Effect of incidence on wall heating rates and aerodynamics on a film cooled transonic turbine blade

Cengiz Camci, Tony Arts

Research output: Contribution to journalConference articlepeer-review

Abstract

This study investigates the influence of incidence on convective heat transfer to highly curved surfaces of a film cooled turbine rotor blade. A computational study of free stream inviscid aerodynamics without cooling at various incidences is followed by well documented measured heat transfer data sets. The heat transfer experiments are discussed for cases with and without film cooling, performed under realistic gas turbine flow conditions in the short duration heat transfer facility of the von Karman Institute for Fluid Dynamics. The precise location of the stagnation point and the iso-Mach number contours in the passage for each incidence (-10°, 0°, 10°, +10°) are presented for a nominal exit Mach number of 0.94. The free stream mass flow rate was kept constant for each experiment at different incidence levels. Three rows of compound angled discrete cooling holes are located near the leading edge in a shower-head configuration.

Original languageEnglish (US)
Pages (from-to)GT46 10p
JournalAmerican Society of Mechanical Engineers (Paper)
StatePublished - Jan 1 1990
EventInternational Gas Turbine and Aeroengine Congress and Exposition - Brussels, Belg
Duration: Jun 11 1990Jun 14 1990

All Science Journal Classification (ASJC) codes

  • Mechanical Engineering

Fingerprint

Dive into the research topics of 'Effect of incidence on wall heating rates and aerodynamics on a film cooled transonic turbine blade'. Together they form a unique fingerprint.

Cite this