Numerical Study of Wakes on Downstream Effects in Static Cascade Flow Field to Simulation of Rotor Wake

Article Preview

Abstract:

The effects of moving wakes on the compressor cascade flow are discussed in this article, which can be regarded as the flow simulation between stages of compressor cascade. The moving wakes are simulated by moving cylinder before a compressor cascade flow. Different flow situations by changing the angle of wakes direction are presented by numerical simulation. The performance of cascade influenced by cylinder wakes can be related to several parameters, such as the distance between cascades in the shaft direction, the angle of wake direction. Loss of the cascade changes along with those parameters whose optimal direction is demonstrated.

You might also be interested in these eBooks

Info:

Periodical:

Advanced Materials Research (Volumes 805-806)

Pages:

1865-1869

Citation:

Online since:

September 2013

Export:

Price:

Permissions CCC:

Permissions PLS:

Сopyright:

© 2013 Trans Tech Publications Ltd. All Rights Reserved

Share:

Citation:

[1] Hodson P H, Howell R J. Blade interaction transition and high-lift aero foils in low-pressure turbines[J]. Annual Re-view of Fluid Mech., 2005, 37(1): 71-98.

DOI: 10.1146/annurev.fluid.37.061903.175511

Google Scholar

[2] Halstead D E, Wisler D C, Okishi T H, et al. Boundary layer development in axial compressor and turbine part 1 of 4: composite picture[J]. Transactions of the ASME, 1997, 119(1): 114-127.

Google Scholar

[3] Pfeil H, Herbst R, Schrder T. Investigation of the laminar- turbulent transition of boundary layers disturbed by wakes [J]. ASME Journal of Engineering for Power, 1983, 105.

DOI: 10.1115/1.3227373

Google Scholar

[4] LI Zhiping. Experimental investigation of realizing un-steady cooperative flow type in axial-flow compressor[D]. Beijing: Beijing University of Aeronautics and Astro-nautics, 2006. (in Chinese).

Google Scholar

[5] Valkov T V, Tan C S. Effect of upstream rotor vertical disturbances on the time-averaged performance of axial compressor stators: Part 1—Framework of technical approach and wake-stator blade interactions[J]. Journal ofTurbomachinery, 1999, 121(3): 377-386. ).

DOI: 10.1115/1.2841330

Google Scholar

[6] Schulte V, Hodson H P. Unsteady wake-induced boundary layer transition in high lift LP turbines[J]. Journal of Tur-bomachinery, 1998, 120(1): 28-35.

DOI: 10.1115/1.2841384

Google Scholar

[7] LH Smith. Wake Dispersion in Turbomachines[J]. ASME Journal of Basic Engineering, SeriesD, №3: 688-690, (1966).

Google Scholar

[8] YE Jian, ZOU Zhengping. Large-eddy simulation of periodic wake/laminar separation bubble interaction under low Reynolds number conditions[J]. Journal of Engineering Thermophysics, 2007, 28(2): 215-218. (in Chinese).

Google Scholar

[9] YANG Lin, LIU Huoxing, ZOU Zhengping, et al. Aerodynamic design of low pressure turbines on the condition of low Reynolds number[J]. Journal of Engineering Thermophysis, 2005, 26(4): 228-230. (in Chinese).

Google Scholar

[10] ZHANG Weihao, LIU Huoxing, LI Wei. Wake-boundary layer interaction on low pressure turbine cascade blade[J]. Journal of Aerospace Power, 2009, 24 (4): 843-850. (in Chinese).

Google Scholar

[11] Stieger R D, Hodson H P. The transition mechanism of highly loaded LP turbine blades[R]. ASME, GT2003238304, (2003).

DOI: 10.1115/gt2003-38304

Google Scholar