Experimental and simulation study on the effect of geometrical and flow parameters for combined-hole film cooling
Film cooling method was applied to the turbine blades to provide thermal protection from high turbine inlet temperatures in modern gas turbines. Recent literature discovers that combining two cylindrical holes of film cooling is one of the ways to further enhance the film cooling performances....
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| Format: | Thesis |
| Language: | English English English |
| Published: |
2016
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| Subjects: | |
| Online Access: | http://eprints.uthm.edu.my/751/1/24p%20HASWIRA%20HASSAN.pdf http://eprints.uthm.edu.my/751/2/HASWIRA%20HASSAN%20COPYRIGHT%20DECLARATION.pdf http://eprints.uthm.edu.my/751/3/HASWIRA%20HASSAN%20WATERMARK.pdf |
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| Summary: | Film cooling method was applied to the turbine blades to provide thermal protection
from high turbine inlet temperatures in modern gas turbines. Recent literature
discovers that combining two cylindrical holes of film cooling is one of the ways to
further enhance the film cooling performances. In the present study, a batch of
simulations and experiments involving two cylindrical holes with opposite compound
angle were carried out and this two cylindrical hole also known as combined-hole film
cooling. The main objective of this study is to determine the influence of different
blowing ratio, M with a combination of different lateral distance between cooling holes
(PoD), a streamwise distance between cooling holes (LoD) and compound angle of
cooling hole (1/2) on the film cooling performance. The simulation of the present
study had been carried out by using Computational Fluid Dynamic (CFD) with
application of Shear Stress Transport (SST) turbulence model analysis from ANSYS
CFX. Meanwhile, the experimental approach makes used of open end wind tunnel and
the temperature distributions were measured by using infrared thermography camera.
The purpose of the experimental approach in the present study is to validate three cases
from all cases considered in the simulation approach. As the results shown, the lateral
coverage was observed to be increased as PoD and 1/2 increased due to the interaction
between two cooling air ejected from both cooling holes. Meanwhile, film cooling
performance insignificantly changed when different LoD was applied. As the
conclusion, a combination of the different geometrical parameters with various flow
parameters produced a pattern of results. Therefore, the best configuration has been
determined based on the average area of film cooling effectiveness. For M = 0.5, PoD
= 1.0, LoD = 2.5 and 1 / 2 = -45o
/+45o
case is the most effective configuration. In the
case of M = 1.0 and M = 1.5, PoD = 0.0, LoD = 3.5, 1 / 2 = -45o
/+45o
and PoD = 0.0,
LoD = 2.5, 1 / 2 = -45o
/+30o
are the best configurations based on the overall
performance of film cooling. |
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