Investigation on the Influence of Various Mainstream Pressure Gradients on the Film Cooling Performances of Cylindrical Hole and Expansion Shaped Holes
-
Hui-Ren Zhu
Abstract
In the present paper, experimental and numerical investigations have been carried out on the film cooling characteristics of cylindrical hole, laidback fan shaped hole and doublefan shaped holes in the presence of various mainstream pressure gradients. Three momentum ratios: 1, 2 and 4, were measured. The pressure gradients, especially the adverse pressure gradient, improve the jet coverage and the jet lateral spread for cylindrical hole film cooling and 45° inclined doublefan shaped hole film cooling, especially under large momentum ratios. However, the effect of pressure gradient on the film cooling effectiveness of 90° inclined doublefan shaped hole is different from that of 45° inclined doublefan shaped hole. The film cooling effectiveness under favorable pressure gradient is the highest for 90° inclined hole. The effect of pressure gradients on the film cooling effectiveness of laidback fan shaped hole and 20° inclined doublefan shaped hole is weak because of the jets' good attachment on the wall. For all the holes, the normalized heat transfer coefficient h/h0 under favorable mainstream pressure gradient is the highest under all the momentum ratios. Relative to the h/h0 of zero pressure gradient, the h/h0 of adverse pressure gradient is lower or close in the upstream region, but higher in the downstream region.
©2014 by Walter de Gruyter Berlin/Boston
Articles in the same Issue
- Frontmatter
- Investigation on the Influence of Various Mainstream Pressure Gradients on the Film Cooling Performances of Cylindrical Hole and Expansion Shaped Holes
- Experimental Investigation of an Active Elastic Support/Dry Friction Damper on Vibration Control of Rotor Systems
- Influencing Factors on the Performance of Pulse Detonation Engine at Test Bench
- Pipe Diffuser for Radial and Axial-centrifugal Compressor
- Noise Power Spectrum Research of the Turboprop Engine Test
- Large Eddy Simulation of a Low Speed Subsonic Jet: A Validation Study
- Studies on Downstream Stator with Rotor Re-Staggering and Forward Sweeping in a Subsonic Axial Compressor Stage
- Development of Practical Integral Condition Monitoring System for a Small Turbojet Engine Using MATLAB/SIMULINK and LabVIEW
- Influence of Rib Height on Heat Transfer Augmentation – Application to Aircraft Turbines
Articles in the same Issue
- Frontmatter
- Investigation on the Influence of Various Mainstream Pressure Gradients on the Film Cooling Performances of Cylindrical Hole and Expansion Shaped Holes
- Experimental Investigation of an Active Elastic Support/Dry Friction Damper on Vibration Control of Rotor Systems
- Influencing Factors on the Performance of Pulse Detonation Engine at Test Bench
- Pipe Diffuser for Radial and Axial-centrifugal Compressor
- Noise Power Spectrum Research of the Turboprop Engine Test
- Large Eddy Simulation of a Low Speed Subsonic Jet: A Validation Study
- Studies on Downstream Stator with Rotor Re-Staggering and Forward Sweeping in a Subsonic Axial Compressor Stage
- Development of Practical Integral Condition Monitoring System for a Small Turbojet Engine Using MATLAB/SIMULINK and LabVIEW
- Influence of Rib Height on Heat Transfer Augmentation – Application to Aircraft Turbines
