Migration of combustor exit profiles through high pressure turbine vanes

M. D. Barringer, K. A. Thole, M. D. Polanka, J. P. Clark, P. J. Koch

Research output: Chapter in Book/Report/Conference proceedingConference contribution

4 Scopus citations


The high pressure turbine stage within gas turbine engines is exposed to combustor exit flows that are nonuniform in both stagnation pressure and temperature. These highly turbulent flows typically enter the first stage vanes with significant spatial gradients near the inner and outer diameter endwalls. These gradients can result in secondary flow development within the vane passage that is different than what classical secondary flow models predict. The heat transfer between the working fluid and the turbine vane surface and endwalls is directly related to the secondary flows. The goal of the current study was to examine the migration of different inlet radial temperature and pressure profiles through the high turbine vane of a modern turbine engine. The tests were performed using an inlet profile generator located in the Turbine Research Facility (TRF) at the Air Force Research Laboratory (AFRL). Comparisons of area-averaged radial exit profiles are reported as well as profiles at three vane pitch locations to document the circumferential variation in the profiles. The results show that the shape of the total pressure profile near the endwalls at the inlet of the vane can alter the redistribution of stagnation enthalpy through the airfoil passage significantly. Total pressure loss and exit flow angle variations are also examined for the different inlet profiles.

Original languageEnglish (US)
Title of host publicationProceedings of the ASME Turbo Expo 2007 - Power for Land, Sea, and Air
Number of pages12
StatePublished - 2007
Event2007 ASME Turbo Expo - Montreal, Que., Canada
Duration: May 14 2007May 17 2007

Publication series

NameProceedings of the ASME Turbo Expo
Volume4 PART B


Other2007 ASME Turbo Expo
CityMontreal, Que.

All Science Journal Classification (ASJC) codes

  • General Engineering


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