Experimental and computational studies of film cooling with compound angle injection Metadata

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Title

  • Main Title Experimental and computational studies of film cooling with compound angle injection

Creator

  • Author: Goldstein, R.J.
    Creator Type: Personal
  • Author: Eckert, E.R.G.
    Creator Type: Personal
  • Author: Patankar, S.V.
    Creator Type: Personal
  • Author: Simon, T.W.
    Creator Type: Personal
    Creator Info: Univ. of Minnesota, Minneapolis, MN (United States). Dept. of Mechanical Engineering

Contributor

  • Sponsor: United States. Department of Energy.
    Contributor Type: Organization
    Contributor Info: USDOE, Washington, DC (United States)

Publisher

  • Name: Clemson Univ., SC (United States)
    Place of Publication: United States

Date

  • Creation: 1995-12-31

Language

  • English

Description

  • Content Description: The thermal efficiency of gas turbine systems depends largely on the turbine inlet temperature. Recent decades have seen a steady rise in the inlet temperature and a resulting reduction in fuel consumption. At the same time, it has been necessary to employ intensive cooling of the hot components. Among various cooling methods, film cooling has become a standard method for cooling of the turbine airfoils and combustion chamber walls. The University of Minnesota program is a combined experimental and computational study of various film-cooling configurations. Whereas a large number of parameters influence film cooling processes, this research focuses on compound angle injection through a single row and through two rows of holes. Later work will investigate the values of contoured hole designs. An appreciation of the advantages of compound angle injection has risen recently with the demand for more effective cooling and with improved understanding of the flow; this project should continue to further this understanding. Approaches being applied include: (1) a new measurement system that extends the mass/heat transfer analogy to obtain both local film cooling and local mass (heat) transfer results in a single system, (2) direct measurement of three-dimensional turbulent transport in a highly-disturbed flow, (3) the use of compound angle and shaped holes to optimize film cooling performance, and (4) an exploration of anisotropy corrections to turbulence modeling of film cooling jets.
  • Physical Description: 31 p.

Subject

  • Keyword: Heat Transfer
  • Keyword: Combustion
  • Keyword: Anisotropy
  • Keyword: Film Cooling
  • STI Subject Categories: 33 Advanced Propulsion Systems
  • Keyword: Gas Turbines
  • Keyword: Thermal Efficiency
  • STI Subject Categories: 20 Fossil-Fueled Power Plants
  • Keyword: Turbulence
  • Keyword: Jets

Source

  • Conference: Advanced turbine systems (ATS) annual review, Morgantown, WV (United States), 17-18 Oct 1995

Collection

  • Name: Office of Scientific & Technical Information Technical Reports
    Code: OSTI

Institution

  • Name: UNT Libraries Government Documents Department
    Code: UNTGD

Resource Type

  • Article

Format

  • Text

Identifier

  • Other: DE96008942
  • Report No.: DOE/MC/29061--96/C0668
  • Report No.: CONF-9510109--35
  • Grant Number: FC21-92MC29061
  • Office of Scientific & Technical Information Report Number: 219510
  • Archival Resource Key: ark:/67531/metadc664212

Note

  • Display Note: OSTI as DE96008942