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Numerical investigations of the separated transitional flow over compressor blades with different loading distributions

机译:不同负载分布的分离过渡流过压缩机叶片的数值研究

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摘要

Large eddy simulations (LESs) were conducted to investigate the separated flow transition process over two compressor blades with different loading distributions at Reynolds numbers (Re) of 1.5x10(5) and 0.8x10(5) . The baseline airfoil (V103-B) was redesigned to obtain a new front-loaded airfoil (V103-F). At Re=1.5 x10(5) , a time-averaged laminar separation bubble (LSB) formed on the suction surface of V103-B and V103-F. The two-dimensional spanwise vortices shed periodically at approximately the same frequency and were further twisted through their interaction with the streamwise evolving vortices. Then, small vortex structures were generated in the vortex pairing, which was related to the onset of transition. The distorted hairpin vortices finally broke down into small turbulent eddies near the reattachment, along with an ejection-sweeping process of the near-wall flow. As Re decreased to 0.8 x10(5) , the separated shear layer failed to reattach on the blade surfaces of the two airfoils. The near-wall flow ejection-sweeping disappeared, and there was no distinct periodicity for the two-dimensional spanwise vortex shedding. The spectral analysis indicated that the transition processes in the LSBs of the two airfoils at Re=1.5 x10(5) were both dominated by the Kelvin-Helmholtz (K-H) mechanism; however, the transition onset on the suction surface of V103-F was promoted, and the size of LSB was consequently smaller than that of V103B. The loss generation mechanism in the LSB was analyzed by comparing the deformation work terms due to the viscous and turbulent dissipation effects, with the results indicating that the largest amount of loss was determined by the Reynolds shear stresses. Due to the suppression of the LSB on the suction surface of V103-F, the profile loss was decreased distinctly by 32.3% at Re=1.5 x10(5) compared with that of V103-B. (C) 2020 Elsevier Masson SAS. All rights reserved.
机译:进行大型涡流模拟(较少)以研究两个压缩机叶片的分离的流动过渡过程,在雷诺数(RE)为1.5×10(5)和0.8x10(5)时的不同负载分布。重新设计基线翼型(V103-B)以获得新的前负载翼型(V103-F)。在Re = 1.5×10(5)中,在V103-B和V103-F的吸入表面上形成的时间平均层间分离气泡(LSB)。定期旋转的二维翼展涡流大致相同的频率,并且通过它们与流动演化涡流的相互作用进一步扭曲。然后,在涡旋配对中产生小涡流结构,其与转变发作有关。扭曲的发夹涡流最终突破了重新附近附近的小湍流漩涡,以及近壁流的射精扫描过程。重新降低至0.8×10(5),分离的剪切层未能在两个翼型的刀片表面上重新连接。近壁流动喷射扫描消失,无线周期性的二维血管涡流脱落。光谱分析表明,在重新= 1.5×10(5)的两个翼型中的LSB中的过渡过程均由Kelvin-Helmholtz(K-H)机制主导;然而,促进了V103-F的抽吸表面上的过渡发作,因此LSB的尺寸小于V103b的大小。通过比较由于粘性和湍流耗散效应的变形工作项进行比较,分析了LSB中的损失产生机制,结果表明雷诺剪切应力测定了最大的损失量。由于V103-F的吸入表面上的LSB抑制,与V103-B的抽吸表面上的曲线损失明显减小了32.3%。 (c)2020 Elsevier Masson SAS。版权所有。

著录项

  • 来源
    《Aerospace science and technology》 |2020年第1期|106113.1-106113.13|共13页
  • 作者单位

    Chinese Acad Sci Key Lab Light Duty Gas Turbine Inst Engn Thermophys Beijing 100190 Peoples R China|Univ Chinese Acad Sci Beijing 100049 Peoples R China;

    Chinese Acad Sci Key Lab Light Duty Gas Turbine Inst Engn Thermophys Beijing 100190 Peoples R China|Univ Chinese Acad Sci Beijing 100049 Peoples R China;

    Chinese Acad Sci Key Lab Light Duty Gas Turbine Inst Engn Thermophys Beijing 100190 Peoples R China|Univ Chinese Acad Sci Beijing 100049 Peoples R China;

    Chinese Acad Sci Key Lab Light Duty Gas Turbine Inst Engn Thermophys Beijing 100190 Peoples R China|Univ Chinese Acad Sci Beijing 100049 Peoples R China;

    Chinese Acad Sci Key Lab Light Duty Gas Turbine Inst Engn Thermophys Beijing 100190 Peoples R China|Univ Chinese Acad Sci Beijing 100049 Peoples R China;

    Chinese Acad Sci Key Lab Light Duty Gas Turbine Inst Engn Thermophys Beijing 100190 Peoples R China|Univ Chinese Acad Sci Beijing 100049 Peoples R China;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

    Separated flow transition; Compressor airfoil; Loading distribution; Vortex dynamics; Loss mechanism; Large eddy simulation;

    机译:分离的流动过渡;压缩机翼型;装载分布;涡旋动力学;损失机制;大涡模拟;

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