A Passive Method to Control Combustion Instabilities with Perforated Liner  

作　　者：Li Lei Guo Zhihui Zhang Chengyu Sun Xiaofeng 

机构地区：[1]School of Jet Propulsion,Beijing University of Aeronautics and Astronautics,Beijing 100191,China

出　　处：《Chinese Journal of Aeronautics》2010年第6期623-630,共8页中国航空学报(英文版)

基　　金：National Natural Science Foundation of China (50890181);Aeronautical Science Foundation of China (2009ZB51)

摘　　要：The effectiveness of perforated liner with bias flow on the control of combustion instability is investigated. Combustion instabilities result from the coupling between acoustic waves and unsteady combustion heat release. Sometimes the phenomenon happens in afterburners of aeroengine and rocket engine, and it always causes damage to flame holders, liner seetions and other engine components. Passive methods, such as perforated liner, are often used to suppress such instabilities in application. In this article, first, a burner testbed is built in order to study the characteristic of this phenomenon. The unstable frequencies and unsta- ble area are investigated experimentally. Then an analytical model, based on "transfer element method", is developed and the numerical results are compared with those from experiments. At last the perforated liner is applied to the burner to suppress the instabilities. The results show that the sound pressure can be greatly reduced by the perforated liner.The effectiveness of perforated liner with bias flow on the control of combustion instability is investigated. Combustion instabilities result from the coupling between acoustic waves and unsteady combustion heat release. Sometimes the phenomenon happens in afterburners of aeroengine and rocket engine, and it always causes damage to flame holders, liner seetions and other engine components. Passive methods, such as perforated liner, are often used to suppress such instabilities in application. In this article, first, a burner testbed is built in order to study the characteristic of this phenomenon. The unstable frequencies and unsta- ble area are investigated experimentally. Then an analytical model, based on "transfer element method", is developed and the numerical results are compared with those from experiments. At last the perforated liner is applied to the burner to suppress the instabilities. The results show that the sound pressure can be greatly reduced by the perforated liner.

关 键 词：combustion instabilities combustors perforated liner bias flow resonating frequency 

分 类 号：TK16[动力工程及工程热物理—热能工程]