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对压缩机级联的尖端泄漏损失机制的研究,使用增强延迟脱离模拟方法
Shiyan Lin1, Ruiyu Li2, Limin Gao1
1School of Power and Energy, Northwestern Polytechnical University, Xi'an 710072, China.
Entropy (Basel, Switzerland)
|April 26, 2024
概括
本研究使用增强延迟脱离模拟 (EDDES) 和Liutex方法分析了压缩机尖端泄漏流量. 它揭示了复杂的互动,并量化了空气动力学损失,显示二次流量损失随着撞击角度显著增加.
科学领域:
- 空气动力学 航空动力学
- 流体力学 流体力学 流体力学
- 轮机的机械设备
背景情况:
- 尖端泄漏流量显著影响压缩机空气动力学损失和效率.
- 了解尖端区域的损失机制对于高性能压缩机设计至关重要.
研究的目的:
- 调查高负载悬臂定位器级联的尖端区域的损失机制.
- 分析撞击角度对空气动力学损失和结构的影响.
主要方法:
- 使用增强延迟独立模拟 (EDDES) 进行高保真流场分析.
- 利用Liutex方法研究尖端区域的状结构.
- 进行了生成率分析,以量化损失来源.
主要成果:
- 确定了尖端泄漏 (TLV),通道 (PV) 和诱导 (IV).
- 观察到IV,PV和低能流体之间的相互作用,在特定的冲击角度形成"三形"混合.
- 量化损失来源:端壁,叶片形状,后继和二次流量损失.
结论:
- 损失来源因发生角度而异,二次流量损失在较高的角度变得占主导地位 (47%在i=8°).
- 发生角的增加导致绝对损失的增加和二次流量损失的比例的增加.
- 该研究提供了对尖端泄漏流体物理和压缩机损失贡献的见解.
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