Effect of Temperature Ratio on Jet Impingement Heat Transfer in Active Clearance Control Systems

Author:

Da Soghe Riccardo1,Bianchini Cosimo1,D’Errico Jacopo1,Tarchi Lorenzo1

Affiliation:

1. Ergon Research srl, via Campani 50, 50127 Florence, Italy e-mail:

Abstract

Impinging jet arrays are typically used to cool several gas turbine parts. Some examples of such applications can be found in the internal cooling of high-pressure turbine airfoils or in the turbine blade tip clearances control of aero-engines. The effect of the wall-to-jets temperature ratio (TR) on heat transfer is generally neglected by the correlations available in the open literature. In the present contribution, the impact of the temperature ratio on the heat transfer for a real engine active clearance control system is analyzed by means of validated computational fluid dynamics (CFD) computations. At different jets Reynolds number and considering several impingement array arrangements, a wide range of target wall-to-jets temperature ratio is accounted for. Computational results prove that both local and averaged Nusselt numbers reduce with increasing. An in-depth analysis of the numerical data shows that the last mentioned evidence is motivated by both the heat transfer incurring between the spent coolant flow and the fresh jets and the variation of gas properties with temperature through the boundary layer. A scaling procedure, based on the TR power law, was proposed to estimate the Nusselt number at different wall temperature levels necessary to correct available open-literature correlations, typically developed with small temperature differences, for real engine applications.

Publisher

ASME International

Subject

Mechanical Engineering

Reference28 articles.

1. Self-acting Clearance Control for Turbine Blade Outer Air Seals;Justak,2009

2. Effects of Inlet Temperature Uniformity and Nonuniformity on the Tip Leakage Flow and Rotor Blade Tip and Casing Heat Transfer Characteristics;Rahman;ASME J. Turbomach,2012

3. Tip Clearance Effects on Inlet Hot Streak Migration Characteristics in High Pressure Stage of a Vaneless Counter-rotating Turbine;Qingjun;ASME J. Turbomach,2010

4. High Pressure Turbine Test Hardware;Halila,1982

5. CF6 Jet Engine Performance Improvement—Low Pressure Turbine Active Clearance Control;Beck,1982

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