| 一种涡轮排气蜗壳的优化设计 |
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| 引用本文： | 黄恩德,楚武利,董玮.一种涡轮排气蜗壳的优化设计[J].航空动力学报,2017,32(2):455-461. |
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| 作者姓名： | 黄恩德 楚武利 董玮 |
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| 作者单位： | 1.西北工业大学 动力与能源学院，西安 710129 |
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| 基金项目： | 国家自然科学基金（51576162，51236006） |
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| 摘 要： | 为了改善涡轮排气蜗壳的排气效果，选取一种箱式蜗壳为原始计算模型，通过数值模拟研究了该排气蜗壳的气动性能，揭示了蜗壳内部流动损失的主要来源，在不改变其几何尺寸的前提下，提出了一种蜗壳的分流层改型设计，并与两种一般改型方式的效果作比较.数值计算结果表明:在设计工况下，分流层改型设计可使排气蜗壳的总压损失系数最多降低32.12%，静叶恢复系数最多提高48.73%，其效果好于扩压结构弧线改型，但弱于蜗壳壁面轮廓型线改型，在此基础上揭示了分流层设计改善蜗壳气动性能的机理.
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| 关 键 词： | 排气蜗壳 分流层 改型 流动损失 气动性能 |
| 收稿时间： | 2015/6/3 0:00:00 |
An optimal design of a turbine exhaust volute |
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| HUANG En-de,CHU Wu-li,DONG Wei.An optimal design of a turbine exhaust volute[J].Journal of Aerospace Power,2017,32(2):455-461. |
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| Authors: | HUANG En-de CHU Wu-li DONG Wei |
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| Abstract: | In order to improve the aerodynamic performance of a gas turbine exhaust volute,a collection-shell type volute was numerically studied and the source of flow losses was presented.Based on that,a flow separation layer design was put forward without changing the geometry size of the exhaust volute,and the comparisons of the effects between this design and two common methods were carried out.The numerical simulation results show that the flow separation layer design can at most decrease the total pressure loss coefficient by 32.12 ％ and increase the static pressure recovery coefficient by 48.73 ％ on the design point;this is better than the result of adjusting arc lines of the diffusing structure,but worse than that of the wall profile modification of the collector.Accordingly,the mechanism of how the separation layer can improve the aerodynamic performance of the volute was revealed. |
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| Keywords: | exhaust volute separation layer modification flow losses aerodynamic performance |
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