Effect of multi-hole arrangement on the effusion cooling with backward injection
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Ved Prakash
,
Sunil Chandel
Abstract
In the present work, a three-dimensional numerical analysis of multi-hole film cooling on an adiabatic flat plate with combined backward and forward injection holes is carried out at varying velocity ratios from 0.5 to 2.5. The effect of three different multi-hole arrangements, square-diamond, long-diamond, and super-long-diamond with constant perforated percentage (3.27%), on film cooling performance is studied. Combining backward and forward injection holes help in achieving higher velocity boundary layer thickness in the multi-hole arrangement. It is observed that super-long-diamond arrangement provides the highest film cooling effectiveness than square-diamond and long-diamond arrangements and favours early development of coolant film layer.
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Author contributions: All the authors have accepted responsibility for the entire content of this submitted manuscript and approved submission.
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Research funding: None declared.
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Conflict of interest statement: The authors declare no conflicts of interest regarding this article.
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Articles in the same Issue
- Frontmatter
- Design and aerodynamic performance analysis of a variable geometry axisymmetric inlet for TBCC
- Effect of multi-hole arrangement on the effusion cooling with backward injection
- Research on a component characteristic adaptive correction method for variable cycle engines
- Optimization of a circumferential groove in a centrifugal compressor
- Comparative study of numerical approaches to adaptive gas turbine cycle analysis
- Numerical simulation of shock wave/tip leakage vortex interaction for a transonic axial fan rotor
- Experimental research on suppressing unbalanced vibration of rotor by integral squeeze film damper
- The influence of the geometry of V-gutter bluff body on transient vortex shedding
- Design and validation of a two-dimensional variable geometry inlet
- Computational assessment of performance parameters of an aero gas turbine combustor for full flight envelope operation
- Investigation of effect of atomization performance on lean blowout limit for gas turbine combustors by comparison of utilizing aviation kerosene and methane as fuel
- Design optimization of a supersonic through-flow fan rotor based on the blade profiles
Articles in the same Issue
- Frontmatter
- Design and aerodynamic performance analysis of a variable geometry axisymmetric inlet for TBCC
- Effect of multi-hole arrangement on the effusion cooling with backward injection
- Research on a component characteristic adaptive correction method for variable cycle engines
- Optimization of a circumferential groove in a centrifugal compressor
- Comparative study of numerical approaches to adaptive gas turbine cycle analysis
- Numerical simulation of shock wave/tip leakage vortex interaction for a transonic axial fan rotor
- Experimental research on suppressing unbalanced vibration of rotor by integral squeeze film damper
- The influence of the geometry of V-gutter bluff body on transient vortex shedding
- Design and validation of a two-dimensional variable geometry inlet
- Computational assessment of performance parameters of an aero gas turbine combustor for full flight envelope operation
- Investigation of effect of atomization performance on lean blowout limit for gas turbine combustors by comparison of utilizing aviation kerosene and methane as fuel
- Design optimization of a supersonic through-flow fan rotor based on the blade profiles
