Experimental and numerical investigation of near cooling hole heat fluxes on a film-cooled turbine blade

Research output: Contribution to journalArticle

14 Citations (Scopus)

Abstract

Discrete hole film cooling on highly curved surfaces of a gas turbine blade produces very significant wall temperature gradients and wall heat flux variations near downstream and upstream of rows of circular cooling holes. In this study a set of well-defined external heat transfer coefficient distributions in the presence of discrete hole film cooling is presented. Heat transfer coefficients are measured on the suction side of an HP rotor blade profile in a short-duration facility under well-simulated gas turbine flow conditions. The main emphasis of the study is to evaluate the internal heat flux distributions in a detailed way near the cooling holes by using a computational technique. The method uses the measured external heat transfer coefficients as boundary conditions in addition to available internal heat transfer correlations for the internal passages.

Original languageEnglish (US)
Pages (from-to)63-70
Number of pages8
JournalJournal of Turbomachinery
Volume111
Issue number1
StatePublished - Jan 1989

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Turbomachine blades
Heat flux
Turbines
Heat transfer coefficients
Cooling
Gas turbines
Thermal gradients
Rotors
Boundary conditions
Heat transfer

All Science Journal Classification (ASJC) codes

  • Mechanical Engineering

Cite this

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title = "Experimental and numerical investigation of near cooling hole heat fluxes on a film-cooled turbine blade",
abstract = "Discrete hole film cooling on highly curved surfaces of a gas turbine blade produces very significant wall temperature gradients and wall heat flux variations near downstream and upstream of rows of circular cooling holes. In this study a set of well-defined external heat transfer coefficient distributions in the presence of discrete hole film cooling is presented. Heat transfer coefficients are measured on the suction side of an HP rotor blade profile in a short-duration facility under well-simulated gas turbine flow conditions. The main emphasis of the study is to evaluate the internal heat flux distributions in a detailed way near the cooling holes by using a computational technique. The method uses the measured external heat transfer coefficients as boundary conditions in addition to available internal heat transfer correlations for the internal passages.",
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Experimental and numerical investigation of near cooling hole heat fluxes on a film-cooled turbine blade. / Camci, Cengiz.

In: Journal of Turbomachinery, Vol. 111, No. 1, 01.1989, p. 63-70.

Research output: Contribution to journalArticle

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