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Heat Transfer and Flow Characteristics on a Gas Turbine Shroud
Author(s) -
OBATA Masakazu,
KUMADA Masaya,
IJICHI Nobuaki
Publication year - 2001
Publication title -
annals of the new york academy of sciences
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 1.712
H-Index - 248
eISSN - 1749-6632
pISSN - 0077-8923
DOI - 10.1111/j.1749-6632.2001.tb05862.x
Subject(s) - shroud , mechanics , heat transfer coefficient , heat transfer , materials science , heat flux , turbine , reynolds number , groove (engineering) , tip clearance , flow (mathematics) , rotational speed , work (physics) , turbine blade , thermodynamics , turbulence , mechanical engineering , physics , engineering , metallurgy
A bstract : The work described in this paper is an experimental investigation of the heat transfer from the main flow to a turbine shroud surface, which may be applicable to ceramic gas turbines. Three kinds of turbine shrouds are considered with a flat surface, a taper surface and a spiral groove surface opposite to the blades in an axial flow turbine of actual turbo‐charger. Heat transfer measurements were performed for the experimental conditions of a uniform heat flux or a uniform wall temperature. The effects of the inlet flow angle, rotational speed, and tip clearance on the heat transfer coefficient were clarified under on‐ and off‐design flow conditions. The mean heat transfer coefficient was correlated to the blade Reynolds number and tip clearance, and compared with an experimental correlation and measurements of a flat surface. A comparison was also made for the measurement of static pressure distributions.