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Research Papers

A Three-Dimensional Conjugate Approach for Analyzing a Double-Walled Effusion-Cooled Turbine Blade

[+] Author and Article Information
Gladys C. Ngetich

Department of Engineering Science,
University of Oxford,
Oxford OX1 3PJ, UK
e-mail: gladys.ngetich@oriel.ox.ac.uk

Alexander V. Murray

Department of Engineering Science,
University of Oxford,
Oxford OX1 3PJ, UK
e-mail: alexander.murray@eng.ox.ac.uk

Peter T. Ireland

Department of Engineering Science,
University of Oxford,
Oxford OX1 3PJ, UK
e-mail: peter.ireland@eng.ox.ac.uk

Eduardo Romero

Rolls-Royce Plc.,
Bristol BS34 7QE, UK
e-mail: eduardo.romero@rolls-royce.com

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received July 20, 2018; final manuscript received August 29, 2018; published online October 17, 2018. Editor: Kenneth Hall.

J. Turbomach 141(1), 011002 (Oct 17, 2018) (10 pages) Paper No: TURBO-18-1168; doi: 10.1115/1.4041379 History: Received July 20, 2018; Revised August 29, 2018

A double-wall cooling scheme combined with effusion cooling offers a practical approximation to transpiration cooling which in turn presents the potential for very high cooling effectiveness. The use of the conventional conjugate computational fluid dynamics (CFD) for the double-wall blade can be computationally expensive and this approach is therefore less than ideal in cases where only the preliminary results are required. This paper presents a computationally efficient numerical approach for analyzing a double-wall effusion cooled gas turbine blade. An existing correlation from the literature was modified and used to represent the two-dimensional distribution of film cooling effectiveness. The internal heat transfer coefficient was calculated from a validated conjugate analysis of a wall element representing an element of the aerofoil wall and the conduction through the blade solved using a finite element code in ANSYS. The numerical procedure developed has permitted a rapid evaluation of the critical parameters including film cooling effectiveness, blade temperature distribution (and hence metal effectiveness), as well as coolant mass flow consumption. Good agreement was found between the results from this study and that from literature. This paper shows that a straightforward numerical approach that combines an existing correlation for film cooling from the literature with a conjugate analysis of a small wall element can be used to quickly predict the blade temperature distribution and other crucial blade performance parameters.

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References

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Figures

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Fig. 1

Features of a double-walled effusion cooled concept turbine blade

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Fig. 2

Features of a double-walled effusion cooled concept turbine blade including leading edge showerhead cooling holes, pin-fin bank, TE slots and the flow direction

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Fig. 3

CFD results of flow velocity contour distribution in the unit cell from Murray et al. [23]

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Fig. 4

Double-wall blade with the unit wall element showing the definition of the geometrical parameters

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Fig. 5

Outer skin of the blade where numerical analysis is performed

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Fig. 6

ηc−Re characteristics compared to that of three simple duct cooling systems, characterized by L/Dh = 20, 40 and 60

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Fig. 7

Steps in the iterative code used to determine aerofoil wall temperature

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Fig. 8

Model setup in ansys steady-state thermal module

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Fig. 9

(a) Film cooling effectiveness on the blade and (b) its corresponding adiabatic wall temperature at Po,c=40 bar

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Fig. 10

Nondimensional film flow rate per hole, film cooling effectiveness, metal effectiveness and dimensionless external heat transfer coefficient as a function of the blade's dimensionless streamwise location

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Fig. 11

A graph of effectiveness as a function of nondimensional coolant mass flow, m* from this study

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