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进口雷诺数和湍流度对压气机叶栅流动特性影响

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针对高空条件下，无人机发动机的压气机气动性能明显下降的问题，本文以某高亚声速压气机叶型V103为研究对象，采用数值模拟方法研究了3 种雷诺数(Re=1。5×105，4。5×105，1。2×106)条件下，不同来流湍流度(Tu=1%，3%，5%，6%，7。5%，10%)对压气机叶栅内部流动特性的影响，分析了流动分离和转捩之间的变化关系，以及由此引起的叶型损失变化规律。研究结果表明:当湍流度不变时，随着雷诺数减小，分离泡长度增加，但分离点位置不变;当雷诺数不变，湍流度减小，层流分离点位置会提前，并且前移现象在低雷诺数下更明显;当湍流度增加，叶片表面分离泡消失，但损失仍然呈现出随着湍流度增加而增大的趋势;在不同雷诺数条件下，都存在一个对应于最小叶型损失的来流湍流度，且该湍流度随着雷诺数的减小而略有增大。本文为修正低雷诺数条件下压气机叶型损失模型和发展预测压气机高空低雷诺数效应的数值模型提供理论指导。
Influence of inlet Reynolds number and turbulent intensity on the flow mechanism in compressor profiles
To address the problem of decreased aerodynamic performance of unmanned aerial vehicle engine compres-sors at high altitudes,the V103 subsonic compressor blade profile is selected for a numerical study.This study inves-tigates the effects of different inflow turbulence levels(Tu=1%,3%,5%,6%,7.5%,10%)on the internal flow characteristics of the compressor cascade under three Reynolds numbers(Re=1.5×105,4.5×105,1.2×106).The re-lationship between flow separation and transition and the variation in blade profile loss caused by these factors are an-alyzed.The results indicate that when the turbulent intensity remains constant,the length of the separation bubble in-creases with a decrease in the Reynolds number,while the position of the separation point remains unchanged.When the Reynolds number remains constant,the laminar separation point moves forward as the inlet turbulent intensity de-creases.This phenomenon becomes more pronounced under low Reynolds number conditions.When the inlet turbu-lent intensity increases,the separation bubble on the blade surface disappears,but the loss continues to increase.Under different Reynolds number conditions,there exists an inflow turbulence corresponding to the minimum profile loss,and this turbulence increases slightly as the Reynolds number decreases.This paper provides theoretical guid-ance for modifying the compressor profile loss model at low Reynolds numbers and developing a numerical model to predict the compressor's performance at high altitudes with low Reynolds numbers.

low Reynolds numberinlet turbulent intensityflow separationboundary layer separationflow transi-tionblade profile lossnumerical simulationcompressor cascadeboundary layer

杜文海、陈珂、彭旻扬、王硕琨、张燕峰

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北京石油化工学院 机械工程学院,北京 102617

中国电建集团 北京勘测设计研究院有限公司,北京 100024

国家电投集团 科学技术研究院有限公司,北京 100034

中国科学院 工程热物理研究所,北京 100190

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低雷诺数 进口湍流度 流动分离 边界层分离 转捩 叶型损失 数值模拟 压气机叶栅 表面边界层

国家自然科学基金项目北京市教委科技一般项目

52076015KM201910017007

2024

10.11990/jheu.202210025

哈尔滨工程大学学报
哈尔滨工程大学

哈尔滨工程大学学报

CSTPCD北大核心
影响因子：0.655
ISSN：1006-7043
年,卷(期)：2024.45(8)