EXPERIMENTAL HEAT TRANSFER INVESTIGATION AROUND THE FILM-COOLED LEADING EDGE OF A HIGH-PRESSURE GAS TURBINE ROTOR BLADE.

Cengiz Camci, T. Arts

Research output: Contribution to journalArticle

2 Citations (Scopus)

Abstract

A description is given of an experimental heat transfer investigation around the leading edge of a high-pressure film-cooled gas turbine rotor blade. The measurements were performed in the VKI isentropic compression tube facility using platinum thin film gages painted on a blade made of machinable glass ceramic. Free stream to wall temperature ratio, Reynolds, and Mach numbers were selected from actual aeroengines conditions. Heat transfer data obtained without and with film cooling in a stationary frame are presented. The effects of coolant to free-stream mass weight ratio and temperature ratio were successively investigated.

Original languageEnglish (US)
Journal[No source information available]
StatePublished - 1985

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Turbomachine blades
Gas turbines
Rotors
Heat transfer
Glass ceramics
Coolants
Mach number
Gages
Platinum
Compaction
Reynolds number
Cooling
Thin films
Temperature

All Science Journal Classification (ASJC) codes

  • Mechanical Engineering

Cite this

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abstract = "A description is given of an experimental heat transfer investigation around the leading edge of a high-pressure film-cooled gas turbine rotor blade. The measurements were performed in the VKI isentropic compression tube facility using platinum thin film gages painted on a blade made of machinable glass ceramic. Free stream to wall temperature ratio, Reynolds, and Mach numbers were selected from actual aeroengines conditions. Heat transfer data obtained without and with film cooling in a stationary frame are presented. The effects of coolant to free-stream mass weight ratio and temperature ratio were successively investigated.",
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AU - Arts, T.

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N2 - A description is given of an experimental heat transfer investigation around the leading edge of a high-pressure film-cooled gas turbine rotor blade. The measurements were performed in the VKI isentropic compression tube facility using platinum thin film gages painted on a blade made of machinable glass ceramic. Free stream to wall temperature ratio, Reynolds, and Mach numbers were selected from actual aeroengines conditions. Heat transfer data obtained without and with film cooling in a stationary frame are presented. The effects of coolant to free-stream mass weight ratio and temperature ratio were successively investigated.

AB - A description is given of an experimental heat transfer investigation around the leading edge of a high-pressure film-cooled gas turbine rotor blade. The measurements were performed in the VKI isentropic compression tube facility using platinum thin film gages painted on a blade made of machinable glass ceramic. Free stream to wall temperature ratio, Reynolds, and Mach numbers were selected from actual aeroengines conditions. Heat transfer data obtained without and with film cooling in a stationary frame are presented. The effects of coolant to free-stream mass weight ratio and temperature ratio were successively investigated.

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