对比分析结果表明:叶尖泄漏和叶片吸力面的分离均会引起叶尖通道堵塞,进而诱发失速。在实壁机匣情况下叶尖泄漏流堵塞叶尖通道是诱发失速的主要原因;全通槽和桥式槽处理机匣均能减弱叶尖泄漏流强度,但是全通槽处理机匣加剧了吸力面的分离,这造成了较大的效率损失;而桥式槽处理机匣能够通过改变抽吸区和喷气区的面积大小控制泄漏流和分离流引发的流道堵塞,从而在裕度提升和效率损失之间取得平衡。研究表明:喷气区面积越大,叶尖攻角越大,吸力面分离越强,压气机效率越低;抽吸区面积越大,泄漏流越弱,压气机的失速裕度越大。

关 键 词:压气机扩稳  失速机制  桥式处理机匣  喷气区  抽吸区  航空发动机

Investigation on Mechanisms of Stall Margin Improvement of Casing Treatment with Bridge Structure
Authors:HUANG Shuchao  YUAN Wei  HAN Le
Institution:1. National Key Laboratory of Science and Technology on Aero-Engine & Aero-Thermodynamics, Beihang University, Beijing 100191, China; 2. Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100191, China
Abstract:Numerical investigation was performed on the casing treatment with bridge structure to explore the mechanism of stall and margin improvement. The results show that both of the tip leakage flow and the separation flow on suction side of blade can block the rotor tip passage which will lead to stall. The tip leakage flow is the mean reason of stall in compressor with smooth shroud. Both of arc skewed slot and bridge casing treatment can reduce the strength of tip leakage flow. But arc skewed slot enhances the separation flow on suction side which lead to heavy efficiency loss. Bridge casing treatment can balance the margin improvement and efficiency loss by restrict both the tip leakage flow and the separation flow by changing bleeding area and injecting area. The enlargement of the injecting area will magnify the attack angle and enhance the separation flow on suction side and the efficiency loss. The bigger the bleeding area is, the better the tip leakage meliorated and the more the stall margin improved
Keywords:compressor stall margin improvement  stall mechanism  casing treatment with bridge structure  injecting area  bleeding area  aeroengine
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