An advanced impingement/film cooling scheme for gas turbines - Numerical study

A. Immarigeon, Ibrahim Hassan

Research output: Contribution to journalArticle

28 Citations (Scopus)

Abstract

Purpose - The present study aims to conduct a numerical investigation of a novel film cooling scheme combining in-hole impingement cooling and flow turbulators with traditional downstream film cooling, and was originally proposed by Pratt & Whitney Canada for high temperature gas turbine applications. Design/methodology/approach - Steady-state simulations were performed and the flow was considered incompressible and turbulent. The CFD package FLUENT 6.1 was used to solve the Navier-Stokes equations numerically, and the preprocessor, Gambit, was used to generate the required grid. Findings - It was determined that the proposed scheme geometry can prevent coolant lift-off much better than standard round holes, since the cooling jet remains attached to the surface at much higher blowing rates, indicating a superior performance for the proposed scheme. Research limitations/implications - The present study was concerned only with the downstream effectiveness aspect of performance. The performance related to the heat transfer coefficient is a prospective topic for future studies. Practical implications - Advanced and innovative cooling techniques are essential in order to improve the efficiency and power output of gas turbines. This scheme combines in-hole impingement cooling and flow turbulators with traditional downstream film cooling for improved cooling capabilities. Originality/value - This new advanced cooling scheme both combines the advantages of traditional film cooling with those of impingement cooling, and provides greater airfoil protection than traditional film cooling. This study is of value for those interested in gas turbine cooling.

Original languageEnglish
Pages (from-to)470-493
Number of pages24
JournalInternational Journal of Numerical Methods for Heat and Fluid Flow
Volume16
Issue number4
DOIs
Publication statusPublished - 2006
Externally publishedYes

Fingerprint

Film Cooling
Gas Turbine
Gas turbines
Cooling
Numerical Study
FLUENT
Heat Transfer Coefficient
Airfoil
Numerical Investigation
Design Methodology
Navier-Stokes Equations
Grid
Blow molding
Airfoils
Coolants
Heat transfer coefficients
Output
Navier Stokes equations

Keywords

  • Computational geometry
  • Cooling
  • Films (states of matter)
  • Flow measurement
  • Gas flow

ASJC Scopus subject areas

  • Mechanics of Materials
  • Mechanical Engineering
  • Computer Science Applications
  • Applied Mathematics

Cite this

An advanced impingement/film cooling scheme for gas turbines - Numerical study. / Immarigeon, A.; Hassan, Ibrahim.

In: International Journal of Numerical Methods for Heat and Fluid Flow, Vol. 16, No. 4, 2006, p. 470-493.

Research output: Contribution to journalArticle

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