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Research Papers

Effect of Rotation on a Gas Turbine Blade Internal Cooling System: Numerical Investigation

[+] Author and Article Information
E. Burberi

Department of Industrial Engineering,
University of Florence,
via S. Marta 3,
Florence 50139, Italy
e-mail: emanuele.burberi@htc.de.unifi.it

D. Massini

Department of Industrial Engineering,
University of Florence,
via S. Marta 3,
Florence 50139, Italy
e-mail: daniele.massini@htc.de.unifi.it

L. Cocchi

Department of Industrial Engineering,
University of Florence,
via S. Marta 3,
Florence 50139, Italy
e-mail: lorenzo.cocchi@htc.de.unifi.it

L. Mazzei

Department of Industrial Engineering,
University of Florence,
via S. Marta 3,
Florence 50139, Italy
e-mail: lorenzo.mazzei@htc.de.unifi.it

A. Andreini

Department of Industrial Engineering,
University of Florence,
via S. Marta 3,
Florence 50139, Italy
e-mail: antonio.andreini@htc.de.unifi.it

B. Facchini

Department of Industrial Engineering,
University of Florence,
via S. Marta 3,
Florence 50139, Italy
e-mail: bruno.facchini@htc.de.unifi.it

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received August 24, 2016; final manuscript received August 30, 2016; published online November 16, 2016. Editor: Kenneth Hall.

J. Turbomach 139(3), 031005 (Nov 16, 2016) (10 pages) Paper No: TURBO-16-1207; doi: 10.1115/1.4034799 History: Received August 24, 2016; Revised August 30, 2016

Increasing turbine inlet temperature is one of the main strategies used to accomplish the demand for increased performance of modern gas turbines. Thus, optimization of the cooling system is becoming of paramount importance in gas turbine development. Leading edge (LE) represents a critical part of cooled nozzles and blades, given the presence of the hot gases stagnation point, and the unfavorable geometrical characteristics for cooling purposes. This paper reports the results of a numerical investigation, carried out to support a parallel experimental campaign, aimed at assessing the rotation effects on the internal heat transfer coefficient (HTC) distribution in a realistic LE cooling system of a high pressure blade. Experiments were performed in static and rotating conditions replicating a typical range of jet Reynolds number (10,000–40,000) and Rotation number (0–0.05). The experimental results consist of flowfield measurements on several internal planes and HTC distributions on the LE internal surface. Hybrid RANS–large eddy simulation (LES) models were exploited for the simulations, such as scale adaptive simulation and detached eddy simulation, given their ability to resolve the complex flowfield associated with jet impingement. Numerical flowfield results are reported in terms of both jet velocity profiles and 2D vector plots on two internal planes, while the HTC distributions are presented as detailed 2D maps together with averaged Nusselt number profiles. A fairly good agreement with experiments is observed, which represents a validation of the adopted modeling strategy, allowing an in-depth interpretation of the experimental results.

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Figures

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Fig. 1

Sketch of the test rig

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Fig. 2

Flow split within the test article and geometry details of the investigated model

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Fig. 5

Sketch of computational domain (a) and mesh (b)

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Fig. 3

PIV plane position (a) and heating inconel sheet location (b)

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Fig. 6

PIV (left) and CFD (right) velocity maps on plane XZ in static and rotating conditions for both HUB and TIP blade configuration at Rej = 30,000

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Fig. 14

Eddy viscosity ratio on the central region of radial symmetry plane

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Fig. 7

PIV and CFD velocity profiles on plane XZ (at z/ZLE = 0.09) in static and rotating conditions for both HUB and TIP blade configurations at Rej = 30,000

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Fig. 8

PIV (left) and CFD (right) velocity maps on plane YZ in static and rotating conditions for both HUB and TIP blade configurations at Rej = 30,000

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Fig. 9

PIV and CFD velocity profiles on plane YZ (at z/ZLE = 0.18) in static and rotating conditions for both HUB and TIP blade configurations at Rej = 30,000

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Fig. 10

Total pressure distribution on a cross-sectional plane (Z = 0 mm) of the feeding channel (DDES simulation, tip configuration)

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Fig. 11

EXP and CFD LE Nusselt 2D maps in static and rotating conditions for both HUB and TIP blade configurations at Rej = 30,000

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Fig. 12

Circumferential (a) and radial (b) EXP and CFD LE Nusselt 2D profiles in static and rotating conditions for both HUB and TIP blade configurations at Rej = 30,000

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Fig. 13

Distribution of M on the domain radial symmetry plane

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