波转子非定常泄漏流动机理

doi:10.7527/S1000-6893.2016.0269

流体力学与飞行力学

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

波转子非定常泄漏流动机理

刘琛源, 刘火星

北京航空航天大学能源与动力工程学院, 北京 100083

收稿日期:2016-07-12 修回日期:2016-10-08 出版日期:2017-05-15 发布日期:2016-10-10
通讯作者: 刘火星 E-mail:liuhuoxing@buaa.edu.cn

Mechanism of nonsteady leakage flow of wave rotors

LIU Chenyuan, LIU Huoxing

School of Energy and Power Engineering, Beihang University, Beijing 100083, China

Received:2016-07-12 Revised:2016-10-08 Online:2017-05-15 Published:2016-10-10

摘要/Abstract

摘要：

针对制约波转子性能的泄漏问题，通过提取波转子中与泄漏相关的主要流动现象并建立波转子单通道泄漏模型，对非定常泄漏流动机制进行了详细的数值研究，对本文给出的非定常泄漏损失预测模型进行了数值验证。结果表明：转子通道中存在不同程度的压力波动，波动幅值与间隙宽度有关；连续反射膨胀波、周期性出现的弓形激波及其反射激波是压力波动的根本原因；间隙内部泄漏过程存在3个主要的流动阶段；泄漏过程中通道激波传播速度不变、波后时均压力不变；在一定间隙宽度范围内，激波马赫数、激波静增压比与无量纲间隙宽度均呈线性关系，当间隙宽度从0增大到0.08时，激波马赫数衰减7.3%，激波静增压比衰减10.1%；泄漏流动通过泄漏产生的主膨胀波对激波传播过程施加影响，通道激波衰减本质上是理想激波与主膨胀波叠加效应的结果；泄漏损失预测模型与数值结果吻合良好。

关键词: 燃气轮机, 波转子, 单通道模型, 非定常泄漏流动, 激波

Abstract:

The problem of leakage flow can restrict the performance of a wave rotor. This paper extracts main flow phenomena related to leakage in a wave rotor, and establishes a two-dimensional single passage leakage model. The mechanism of nonsteady leakage flow is analyzed numerically, and the prediction model for loss of unsteady leakage flow is further verified. The results show that there exists pressure oscillation of varying extent in rotor passage, and the oscillation amplitude is related to the gap width. The continuous reflected expansion wave, periodic emerging bow shock and its reflected shock are reasons for pressure oscillation. There exist three main flow stages in the leakage gap during leakage flow process and during which the propagation speed of passage shock and post-shock time-averaging pressure stay unchanged. Within a certain range of gap width, shock Mach number and shock static pressure ratio are both linearly dependent on the nondimensional leakage gap width. When the gap width is increased from 0 to 0.08, the shock Mach number decreases by 7.3%, and the shock static pressure ratio decreases by 10.1%. The propagation of channel shock wave is influenced by leakage flow process via main expansion wave, and shock wave attenuation is essentially the result of superposition of ideal shock wave and expansion wave. The results obtained with leakage loss prediction model is found to be consistent with CFD results.

Key words: gas turbine, wave rotor, single passage model, nonsteady leakage flow, shock wave

中图分类号:

V231.3

刘琛源, 刘火星. 波转子非定常泄漏流动机理[J]. 航空学报, 2017, 38(5): 120606-120606.

LIU Chenyuan, LIU Huoxing. Mechanism of nonsteady leakage flow of wave rotors[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(5): 120606-120606.

参考文献

[1] WEBER H E. Shock wave engine design[M]. New York:John Wiley & Sons, Inc, 1995:1-4.
[2] DEMPSEY E, MULLER N, AKBARI P, et al. Performance optimization of gas turbines utilizing four-port wave rotors:AIAA-2006-4152[R]. Reston:AIAA, 2006.
[3] AKBARI P, KHARAZI A A, MULLER N. Utilizing wave rotor technology to enhance the turbo compression in power and refrigeration cycles:IMECE-2003-44222[R]. New York:ASME, 2003.
[4] AKBARI P, NALIM R, MULLER N. A review of wave rotor technology and its applications:IMECE-2004-60082[R]. New York:ASME, 2004.
[5] KENTFIELD J A C. Nonsteady, one-dimensional, internal, compressible flows:theory and applications[M]. Oxford:Oxford University Press, 1993:127-128.
[6] WILSON J. An experimental determination of losses in a three-port wave rotor[J]. Journal of Engineering for Gas Turbines and Power, 1998, 120(4):833-842.
[7] PAXSON D E. Comparison between numerically modeled and experimentally measured wave-rotor loss mechanisms[J]. Journal of Propulsion and Power, 1995, 11(5):908-914.
[8] AKBARI P, NALIM M R. Leakage assessment of pressure-exchange wave rotors[J]. Journal of Propulsion and Power, 2008, 24(4):732-740.
[9] WILSON J, WELCH G E, PAXSON D E. Experimental results of performance tests on a four-port wave rotor:AIAA-2007-1250[R]. Reston:AIAA, 2007.
[10] ELEUTERIO F T. Riemann solvers and numerical methods for fluid dynamics[M]. Heidelberg:Springer, 2009:115-119.
[11] GLASS I I, PATTERSON G N. A theoretical and experimental study of shock-tube flows[J]. Journal of the Aeronautical Sciences, 1955, 22(2):73-100.
[12] ZHANG G, SETOGUCHI T, KIM H D. Numerical simulation of flow characteristics in micro shock tubes[J]. Journal of Thermal Science, 2015, 24(3):246-253.
[13] OKAMOTO K, NAGASHIMA T. Visualization of wave rotor inner flow dynamics[J]. Journal of Propulsion and Power, 2007, 23(2):292-300.
[14] ZHANG G, KIM H D. Numerical simulation of shock wave and contact surface propagation in micro shock tubes[J]. Journal of Mechanical Science and Technology, 2015, 29(4):1689-1696.
[15] 阎超. 计算流体力学方法及应用[M]. 北京:北京航空航天大学出版社, 2006:171. YAN C. Methods and applications of computational fluid dynamics[M]. Beijing:Beihang University Press, 2006:171 (in Chinese).
[16] SAITO T, TAKAYAMA K. Numerical simulations of nozzle starting process[J]. Shock Waves, 1999, 9(2):73-79.
[17] DESHPANDE A, PURANIK B. Effect of viscosity and wall heat conduction on shock attenuation in narrow channels[J]. Shock Waves, 2015, 25(1):1-11.
[18] SKEWS B W. The perturbed region behind a diffracting shock wave[J]. Journal of Fluid Mechanics, 1967, 29(4):705-719.
[19] TAKAWAMA K, INOUE O. Shock wave diffraction over a 90 degree sharp corner-posters presented at 18^th ISSW[J]. Shock Waves, 1991, 1(4):301-312.
[20] IGRA O, FALCOVITZ J, REICHENBACH H, et al. Experimental and numerical study of the interaction between a planar shock wave and a square cavity[J]. Journal of Fluid Mechanics, 1996, 313:105-130.

E-mail：hkxb@buaa.edu.cn

关于我们

期刊社服务

专业学科

封面文章

友情链接

主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

波转子非定常泄漏流动机理

Mechanism of nonsteady leakage flow of wave rotors

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 15

编辑推荐

Metrics

本文评价

[1]	谢玮, 罗振兵, 周岩, 刘强, 吴建军, 董昊. 高超声速双楔激波干扰定常射流控制试验研究[J]. 航空学报, 2024, 45(7): 128813-128813.
[2]	汪洪波, 曾宇, 熊大鹏, 杨揖心, 孙明波. SST湍流模型的激波与可压缩效应改进[J]. 航空学报, 2024, 45(3): 128694-128694.
[3]	赖江, 范召林, 王乾, 董思卫, 童福林, 袁先旭. 高超声速有攻角锥裙直接数值模拟[J]. 航空学报, 2024, 45(2): 128610-128610.
[4]	马平, 张宁, 石安华, 于哲峰, 梁世昌, 黄洁. 典型微波波段信号在模拟等离子体中的传输特性[J]. 航空学报, 2023, 44(S2): 729476-729476.
[5]	曾宇, 汪洪波, 孙明波, 王超, 刘旭. SST湍流模型改进研究综述[J]. 航空学报, 2023, 44(9): 27411-027411.
[6]	马印锴, 李祝飞, 黄琪, 杨基明. 宽速域翼尖涡及其与斜激波相互作用[J]. 航空学报, 2023, 44(7): 38-50.
[7]	金毅, 孙姝, 郭赟杰, 谭慧俊, 张悦. 超声速可调进气道内流双解现象及其节流特性[J]. 航空学报, 2023, 44(7): 127134-127134.
[8]	刘为佳, 李映坤, 陈雄, 李春雷. 基于流固耦合的激波/边界层干扰作用下壁板颤振特性[J]. 航空学报, 2023, 44(6): 127085-127085.
[9]	魏皇生, 黄柱, 席光. 一种基于幅值和波数的耗散控制方法[J]. 航空学报, 2023, 44(4): 126589-126589.
[10]	王文杰, 赵旭, 杨龙, 李濠君, 向粤. 跨速域强地效水平助推滑跑气动机理[J]. 航空学报, 2023, 44(21): 528247-528247.
[11]	孙士珺, 李晓龙, 刘艳明, 王建华, 王松涛. 宽速域来流对超声通流风扇叶型气动性能的影响[J]. 航空学报, 2023, 44(21): 528523-528523.
[12]	宋家辉, 许爱国, 苗龙, 廖煜淦, 梁福文, 田丰, 聂明卿, 王宁飞. 激波/平板层流边界层干扰熵增特性[J]. 航空学报, 2023, 44(21): 528520-528520.
[13]	王梦格, 何小明, 王娟娟, 张悦, 汪昆, 谭慧俊, 李留刚. 基于振荡式涡流发生器的激波/边界层干扰控制方法[J]. 航空学报, 2023, 44(20): 128503-128503.
[14]	宋亚辉, 樊高宇, 瞿丽霞, 张跃林, 徐悦, 韩硕. 航空器声爆飞行试验测量技术研究进展[J]. 航空学报, 2023, 44(2): 626186-626186.
[15]	田珊珊, 金亮, 杜兆波, 钟翔宇, 黄伟, 刘远洋. 基于鼓包的激波/边界层干扰控制研究进展[J]. 航空学报, 2023, 44(18): 28411-028411.