Unsteady Flow Control Mechanism of Synthetic Jet on a Low Pressure Turbine Blade

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Unsteady Flow Control Mechanism of Synthetic Jet on a Low Pressure Turbine Blade

更新时间：2025-07-09

- Unsteady Flow Control Mechanism of Synthetic Jet on a Low Pressure Turbine Blade
- Vol. 45, Issue 3, Pages: 95-101(2011)
- 作者机构：
  
  西安交通大学能源与动力工程学院,西安,710049
- 作者简介：
- 基金信息：
- DOI：
  CLC： V231.3
- Online First：10 March 2011，
  
  Published：2011
- 稿件说明：
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Unsteady Flow Control Mechanism of Synthetic Jet on a Low Pressure Turbine Blade[J]. 2011, 45(3): 95-101.
DOI：

Unsteady Flow Control Mechanism of Synthetic Jet on a Low Pressure Turbine Blade[J]. 2011, 45(3): 95-101. DOI：

摘要

基于Langtry-Menter转捩模型的SST湍流模型

通过求解三维非定常雷诺时均Navier-Stokes方程

数值研究了低雷诺数下合成射流涡发生器对Pak-B低压透平叶片吸力面流动分离的影响

揭示了低压透平叶片表面合成射流非定常流动的控制机理.结果表明

引入合成射流涡发生器能够抑制甚至消除低雷诺数下叶片吸力面上的流动分离.在雷诺数为25 000、自由流湍流强度为0.08%下

提高射流控制频率有助于增强合成射流涡发生器对低压透平叶片表面流动分离的控制效果

减少流动损失.当控制频率为10 Hz时

叶栅出口的相对总压损失系数为0.42; 当控制频率增加到20 Hz时

相对总压损失系数仅下降到0.41.这表明

当合成射流控制频率大于10 Hz时

继续增加控制频率来减少叶片表面流动损失的效果是不明显的.

Abstract

The three-dimensional viscous unsteady Reynolds-averaged Navier-Stokes equations were solved to simulate the flow on a low pressure turbine blade. The effects of synthetic jet on the flow separation in the suction side of the Pak-B low pressure turbine blade were numerically investigated by the SST(shear stress transport)turbulence model coupled with the Langtry-Menter transition model for turbulent flow. The unsteady flow control mechanism of synthetic jet and the flow structure were also presented. The numerical results show that the flow separation in the blade suction side can be effectively suppressed even eliminated by introducing the synthetic jet with the proper control frequency. At the Reynolds number of 25 000 and the free stream turbulence intensity of 0.08%

the increase in synthetic jet frequency can improve the control effectiveness of the flow separation on the low pressure turbine blade and reduce the flow loss. When the synthetic jet frequency is 10 Hz

the flow loss coefficient relative to the total pressure at the turbine blade exit is 0.42. However

the relative loss coefficient decreases to only 0.41 when the synthetic jet frequency increases to 20 Hz. These results imply that the flow loss does not drop clearly for the low pressure turbine blade at low Reynolds number when the synthetic jet frequency is greater than 10 Hz.

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references

SHARMA O. Impact of Reynolds number on low pressure turbine performance, CP-1998-206958[R]. New York, USA: NASA, 1998: 65-70.

SMITH B L, GLEZER A. The formation and evolution of synthetic jets [J]. Physics of Fluids, 1998, 10(9):2281-2297.

SCHAEFFLER N. The Interaction of a synthetic jet and a turbulent boundary layer, AIAA 2003-0643 [R]. Reston, VA, USA: AIAA, 2003.

AMITAY M, KIBNS V, PAREKH D, et al. The dynamics of flow reattachment over a thick airfoil controlled by synthetic jet actuators, AIAA 1999-1001 [R]. Reston, VA, USA: AIAA, 1999.

RIZZETTA D P, VISBAL M R. Numerical simulation of separation control for a transitional highly-loaded low-pressure turbine[J]. AIAA Journal, 2005, 43(9):1958-1967.

肖中云,牟斌,陈作斌,等. 零质量射流与分离控制的数值模拟[J]. 空气动力学学报, 2006, 24(1): 46-50.

XIAO Zhongyun, MOU Bin, CHEN Zuobin, et al. Compressible simulation of active flow control using synthetic jets [J]. Acta Aerodynamic Sinica, 2006, 24(1):46-50.

郝礼书,乔志德. 合成射流用于翼型分离流动控制的研究[J]. 西北工业大学学报, 2006, 24(4): 528-531.

HAO Lishu, QIAO Zhide. Maximizing the effect of synthetic jet on airfoil separation flow control[J]. Journal of Northwestern Polytechnical University, 2006, 24(4): 528-531.

MENTER F R, LANGTRY R B. A correlation-based transition model using local variables:partⅠ model formulation, ASME-GT 2004-53452 [R]. New York, USA: ASME, 2004.

LANGTRY R B, MENTER F R. A Correlation-based transition model using local variables:partⅡ test cases and industry applications, ASME-GT 2004-53454 [R]. New York, USA: ASME, 2004.

LIU Xiaomin, ZHOU Haiyang. Numerical investigations of flow separation control for a low pressure turbine blade using steady and pulsed vortex generator jets[C]∥Basic Gas Turbine Metallurgy and Repair Technology Workshop. New York, USA: ASME, 2010: 1253-1262.

周海洋. 低压透平叶片流动分离主动控制的数值研究[D]. 西安:西安交通大学能源与动力工程学院,2010.

HUANG Junhui, CORKE T C, THOMAS F O. Plasma actuators for separation control of low-pressure turbine blades [J]. AIAA Journal, 2006, 44(1): 51-57.

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