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叶尖泄漏掺混损失影响因素分析
引用本文:邵卫卫,季路成,程荣辉,黄伟光.叶尖泄漏掺混损失影响因素分析[J].航空动力学报,2007,22(10):1722-1729.
作者姓名:邵卫卫  季路成  程荣辉  黄伟光
作者单位:1. 中国科学院,研究生院,北京,100080;中国科学院,工程热物理研究所,北京,100080
2. 中国科学院,工程热物理研究所,北京,100080
3. 中国燃气涡轮研究院,成都,610500
摘    要:借鉴Denton不可压叶尖泄漏损失的理论分析,推导出可压缩流动中叶尖泄漏掺混损失基本关系式,其集中反映了尖区叶表压强、叶尖间隙、泄漏流流量系数及总损失系数影响.在仅考虑泄漏掺混损失情况下,数值分析了叶尖基元负荷、间隙、泄漏流量系数整体水平及其弦向分布等因素对叶尖泄漏掺混损失的影响.结果展示了各因素对叶尖泄漏掺混损失的作用及机理.最后提出一个重要的组合参数,反映了叶片尖部载荷和叶尖间隙的流向分布对叶尖泄漏掺混损失的综合影响.

关 键 词:航空、航天推进系统  叶轮机  风扇/压气机  涡轮  叶尖泄漏  可压缩流动  掺混损失
文章编号:1000-8055(2007)10-1722-08
收稿时间:2006/9/21 0:00:00
修稿时间:2006年9月21日

Analysis of influential factors to tip leakage mixing loss
SHAO Wei-wei,JI Lu-cheng,CHENG Rong-hui and HUANG Wei-guang.Analysis of influential factors to tip leakage mixing loss[J].Journal of Aerospace Power,2007,22(10):1722-1729.
Authors:SHAO Wei-wei  JI Lu-cheng  CHENG Rong-hui and HUANG Wei-guang
Institution:Graduate School of Chinese Academy of Sciences, 100080, China;Institute of Engineering Thermophysics, Chinese Academy of Sciences, 100080, China;Institute of Engineering Thermophysics, Chinese Academy of Sciences, 100080, China;China Gas Turbine Establishment, Chengdu 610500, China;Institute of Engineering Thermophysics, Chinese Academy of Sciences, 100080, China
Abstract:A basic relational model for tip leakage mixing loss of unshrouded blades for compressible flow was derived from theoretical analysis of Denton.Relationship.It reflected the influential factors such as blade surface static pressure,chordwise distribution of tip clearance,discharge coefficient and total pressure loss coefficient in the tip region.While only the mixing loss of tip leakage was considered,numerical analysis was performed for the influence of basic load of tip,clearance,average level and chordwise distribution upon mixing loss.The results clearly indicate the governing actions and mechanisms of various factors against the tip leakage mixing loss.Finally, an important combination parameter was put forward to reflect the overall influence of blade loading and tip clearance distribution on the tip leakage mixing loss.
Keywords:aerospace propulsion system  turbomachinery  fan/compressor  turbine  tip leakage  compressible flow  mixing loss
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