离心压气机确定应力场分析

柳阳威; 黄卫兵; 刘宝杰

离心压气机确定应力场分析

1.
北京航空航天大学航空发动机气动热力重点实验室, 北京 100083
2.
中国人民解放军驻沈阳黎明发动机制造公司军事代表室, 沈阳 110043

基金项目: 国防基础预研项目(A0620060430);航空支撑科技基金(04B51004)

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出版历程
- 收稿日期: 2007-03-16
- 修回日期: 2007-06-08
- 刊出日期: 2008-03-28

Analysis of deterministic stresses in a centrifugal compressor

1.
National Key Laboratory on Aero-Engines, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
2.
Customer Representative of Shenyang Liming Engine Manufacturing Corporation, Shenyang 110043, China

摘要

摘要: 采用定常和非定常数值模拟技术,研究了某跨声离心压气机内的固有非定常流动.对比分析了定常流场和非定常时均流场之间的差别,着重分析了通道内确定应力的分布规律以及交界面确定应力的分布特点.结果表明,叶轮和扩压器中的确定应力在数值上相当,通道内的确定应力沿周向分布有较大的梯度、沿流向分布的总体趋势是从交界面向两侧迅速衰减,交界面处的确定应力和其空间相关项之间在数值上存在一定的偏差.
- 航空、航天推进系统 /
- 离心压气机 /
- 转静干涉 /
- 确定应力 /
- 数值模拟
Abstract: Steady and unsteady simulations were conducted in the investigation of deterministic unsteady phenomenon in a transonic centrifugal compressor with splitter blade.Results from the steady and unsteady simulations were compared firstly and then the distributions of deterministic stresses in the blade passage and the components of deterministic stresses based on velocity decomposition at the impeller/diffuser interface were studied in depth.The study indicates that the deterministic stresses in the impeller and diffuser are of similar magnitudes,and that the stresses in the passage have large gradients in circumferential direction and decrease rapidly from the interface towards two sides in flow direction,and also shows that the spatial correlations have some discrepancies with the deterministic stresses at the impeller/diffuser interface.
- aerospace propulsion system /
- centrifugal compressor /
- impeller/diffuser interaction /
- deterministic stresses /
- numerical simulation

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参考文献(13)

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