The Effect of Blowing Ratio on Film Cooling Effectiveness Using Cylindrical and Row Trenched Cooling Holes with Alignment Angle of 90 Degrees

Azwadi, Nor; Kianpour, Ehsan

doi:10.1155/2014/470576

Cited by 2 publications

(1 citation statement)

References 26 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The results indicated that high temperature gradient was developed upstream of the dilution holes. Kianpour et al [8,9] re-simulated the Vakil and Thole's combustor. They offered various geometries of cooling holes.…”

Section: Introductionmentioning

confidence: 99%

Influence of Compound Spherical Trenched Holes on Film Cooling Performance at the end of Combustor Simulator

Sidik

Kianpour²

2022

ARASET

View full text Add to dashboard Cite

The major effects of cylindrical and spherical trenched cooling holes with distance between the hole surface and the combustion chamber panel and the filler diameter on the spherical hole contact surface and the panel surface H=0.3,R=D/2=0.1, H=0.3, R=D/2=0.2 and H=0.3, R=D/2=0.3 cm at BR=3.18 on the film cooling effectiveness near the combustor end wall surface is an important subject to study in details. In this research, a three-dimensional representation of a Pratt and Whitney gas turbine engine was simulated and analysed with a commercial finite volume package FLUENT 6.2.26. The analyses were done with RANS turbulence model on internal cooling passages. The combustor simulator was combined with the interaction of two rows of dilution jets, which were staggered in the streamwise direction and aligned in the spanwise direction. In comparison with the baseline case, the application of trenched holes increased the effectiveness of film cooling up to 47% near the wall surface and an average of 35% in depth of combustor simulator .

show abstract

Section: Introductionmentioning

confidence: 99%

Influence of Compound Spherical Trenched Holes on Film Cooling Performance at the end of Combustor Simulator

Sidik

Kianpour²

2022

ARASET

View full text Add to dashboard Cite

show abstract

Performance prediction of trailing-edge cooling system of gas turbine blade using detached eddy simulation

Jamaldi

Hassan

2020

ARSTech

View full text Add to dashboard Cite

This study aims to evaluate the performance of the trailing-edge (TE) cooling system in a gas turbine blade. Eddy Simulation (DES), based on the turbulence model of Spallart-Almaras (SA), was used to simulate the TE cooling system. A TE configuration with a five-row staggered pin-fin arrangement was employed as a computational domain. Three parameters, i.e., the coefficient of heat transfer on the pin-fins surface (hpin), the coefficient of discharge (CD), and the effectiveness of adiabatic film cooling were used to assess the performances. The findings denoted that the heat transfer fluctuations occurred on the surface of the pin-fins in each row. The discharge coefficient increased with the rising of the blowing ratio. The trend predicted data of effectiveness were in good agreement with realistic discrepancies compared to other researches, mainly for higher blowing ratio. The average effectiveness along the cut-off region was to be sensitive to the changes of the blowing ratio, which was attributed to the structures of turbulent flow along the mixing region.

show abstract

The Effect of Blowing Ratio on Film Cooling Effectiveness Using Cylindrical and Row Trenched Cooling Holes with Alignment Angle of 90 Degrees

Cited by 2 publications

References 26 publications

Influence of Compound Spherical Trenched Holes on Film Cooling Performance at the end of Combustor Simulator

Influence of Compound Spherical Trenched Holes on Film Cooling Performance at the end of Combustor Simulator

Performance prediction of trailing-edge cooling system of gas turbine blade using detached eddy simulation

Contact Info

Product

Resources

About