针对分布式供能的市场开发了2MW的燃气轮机，本燃机采用压比位7：1的径流式涡轮。在本文中，研究了各种几何尺寸变化对涡轮性能的影响，其中包括叶轮的叶尖间隙、叶背间隙。除此之外，导风轮深切以及排风轮尾缘导圆的影响也进行了相关研究。最终，与分体式叶轮相关的几何特征也进行了相关分析。这些几何特征的分析方法主要采用计算流体力学的方法。部分的试验数据与整机测试中的性能数据进行了对比和验证。结果表明，对于本文的这种高落压比涡轮而言，排风轮的径向叶尖间隙、导风轮的轴向叶尖间隙，甚至包括深切导风轮的轮背间隙都对性能几乎没有影响。在全部的算例中，1%的间隙改变，仅仅导致约0.1%的性能恶化。这一发现与已有的低压比叶轮的结果十分不一致，这也意味着对于高压比叶轮存在不同的物理机理。
Abstract
A 2 MW gas turbine engine has been developed for the distributed power market. This engine features a 7:1 pressure ratio radial inflow turbine. In this paper, influences of various geometry features are investigated including turbine tip and backface clearances. In addition to the clearances, the effects of the inducer deep scallop and exducer rounded trailing edge are investigated. Finally, geometric features associated with a split rotor (separate inducer and exducer) are studied. These geometry features are investigated numerically using CFD. Part of the numerical results is also compared to experimental data acquired during engine test to validate the CFD results.
Results indicated that for this specific turbine, the influences of the exducer radial tip clearance, inducer axial tip clearance, and even scalloped blade backface clearance all have negligible influences on performance. In all cases, 1% increase in clearance only attributes to approximately a 0.1% lower efficiency. This finding is very different from former published papers with low pressure ratio turbines, indicating different flow physics apply for a turbine with a relatively high-pressure ratio.
关键词
radial turbine /
high pressure ratio /
scallop /
leakage /
clearance
{{custom_keyword}} /
Key words
radial turbine /
high pressure ratio /
scallop /
leakage /
clearance
{{custom_keyword}} /
{{custom_sec.title}}
{{custom_sec.title}}
{{custom_sec.content}}
参考文献
[1] Rodgers C., Review of mixed flow and radial turbine options. AIAA Paper, 1990, No. 90-2414.
[2] Jones A.C., Design and test of a small, high pressure ratio radial turbine. ASME Journal of Turbomachinery, 1996, 118(2): 362–370.
[3] Simonyi P.S., Boyle R.J., Comparison of a quasi-3D analysis and experimental performance for three compact radial turbines. AIAA Paper, 1991, No. 91-2128.
[4] He P., Sun Z.G., Chen H.S., Tan C.Q., Investigation of backface cavity sealing flow in deeply scalloped radial turbines. IMech Part G: Journal of Power and Energy, 2012, 226(6): 751–763.
[5] He P., Chen H.S., Tan C.Q., Aerothermal investigation of backface clearance flow in deeply scalloped radial turbines. Journal of Turbomachinery, 2013, 135: 021002.
[6] Futral S.M., Holeski D.E., Experimental results of varying the blade-shroud clearance in a 6.02-inch radial inflow turbine. NASA 1970, TND-5513.
[7] Dambach R., Hodson H.P., Huntsman I., An experimental study of tip clearance flow in a radial inflow turbine. ASME Journal of Turbomachinery, 1999, 121: 644–650.
[8] Dambach R., Hodson H.P., Tip leakage flow in a radial inflow turbine with varying gap height. AIAA Journal of Propulsion and Power, 2001, 17: 644–650.
[9] Dambach R., Hodson H.P., An experimental study of tip clearance flow in a radial inflow turbine. ASME Turbo Expo, 1998, 98-GT-467.
[10] Deng Q.H., Niu J.F., Feng Z.P., Tip leakage flow in radial inflow rotor of a microturbine with varying blade-shroud clearance. ASME Turbo Expo, 2007, GT2007-27722.
[11] Furukawa M., Inoue, M., Saiki, K., et al., The role of tip leakage vortex breakdown in compressor rotor aerodynamics. ASME Journal of Turbomachinery, 1999, 121: 469–480.
[12] Li W., Wang X., Zhang X.H., et al., Experimental and numerical investigations of closed radial inflow turbine with labyrinth seals. ASME Journal of Engineering for Gas Turbines and Power, 2018, 140: 102502.
[13] Liu H., Romagnoli A., Ricardo M.B., et al., Multi-injection turbine housing: a novel concept for tip-leakage improvement in radial turbines. ASME Turbo Expo, 2017, GT2017-63975.
[14] Huang W.L., Zhao H.J., Wang Z.H., Xi G., Numerical study on interaction of tip synthetic jet with tip leakage flow in centrifugal impeller. ASME Turbo Expo, 2018, GT2018-76330.
[15] Wang N.A., Sun X.J., Huang D.G., Design and analysis of a single-stage transonic centrifugal turbine for Organic Rankine Cycle (ORC). Journal of Thermal Science, 2020, 29(1): 32–42.
{{custom_fnGroup.title_cn}}
脚注
{{custom_fn.content}}
基金
This work was supported by the Key Programs of Chinese Academy of Sciences under Project No. ZDRW-CN-2017-2, Innovation Academy of Light-duty Gas Turbine with Project No. CXYJJ19-ZD-01, and Changde Institute for Integrated Energy Technology with Project No. E164291C01.
{{custom_fund}}
版权
Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag GmbH Germany, part of Springer Nature 2022
PDF(5348 KB)
