scholarly journals Computational study of hole shape effect on film cooling performance

2011 ◽  
Vol 225 (4) ◽  
pp. 505-519 ◽  
Author(s):  
J Yao ◽  
Y F Yao
Keyword(s):  
Film Cooling ◽  
Computational Study ◽  
Shape Effect ◽  
Cooling Performance ◽  
Hole Shape

scholarly journals Effects of Hole Shape on Film Cooling With Large Angle Injection

1999 ◽  
Author(s):  
Atui Kohil ◽  
David G. Bogard
Keyword(s):  
Velocity Field ◽  
Film Cooling ◽  
Field Measurements ◽  
Round Hole ◽  
Cooling Performance ◽  
Injection Angle ◽  
Hole Shape ◽  
Shaped Hole ◽  
Adiabatic Effectiveness ◽  
Better Than

In this study the film cooling performance of a single row of discrete holes inclined at an injection angle of 55° is investigated at a density ratio of DR = 1.6. Three different hole geometries were used in this study, a round hole and two shaped holes. One shaped hole had forward and lateral expansions of 15°, and the other a 15° lateral with a 25° forward expansion. For reference, a round hole with an injection angle of 35° was also tested. The film cooling performance of each hole shape was evaluated using adiabatic effectiveness, thermal field, and velocity field measurements. The shaped holes showed higher spatially averaged adiabatic effectiveness than the round hole over the whole range of momentum flux ratios (I) investigated. The effectiveness values for the shaped holes were only marginally better than the round hole at the low I, but at the high I, the shaped holes performed much better than the round hole. The temperature and velocity field measurements near the hole exit suggest that there is a slight detachment of the jet from the wall for the round hole, while the jets remain attached for the two shaped holes. The shaped hole with the larger forward expansion had a warmer jet with a higher trajectory at the hole exit suggesting ingestion of mainstream fluid and flow separation within the hole.

Computational Study on Pressure Side Film Cooling and Flow Structure

2013 ◽  
Author(s):  
Radheesh Dhanasegaran ◽  
Girish Venkatachalapathy ◽  
Nagarajan Gnanasekaran
Keyword(s):  
Flow Structure ◽  
Film Cooling ◽  
Computational Study ◽  
Pressure Side ◽  
Cooling Performance ◽  
Pressure Surface ◽  
Blowing Ratio ◽  
Commercial Code ◽  
Cylindrical Holes ◽  
Specific Geometry

A computational investigation is carried out to understand the film cooling performance and flow phenomenon on a pressure side of gas turbine airfoil. A specific geometry with multiple rows of cylindrical holes is considered on the pressure surface and opposite to which a flat surface is kept so as to avoid effect of imposed flow conditions. Meshing of the present model is done by using GAMBIT. Computations are carried out with K-epsilon Realizable model available in the commercial code FLUENT. The film cooling performance is discussed with flow structure followed by the effectiveness distribution on the pressure surface. The blowing ratio is varied from 0.4–2.4 and it is found that, at very low blowing ratio cases in the initial part of the pressure surface higher effectiveness values are observed but at higher blowing ratio these values become very low whereas close to the trailing edge side the effectiveness distribution is just the reverse. It was found that the optimum blowing ratio was close to unity where better flow and temperature distribution were observed.

scholarly journals Effect of Film-Hole Shape on Turbine-Blade Film-Cooling Performance

2001 ◽  
Vol 15 (3) ◽  
pp. 257-265 ◽  
Author(s):  
Shuye Teng ◽  
Je-Chin Han ◽  
Philip E. Poinsatte
Keyword(s):  
Turbine Blade ◽  
Film Cooling ◽  
Cooling Performance ◽  
Hole Shape

scholarly journals Computational study of plasma actuator on film cooling performance for different shaped holes

AIP Advances ◽  
2015 ◽  
Vol 5 (6) ◽  
pp. 067104 ◽  
Author(s):  
Sheng-ji Dai ◽  
Yang Xiao ◽  
Li-ming He ◽  
Tao Jin ◽  
Peng-hui Hou ◽  
...  
Keyword(s):  
Film Cooling ◽  
Computational Study ◽  
Plasma Actuator ◽  
Cooling Performance

The Variation of Heat Transfer Coefficient, Adiabatic Effectiveness and Aerodynamic Loss with Film Cooling Hole Shape

2006 ◽  
Vol 934 (1) ◽  
pp. 361-368 ◽  
Author(s):  
J.E. SARGISON ◽  
S.M. GUO ◽  
M.L.G. OLDFIELD ◽  
A.J. RAWLINSON
Keyword(s):  
Heat Transfer ◽  
Heat Transfer Coefficient ◽  
Transfer Coefficient ◽  
Film Cooling ◽  
Hole Shape ◽  
Aerodynamic Loss ◽  
Cooling Hole ◽  
Adiabatic Effectiveness

Influence of the braided structure on the film cooling performance over the ceramic matrix composite plate

2021 ◽  
Vol 170 ◽  
pp. 107112
Author(s):  
Zecan Tu ◽  
Chenwei Zhao ◽  
Junkui Mao ◽  
Xiao Zhao ◽  
Xingsi Han
Keyword(s):  
Matrix Composite ◽  
Film Cooling ◽  
Composite Plate ◽  
Ceramic Matrix Composite ◽  
Ceramic Matrix ◽  
Cooling Performance ◽  
Braided Structure
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