scholarly journals Experimental Investigation of Three-Dimensional Flow Development by Pitching Low-Aspect-Ratio Wing

Author(s):  
Huai-Te Yu ◽  
Luis P. Bernal
1985 ◽  
Vol 107 (4) ◽  
pp. 983-990 ◽  
Author(s):  
E. Boletis

Tip endwall contouring is one of the most effective methods to improve the performance of low aspect ratio turbine vanes [1]. In view of the wide variety of geometric parameters, it appears that only the physical understanding of the three-dimensional flow field will allow us to evaluate the probable benefits of a particular endwall contouring. The paper describes the experimental investigation of the three-dimensional flow through a low-speed, low aspect ratio, high-turning annular turbine nozzle guide vane with meridional tip endwall contouring. The full impact of the effects of tip contouring is evaluated by comparison with the results of a previous study in an annular turbine nozzle guide vane of the same blade and cascade geometry with cylindrical endwalls [12]. In parallel, the present experimental study provides a fully three-dimensional test case for comparison with advanced theoretical calculation methods [15]. The flow is explored by means of double-head, four-hole pressure probes in five axial planes from far upstream to downstream of the blade row. The results are presented in the form of contour plots and spanwise pitch-averaged distributions.


1983 ◽  
Vol 7 (4) ◽  
pp. 289-290 ◽  
Author(s):  
Ezzat D. Doss ◽  
R. K. Ahluwalia

1985 ◽  
Vol 107 (2) ◽  
pp. 436-448 ◽  
Author(s):  
M. J. Pierzga ◽  
J. R. Wood

An experimental investigation of the three-dimensional flow field through a low aspect ratio, transonic, axial-flow fan rotor has been conducted using an advanced laser anemometer (LA) system. Laser velocimeter measurements of the rotor flow field at the design operating speed and over a range of through flow conditions are compared to analytical solutions. The numerical technique used herein yields the solution to the full, three-dimensional, unsteady Euler equations using an explicit time-marching, finite volume approach. The numerical analysis, when coupled with a simplified boundary layer calculation, generally yields good agreement with the experimental data. The test rotor has an aspect ratio of 1.56, a design total pressure ratio of 1.629 and a tip relative Mach number of 1.38. The high spatial resolution of the LA data matrix (9 radial × 30 axial × 50 blade-to-blade) permits details of the transonic flow field such as shock location, turning distribution, and blade loading levels to be investigated an compared to analytical results.


2012 ◽  
Vol 4 (4) ◽  
pp. 37-50
Author(s):  
Mohamed Mokhles Abou-Seida ◽  
Gamal H. Elsaeed ◽  
Tarek Mohamed Salaheldin Mostafa ◽  
Elzahry Farouk Mohamed Elzahry

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