Access the full text.
Sign up today, get DeepDyve free for 14 days.
Constructive methods for improving the film cooling system of ABE rotor blades, Electronic J
AA Khalatov, II Borisov, Y A Dashevskii, SB Reznik (2016)
Heat transfer and hydrodynamics in the fields of centrifugal mass forces, Vol. 10Advanced Film-Cooling Schemes, Nat. Tech. Univ. of Ukraine “Kiev Polytechnical Institute”
(2020)
Il'inkova, and I.I. Khabibullin, Thermophysics of working processes in cooled gas-turbine blades
V. Terekhov, A. Dyachenko, Ya Smulsky, T. Bogatko, N. Yarygina (2022)
Heat Transfer in Subsonic Separated FlowsHeat and Mass Transfer
C. Saumweber, A. Schulz, S. Wittig (2002)
Free-Stream Turbulence Effects on Film Cooling With Shaped HolesJournal of Turbomachinery-transactions of The Asme, 125
L. Wright, S. McClain, M. Clemenson (2011)
PIV Investigation of the Effect of Freestream Turbulence Intensity on Film Cooling From Fanshaped Holes
S. Isaev, A. Schelchkov, A. Leontiev, P. Baranov, M. Gulcova (2016)
Numerical simulation of the turbulent air flow in the narrow channel with a heated wall and a spherical dimple placed on it for vortex heat transfer enhancement depending on the dimple depthInternational Journal of Heat and Mass Transfer, 94
(2015)
Improving the Efficiency of the Gas Turbine by Optimizing the Parametric Structure of the Shape of Transition Channel and Film Cooling Holes, Cand
T. Kampe, S. Völker, Torsten Sämel, C. Heneka, H. Ladisch, A. Schulz, H. Bauer (2013)
Experimental and Numerical Investigation of Flow Field and Downstream Surface Temperatures of Cylindrical and Diffuser Shaped Film Cooling Holes1Journal of Turbomachinery-transactions of The Asme, 135
(2003)
Тheory, Analysis, and Design of Aircraft Engines and Power Plants
B. Laveau, R. Abhari (2010)
Influence of Flow Structure on Shaped Hole Film Cooling Performance
(1993)
Heat Transfer in Cooled Parts of Gas Turbine Engines
D. Zheng, D. Zheng, Xinjun Wang, Qi Yuan (2019)
Numerical investigation on the effect of vortex generator shapes on film cooling performanceThermophysics and Aeromechanics, 26
(2016)
Heat transfer and hydrodynamics in the fields of centrifugal mass forces, Vol. 10, in: Advanced Film-Cooling Schemes
Xianchang Li, Ganesh Subbuswamy, Jiang Zhou (2013)
Performance of Gas Turbine Film Cooling with Backward InjectionEnergy and Power Engineering, 05
(1993)
US, Gas turbine engine component with compound cooling holes and method for making the same
(2012)
Samokhvalov, Analysis of the use of profiled perforation holes for improving the film cooling performance of the back of the nozzle blades of turbines
Neil Genzlinger (2006)
A. and QNew York Times Book Review
W. Marsden (2012)
I and J
W. Colban, K. Thole, D. Bogard (2011)
A film-cooling correlation for shaped holes on a flat-plate surfaceJournal of Turbomachinery-transactions of The Asme, 133
M. Pakhomov, V. Terekhov, A. Khalatov, I. Borisov (2015)
Film cooling effectiveness with injection through circular holes embedded in a transverse trenchThermophysics and Aeromechanics, 22
R. Bunker (2005)
A review of shaped hole turbine film-cooling technologyJournal of Heat Transfer-transactions of The Asme, 127
V. Motulevich (1968)
Method of relative correspondence and its application to problems of heat and mass transferJournal of engineering physics, 14
Film cooling efficiency averaged over the length of a one-row ring of holes for the case of a flat surface with air blowing through fan-shaped holes was estimated experimentally and normalized by the respective efficiency for cylindrical holes in a wide range of injection parameters m (from 0.25 to 5.5) and blowing angles α (from 30° to 75°). Ranges of regime and geometric parameters of film cooling systems in which fan-shaped holes provide a higher cooling efficiency in comparison with cylindrical holes have been identified. With the case of α = 30° taken as an example, we show that very high injection parameters (m = 4.5÷5.5) in the entrance region of the mixing zone (x/d < 10) make the relative efficiency η¯fan/η¯cyl\documentclass[12pt]{minimal}\usepackage{amsmath}\usepackage{wasysym}\usepackage{amsfonts}\usepackage{amssymb}\usepackage{amsbsy}\usepackage{mathrsfs}\usepackage{upgreek}\setlength{\oddsidemargin}{-69pt}\begin{document}$${\bar \eta _{{\rm{fan}}}}/{\bar \eta _{{\rm{cyl}}}}$$\end{document} decrease from 1.7 to 1.05 with the increase of x/d. Simultaneously, the relative efficiency η¯fan/η¯cyl\documentclass[12pt]{minimal}\usepackage{amsmath}\usepackage{wasysym}\usepackage{amsfonts}\usepackage{amssymb}\usepackage{amsbsy}\usepackage{mathrsfs}\usepackage{upgreek}\setlength{\oddsidemargin}{-69pt}\begin{document}$${\bar \eta _{{\rm{fan}}}}/{\bar \eta _{{\rm{cyl}}}}$$\end{document} increases from 1.05 to 1.6 in the main mixing zone (x/d > 10). Fan-shaped holes provide a higher film cooling efficiency at optimal and high values of m and α = 45° (under all other conditions being identical) in comparison with cylindrical holes both in the entrance region and in the main mixing zone. At α = 75°, the efficiency η¯fan\documentclass[12pt]{minimal}\usepackage{amsmath}\usepackage{wasysym}\usepackage{amsfonts}\usepackage{amssymb}\usepackage{amsbsy}\usepackage{mathrsfs}\usepackage{upgreek}\setlength{\oddsidemargin}{-69pt}\begin{document}$${\bar \eta _{{\rm{fan}}}}$$\end{document} is higher than η¯cyl\documentclass[12pt]{minimal}\usepackage{amsmath}\usepackage{wasysym}\usepackage{amsfonts}\usepackage{amssymb}\usepackage{amsbsy}\usepackage{mathrsfs}\usepackage{upgreek}\setlength{\oddsidemargin}{-69pt}\begin{document}$${\bar \eta _{{\rm{cyl}}}}$$\end{document} throughout the whole examined range of injection parameters and throughout the whole examined range of the normalized distance from the location of the injection place. The relative efficiency η¯fan/η¯cyl\documentclass[12pt]{minimal}\usepackage{amsmath}\usepackage{wasysym}\usepackage{amsfonts}\usepackage{amssymb}\usepackage{amsbsy}\usepackage{mathrsfs}\usepackage{upgreek}\setlength{\oddsidemargin}{-69pt}\begin{document}$${\bar \eta _{{\rm{fan}}}}/{\bar \eta _{{\rm{cyl}}}}$$\end{document} decreases from 4 to 1.5 in streamwise direction in the entrance region of the mixing zone (x/d < 5), and it ranges between 1.5 and 2.5 in the main mixing zone (x/d > 5) at all values of injection parameter considered in the paper.
Thermophysics and Aeromechanics – Springer Journals
Published: Sep 1, 2021
Keywords: physical experiment; film cooling; thermal screen efficiency; entrance region; main mixing zone; ring of holes; cylindrical and fan-shaped holes; injection parameter; blowing angle
Read and print from thousands of top scholarly journals.
Already have an account? Log in
Bookmark this article. You can see your Bookmarks on your DeepDyve Library.
To save an article, log in first, or sign up for a DeepDyve account if you don’t already have one.
Copy and paste the desired citation format or use the link below to download a file formatted for EndNote
Access the full text.
Sign up today, get DeepDyve free for 14 days.
All DeepDyve websites use cookies to improve your online experience. They were placed on your computer when you launched this website. You can change your cookie settings through your browser.