Heat transfer and film-cooling for the endwall of a first stage turbine vane

Karen Ann Thole, Daniel G. Knost

Research output: Contribution to journalArticle

70 Scopus citations

Abstract

Secondary flows that result in turbomachines from inherent pressure gradients in airfoil passages, are the main contributors to aerodynamic losses and high heat transfer to the airfoil endwalls. The endwalls present a challenge to durability engineers in maintaining the integrity of the airfoils. One means of preventing degradation in the turbine is to film-cool components whereby coolant is extracted from the compressor and injected through small cooling holes in the airfoil surfaces. In addition to film-cooling, leakage flows from component interfaces, such as the combustor and turbine, can provide cooling in localized areas but also provide a change to the inlet boundary condition to the passage. This paper presents measurements relevant to the endwall region of a vane, which indicate the importance of considering the inlet flow condition.

Original languageEnglish (US)
Pages (from-to)5255-5269
Number of pages15
JournalInternational Journal of Heat and Mass Transfer
Volume48
Issue number25-26
DOIs
StatePublished - Dec 1 2005

All Science Journal Classification (ASJC) codes

  • Condensed Matter Physics
  • Mechanical Engineering
  • Fluid Flow and Transfer Processes

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