Effect of inlet conditions on endwall secondary flows

Kristina S. Hermanson, Karen A. Thole

Research output: Contribution to conferencePaper

Abstract

Exit combustor flow and thermal fields entering downstream stator vane passages in a gas turbine engine are highly non-uniform. These flow and thermal fields can significantly affect the development of the secondary flows in the turbine passages attributing to high platform heat transfer and large aerodynamic losses. This paper presents an analysis of the effects of both the temperature and velocity profiles on the secondary flows in the end wall region of a first stage stator vane geometry. These effects were assessed using the predicted flow field results from computational fluid dynamics (CFD) simulations. Prior to using the predictions, these CFD simulations were benchmarked against flow field data measured in a large scale, linear, turbine vane cascade. Good agreement occurred between the computational predictions and experimentally measured secondary flows. Analyses of the results for several different cases indicate the stagnation pressure gradient is a key parameter in determining the character of the secondary flows.

Original languageEnglish (US)
StatePublished - Jan 1 1999
Event37th Aerospace Sciences Meeting and Exhibit, 1999 - Reno, United States
Duration: Jan 11 1999Jan 14 1999

Other

Other37th Aerospace Sciences Meeting and Exhibit, 1999
CountryUnited States
CityReno
Period1/11/991/14/99

All Science Journal Classification (ASJC) codes

  • Space and Planetary Science
  • Aerospace Engineering

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    Hermanson, K. S., & Thole, K. A. (1999). Effect of inlet conditions on endwall secondary flows. Paper presented at 37th Aerospace Sciences Meeting and Exhibit, 1999, Reno, United States.