变几何径向透平损失模型及其分析

刘晓澜; 谷传纲; 杨波; 王彤; 邢卫东; 张继忠

变几何径向透平损失模型及其分析

1.
上海交通大学动力机械及工程教育部重点实验室, 上海 200030
2.
柴油机高增压技术国防科技重点实验室, 大同 037036

基金项目: 国家自然科学基金项目(50676054)

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出版历程
- 收稿日期: 2006-04-21
- 修回日期: 2006-10-30
- 刊出日期: 2007-05-28

Loss models and loss analysis of variable geometry radial inflow turbine

1.
Key Laboratory for Power Machinery and Engineering of the Ministry of Education of China, Shanghai Jiao Tong University, Shanghai 200030, China
2.
National Laboratory of Diesel-Engine Turbocharging Tech.Datong 037036, China

摘要

摘要: 基于99 mm叶轮实验, 分析了变几何径向透平静叶的各种损失以及不同的损失模型.给出了变几何透平静叶冲角损失的定量分析.通过计算对比不同静叶喉部宽度下叶道边界层摩擦损失, 验证了Glass-man模型在计算叶片流道损失时, 与试验结果是相符的.基于NASA损失模型分析了径向透平静叶的尾缘损失, 损失随着出口边厚度呈线性增加, 减小出口边厚度是减小尾缘损失的有效方法.
- 航空、航天推进系统 /
- 变几何径向透平 /
- 静叶 /
- 损失模型
Abstract: Based on the experimental data of a 99 mm rotor,various losses and loss models of the stator of variable geometry radial inflow turbine(VGT) was analyzed.Also,a quantitative analysis was performed for the incidence loss in VGT's stator.When calculating the blade passage loss,Glassman loss model was proved to match the test results by calculating comparatively the boundary layer friction loss in blade row with different stator throat widths.The trailing-edge loss of radial inflow turbine stator was discussed based on the loss models of NASA,showing that the loss increases linearly with the trailing edge thickness.Thus,an efficient method of reducing trailing-edge loss is to cut down the trailing edge thickness.
- aerospace propulsion system /
- variable geometry radial inflow turbine /
- stator /
- loss model

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参考文献(15)

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