Enhancement of Full Coverage Film Cooling Effectiveness with Mixed Injection Holes
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Mukesh Prakash Mishra
,
A K Sahani
Abstract
In the present work numerical study of full coverage film cooling on an adiabatic flat plate is carried out. Cooling performance of three configurations of cylindrical holes is studied with downstream injection, upstream injection and mixed injection. In mixed injection configuration one column of holes inject in downstream direction and the holes in the adjacent column inject in the upstream direction. Numerical simulations are carried out at different velocity ratios and circumferentially averaged value of adiabatic film cooling effectiveness is estimated. Simulation results indicate that the mixed injection configuration has better and more uniform cooling, throughout the perforated plate, than with downstream injection. The difference is greater with increase in the velocity ratio. Configuration with upstream injection gives better cooling than mixed injection at front few rows of cooling holes but it shows poorer performance with downstream injection in the downstream rows of cooling holes. The obtained results from this study can be an invaluable input for highly loaded combustion chambers.
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© 2018 Walter de Gruyter GmbH, Berlin/Boston
Artikel in diesem Heft
- Frontmatter
- Original Research Articles
- Investigations of Trenched Film Hole Orientation Angle on Film Cooling Effectiveness
- Jet Flow Control Using Semi-Circular Corrugated Tab
- Simulation of Use-Related Multi-Parameter Load Spectrum Based on Principal Component Analysis
- Characterization of Tandem Airfoil Configurations of Axial Compressors
- Research on Suppressing Vibration of Mistuning Cyclic-Periodic Structure
- Research on Power Regulation Schedule Control System for Turboprop Engine
- Enhancement of Full Coverage Film Cooling Effectiveness with Mixed Injection Holes
- CFD Analysis and Experimental Validation of the Flow Field in a Rib Roughed Turbine Internal Cooling Channel
- Perforated Wall in Controlling the Separation Bubble Due to Shock Wave –Boundary Layer Interaction
- Calculating Endogenous and Exogenous Exergy Destruction for an Experimental Turbojet Engine
- One-equation turbulence models applied to practical scramjet inlet
Artikel in diesem Heft
- Frontmatter
- Original Research Articles
- Investigations of Trenched Film Hole Orientation Angle on Film Cooling Effectiveness
- Jet Flow Control Using Semi-Circular Corrugated Tab
- Simulation of Use-Related Multi-Parameter Load Spectrum Based on Principal Component Analysis
- Characterization of Tandem Airfoil Configurations of Axial Compressors
- Research on Suppressing Vibration of Mistuning Cyclic-Periodic Structure
- Research on Power Regulation Schedule Control System for Turboprop Engine
- Enhancement of Full Coverage Film Cooling Effectiveness with Mixed Injection Holes
- CFD Analysis and Experimental Validation of the Flow Field in a Rib Roughed Turbine Internal Cooling Channel
- Perforated Wall in Controlling the Separation Bubble Due to Shock Wave –Boundary Layer Interaction
- Calculating Endogenous and Exogenous Exergy Destruction for an Experimental Turbojet Engine
- One-equation turbulence models applied to practical scramjet inlet
