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| 一种工程实用的多级轴流压气机特性二维数值计算方法 | |
| 引用本文： | 程荣辉,雷丕霓,刘波,周拜豪,周盛.一种工程实用的多级轴流压气机特性二维数值计算方法[J].航空动力学报,2007,22(6):955-960. |
| 作者姓名： | 程荣辉 雷丕霓 刘波 周拜豪 周盛 |
| 作者单位： | 1. 北京航空航天大学,能源与动力工程学院,北京100083;中国燃气涡轮研究院,成都610500 2. 中国燃气涡轮研究院,成都610500 3. 西北工业大学,动力与能源工程学院,西安710072 4. 北京航空航天大学,能源与动力工程学院,北京100083 |
| 摘 要： | 采用二维(轴对称)数学模型,应用流线曲率法求解多级轴流压气机特性.各种不同因素对落后角和损失的影响以分量的形式表示.该方法通过了大量试验数据的校核,具有较高的准确度.对一台多级轴流压气机的计算结果与试验数据的对比分析表明,该方法能较好地预测多级轴流压气机的特性和非设计工况下级间参数的分布. |
| 关 键 词： | 航空、航天推进系统 多级轴流压气机 流线曲率法 损失和落后角模型 特性 二维数值计算 |
| 文章编号： | 1000-8055(2007)06-0955-06 |
| 收稿时间： | 2006/9/11 0:00:00 |
| 修稿时间： | 2006年9月11日 |
A two-dimension numerical method for multi-stage axial compressor performance in engineering applications |
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| CHENG Rong-hui,LEI Pi-ni,LIU Bo,ZHOU Bai-hao and ZHOU Sheng.A two-dimension numerical method for multi-stage axial compressor performance in engineering applications[J].Journal of Aerospace Power,2007,22(6):955-960. | |
| Authors: | CHENG Rong-hui LEI Pi-ni LIU Bo ZHOU Bai-hao and ZHOU Sheng |
| Institution: | School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;Gasturbine Establishment of China, Chengdu 610500, China;Gasturbine Establishment of China, Chengdu 610500, China;School of Power and Energy, Northwestern Polytechnical University, Xi'an 710072, China;Gasturbine Establishment of China, Chengdu 610500, China;School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China |
| Abstract: | The multi-stage axial compressor performance was measured using a streamline curvature method based on two-dimension(axisymmetric) mathematical model.The influence of various factors on the deviation angle and loss was represented by components.After being verified through a number of experiment data,this method offers an extremely high accuracy.By comparing the calculated results and test data for a multi-stage axial compressor,this method demonstrates that it could assist in predicting the characteristics of multi-stage axial compressor and spanwise parameter distribution under off-design working conditions. |
| Keywords: | aerospace propulsion system multi-stage compressor streamline curvature method loss and deviation angle model performance two-dimension numerical calculation |
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