FEATURES OF ORGANIZATION OF FILM COOLING OF HIGH TEMPERATURE GAS TURBINES BLADES


  • A. A. Khalatov Institute of Engineering Thermophysics of the National Academy of Sciences of Ukraine
  • A. S. Kovalenko NTUU «Kyiv Politechnic Inztitute»
  • S. B. Reznik SE IVCHENKO-PROGRESS
DOI: https://doi.org/10.31472/ihe.4.2017.02
Keywords: high temperature turbine, cooling air, convective-film cooling, front edge of blade

Abstract

The features of the release of the cooling air in the interscapular channel high temperature gas turbines at the film cooling are considered. Possibilities of its local distribution on contour of an entrance edge of the perforated blades are investigated. The presented calculations show that the substantial increase in the cooling efficiency can be attained due to channels of small dimension in the blade wall.

 

References

Theory of aerojet engines. Edited Shlyakhtenko S. M., M.: «Mashinostroenie», 1985, 568 pp. (Rus,)

Venediktow V.D. Gas dynamics of cooled turbines.

Shvets I.T, Дybаn Е.P. Air cooling of gas turbines parts. К., «NauKova dumka», 1974. 488 pp. (Rus,)

Дeiths М.Е. Enginiering gas dinamics. M., «Energia», 19734. 392 pp. (Rus,)

Scientific contribution to creation of aircraft engines. In two books. Book 2. A group of authors edited by Scibin V.A. and Sjolonin V.I. M., «Mashinostroenie», 2000. 616 pp.: (Rus,)

Goldstein R.J., Eckert E.R.G., Borggraf F Effects of hole geometri and density on three-dimensional film cooling. Int. J. Heat and Mass Transfer. 1974. Vol. 17, №. 5. P. 011002-1 - 011002-11.

Colban W.F., Thole K.A., Bogard D.A. Fim-cooling correlation for shaped holes on a flat-plate surface. ASME J.of Turbomachinery. 2011. Vol. 133, №. 1. P. 595 - 607.

S. Riznyk, A. Artushenko. Aeroengine high pressure turbine blade cooling system concept. Proceedings of ASME Turbo Expo 2013: Turbine Technical Conference and Exposition, GT 2013,San Antonio, Texas,USA.

Andrew C. Chambers, DavidR.H. Gillespie, Peter T. Ireland, Geoffrey Dailey. The effect of initial cross flow on the cooling performance of a narrow impingement channel. Journal of Heat Transfer. 2005. Vol. 127, APRIL, pp 358364.

Ioannis Ieronymidis, David R.H. Gillespie, Peter T. Ireland, Robert Kingstton. Detailed heat transfer measurements in a model. Proceedings of GT2006 ASME Paper No.GT2006-91231, Turbo Expo 2006: Power for Land, Sea and Air, May 8 -11, 2006, Barcelona, Spain.

Andrew C. Chambers, David R.H. Gillespie, Peter T. Ireland, Mark Mitchell. Enhancement of impingement cooling in a high cross flow channel using shaped impingement cooling holes. Proceedings of GT2006 ASME Turbo Expo 2006: Power for Land, Sea and Air, May 8 -11, 2006, Barcelona, Spain.

Chi Zhang, Quanhong Xu, Mengneng Zhao, Yuzhen Lin and Gaoen Liu. Effect impingement/effusion holearea ratio on discharge coefficients of double cooling wall. Proceedings of GT2006 ASME Turbo Expo 2006: Power for Land, Sea and Air, May 8 -11, 2006, Barcelona, Spain.

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Published
2017-03-24
How to Cite
Khalatov, A., Kovalenko, A., & Reznik, S. (2017). FEATURES OF ORGANIZATION OF FILM COOLING OF HIGH TEMPERATURE GAS TURBINES BLADES. Thermophysics and Thermal Power Engineering, 39(4), 11-20. https://doi.org/https://doi.org/10.31472/ihe.4.2017.02
Issue
Vol 39 No 4 (2017): Industrial Heat Engineering
Section
Heat and Mass Exchange Processes
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