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Gas Turbine Simulation

Gas Turbine simulation has been heavily used by the Gas turbine industries in Singapore with the aim to try and optimize efficiency and extend the gas turbine engine performance.
 
Gas Turbine Simulation

Featured Gas Turbine Simulation Case Studies

Investigation on Effects of Trenched Cooling Holes Dimensions on Film Cooling Effectiveness

Objective:
By using the well-known Bryton cycle, the combustor outlet temperature must increase to have higher efficiencies. However, the turbine inlet temperature increment creates a harsh environment for the downstream components of the combustor. This requires designing an efficient cooling technique in this area.
In the traditional cooling system, the increase in blowing ratio enhances cooling effectiveness. But, the coolant does not well attach on the surface at higher blowing ratios. This necessitates restructuring the cooling holes. A useful way can be trenching cooling holes at the combustor end wall surface and the alignment of row trenched holes; however, this has not been seriously considered as a solution up to the present time.
Approach: The present study has been conducted in order to investigate the effects of trenched cooling holes with different depths and widths at blowing ratio of BR=3.18 on film cooling effectiveness. The two-dimensional representation of a part of combustor end wall was simulated and a program was written in the finite difference method by MATLAB software in order to find the optimum depth and width.
Furthermore, the three-dimensional representation of Pratt and Whitney’s gas turbine engine was selected to investigate the effects of cylindrical and row trenched cooling holes with an alignment angle of 0, 90 and +-60degrees at different blowing ratios of 1.25 and 3.18 on film cooling effectiveness and mixing processes adjacent the end wall surface.
To achieve the objective, the model was simulated and analyzed with the commercial finite volume package, FLUENT 6.2.26.
 
Outcome 
This gas turbine study overall findings show that the application of the row trenched cooling holes near the combustor enwall surface increases the effectiveness of film cooling up to twice its value compared to the cooling performance of baseline case.

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