Numerical Investigation on Two Compound Angles Film Cooling of Stator Blades

2011 ◽  
pp. 689-697
Author(s):  
Zhang Ling ◽  
Wen Guo-liang ◽  
Peng Tao
Keyword(s):  
Numerical Investigation ◽  
Film Cooling

Numerical Investigation of Film Cooling over a Flat Plate with Varying Injection Angle

2017 ◽  
Vol 17 (17th International Conference) ◽  
pp. 1-16
Author(s):  
Abdelaziz Elareibi ◽  
Tarek Elnady ◽  
Ali Elmaihy ◽  
Salman Elshmarka
Keyword(s):  
Flat Plate ◽  
Numerical Investigation ◽  
Film Cooling ◽  
Injection Angle

Numerical Investigation of Film Cooling Effectiveness Including Shockwave Interaction in a Supersonic Nozzle Flow

2022 ◽  
Author(s):  
Manoj Prabakar Sargunaraj ◽  
Andres Torres ◽  
Jose Garduna ◽  
Marcel Otto ◽  
Jayanta S. Kapat ◽  
...  
Keyword(s):  
Numerical Investigation ◽  
Film Cooling ◽  
Supersonic Nozzle ◽  
Nozzle Flow ◽  
Cooling Effectiveness ◽  
Film Cooling Effectiveness

Numerical Investigation on Leading Edge of Film Cooling Blade with Different Turbulence and Blowing Ratios

2014 ◽  
Vol 1070-1072 ◽  
pp. 1731-1734
Author(s):  
Shao Hua Li ◽  
Ge Wu ◽  
Ling Zhang
Keyword(s):  
Temperature Field ◽  
Numerical Investigation ◽  
Turbulence Intensity ◽  
Film Cooling ◽  
Leading Edge ◽  
Cooling Efficiency ◽  
Simulated Temperature

In order to investigate the influence of cooling efficiency of leading edge of film cooling blade with different turbulence intensity and blowing ratios,which use method of N-S equation,various blowing ratios of 1.0、1.5 and 2.0,various turbulence intensity of 5%、12%、20% and 30%,it simulated temperature field in leading edge of film cooling blade.The results show: cooling efficiency decreased when blowing ratios is increased.When turbulence intensity is 5%、12% and 20%,it obtains maximum cooling efficiency blowing ratios of 1.0.When turbulence intensity is 30%,it obtains maximum cooling efficiency blowing ratios of 1.5. In blowing ratios of 1.0,cooling efficiency decreased when turbulence increased.But in blowing ratios of 1.5 and 2.0,cooling efficiency increased when turbulence increased.

Numerical Investigation on Film Cooling Performance of Fusiform Diffusion Holes

2018 ◽  
Vol 140 (12) ◽  
Author(s):  
Bai-Tao An ◽  
Jian-Jun Liu
Keyword(s):  
Numerical Investigation ◽  
Cross Section ◽  
Film Cooling ◽  
Discharge Coefficient ◽  
Cross Sectional ◽  
Cooling Performance ◽  
Blowing Ratio ◽  
Section Area ◽  
Two Sides ◽  
Dynamics Method

This paper presents a numerical investigation of the film-cooling performance of a kind of diffusion hole with a fusiform cross section. Relative to the rectangular diffusion hole, the up- and/or downstream wall of the fusiform diffusion hole is outer convex. Under the same metering section area, six fusiform diffusion holes were divided into two groups with cross-sectional widths of W = 1.7D and W = 2.0D, respectively. Three fusiform cross section shapes in each group included only downstream wall outer convex, only upstream wall outer convex, or a combination of both. Simulations were performed in a flat plate model using a 3D steady computational fluid dynamics method under an engine-representative condition. The simulation results showed that the fusiform diffusion hole with only an outer convex upstream wall migrates the coolant laterally toward the hole centerline, and then forms or enhances a tripeak effectiveness pattern. Conversely, the fusiform diffusion hole with an outer convex downstream wall intensely expands the coolant to the hole two sides, and results in a bipeak effectiveness pattern, regardless of the upstream wall shape. Compared with the rectangular diffusion holes, the fusiform diffusion holes with only an upstream wall outer convex significantly increase the overall effectiveness at high blowing ratios. The increased magnitude is approximately 20% for the hole of W = 1.7D at M = 2.5. Besides, the fusiform diffusion holes with an outer convex upstream wall increase the discharge coefficient about 5%, within the moderate to high blowing ratio range.

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