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Research Papers: Gas Turbines: Combustion, Fuels, and Emissions

Heat Transfer Augmentation Due to Coolant Extraction on the Cold Side of Active Clearance Control Manifolds

[+] Author and Article Information
Riccardo Da Soghe

Ergon Research srl,
Via Panciatichi 92,
Florence 50127, Italy
e-mail: riccardo.dasoghe@ergonresearch.it

Cosimo Bianchini

Ergon Research srl,
Via Panciatichi 92,
Florence 50127, Italy
e-mail: cosimo.bianchini@ergonresearch.it

Antonio Andreini

Department of Industrial Engineering
Florence (DIEF),
University of Florence,
Via di Santa Marta 3,
Firenze (FI) 50139, Italy
e-mail: antonio.andreini@htc.de.unifi.it

Bruno Facchini

Department of Industrial Engineering
Florence (DIEF),
University of Florence,
Via di Santa Marta 3,
Firenze (FI) 50139, Italy
e-mail: bruno.facchini@htc.de.unifi.it

Lorenzo Mazzei

Department of Industrial Engineering
Florence (DIEF),
University of Florence,
Via di Santa Marta 3,
Firenze (FI) 50139, Italy
e-mail: lorenzo.mazzei@htc.de.unifi.it

1Corresponding author.

Contributed by the Combustion and Fuels Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received June 24, 2015; final manuscript received August 14, 2015; published online September 16, 2015. Editor: David Wisler.

J. Eng. Gas Turbines Power 138(2), 021507 (Sep 16, 2015) (10 pages) Paper No: GTP-15-1218; doi: 10.1115/1.4031383 History: Received June 24, 2015; Revised August 14, 2015

Jet array is an arrangement typically used to cool several gas turbine parts. Some examples of such applications can be found in the impingement cooled region of gas turbine airfoils or in the turbine blade tip clearances control of large aero-engines. In the open literature, several contributions focus on the impingement jets formation and deal with the heat transfer phenomena that take place on the impingement target surface. However, deficiencies of general studies emerge when the internal convective cooling of the impinging system feeding channels is concerned. In this work, an aerothermal analysis of jet arrays for active clearance control (ACC) was performed; the aim was the definition of a correlation for the internal (i.e., within the feeding channel) convective heat transfer coefficient augmentation due to the coolant extraction operated by the bleeding holes. The data were taken from a set of computational fluid-dynamics (CFD) Reynolds-averaged Navier–Stokes (RANS) simulations, in which the behavior of the cooling system was investigated over a wide range of fluid-dynamics conditions. More in detail, several different holes arrangements were investigated with the aim of evaluating the influence of the hole spacing on the heat transfer coefficient distribution. Tests were conducted by varying the feeding channel Reynolds number in a wide range of real engine operative conditions. An in depth analysis of the numerical data set has underlined the opportunity of an efficient reduction through the local suction ratio (SR) of hole and feeding pipe, local Reynolds number, and manifold porosity: the dependence of the heat transfer coefficient enhancement factor (EF) from these parameter is roughly exponential.

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References

Figures

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Fig. 3

Scheme of the heat transfer mechanism on ACC manifolds

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Fig. 2

Scheme of a low pressure turbine ACC system [18]

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Fig. 7

EF averaging locations: (left) lines for lateral averaging and (right) surface for area averaging

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Fig. 8

Lateral-averaged profiles of EF downstream the hole: sensitivity to turbulence model (SR = 1.20, 3.47, and 7.48; Re = 30,000)

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Fig. 6

Schematic representation of the test rig [26]

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Fig. 13

Averaging surface

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Fig. 9

Lateral-averaged profiles of EF downstream the hole: sensitivity to mesh refinement (SR = 3.47 and Re = 30,000)

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Fig. 10

Area-averaged values of EF as a function of SR, Re = 30,000

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Fig. 11

Comparisons among Da Soghe and Andreini [7] correlation predictions and Gritsh et al. experimental data [29]

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Fig. 12

Comparisons between actual CFD and Da Soghe and Andreini [7] correlation

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Fig. 15

HTC distribution across the manifold, σ = 1.4%

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Fig. 16

Wall heat flux contour and coolant flow streamlines—(left) approaching the manifold end cap and (right) manifold central location—σ = 1.4% and Re = 20 k

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Fig. 14

SR distribution across the manifold

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Fig. 17

EF distribution across the manifold, σ = 1.4%

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Fig. 18

EF distribution across the manifold, σ = 1.4%

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Fig. 19

Comparison between CFD evaluations with those related to actual correlation

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