IGTC-9 IMPINGEMENT COOLING OF GAS TURBINE COMPONENTS(Session A-3 Heat Transfer III (Internal Surface))

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概要

• 論文の詳細を見る

• Impingement cooling heat transfer data was obtained for test geometries relevant to full coverage gas turbine combustion chamber wall cooling with the full flame tube pressure loss across the impingement plate. An impingement hole pitch to diameter ratio (X/D) of between 10 and 13 is appropriate for this application and two test geometries within this range were studied. The impingement gap to hole diameter ratio (Z/D) was the main parameter studied together with the hole Reynolds number. A significant influence of Z/D on the heat transfer was found and a general correlation equation derived. Evidence of enhanced impingement heat transfer for Z/D less than unity was found.

• 公益社団法人日本ガスタービン学会の論文

著者

• Andrews G.E.

  Department of Fuel and Energy University of Leeds

• Andrews G.e.

  Department Of Fuel And Energy Engineering University Of Leeds

• Hussain C.I.

  Department of Fuel and Energy, University of Leeds

• Hussain C.i.

  Department Of Fuel And Energy University Of Leeds

• Andrews G.E.

  Department of Fuel and Energy, University of Leeds

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• IGTC-9 IMPINGEMENT COOLING OF GAS TURBINE COMPONENTS(Session A-3 Heat Transfer III (Internal Surface))
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