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Research Papers

A Detailed Study of the Interaction Between Two Rows of Cooling Holes

[+] Author and Article Information
Y. Jiang

Osney Thermo-Fluids Laboratory,
Department of Engineering Science,
Oxford University,
Oxford OX2 0ES, UK
e-mail: yuewen.jiang@eng.ox.ac.uk

L. Capone

CFD Methods,
Rolls-Royce PLC,
Derby DE24 8BJ, UK
e-mail: luigi.capone@rolls-royce.com

P. Ireland

Osney Thermo-Fluids Laboratory,
Department of Engineering Science,
Oxford University,
Oxford OX2 0ES, UK
e-mail: peter.ireland@eng.ox.ac.uk

E. Romero

Turbine Systems,
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 September 5, 2017; final manuscript received September 22, 2017; published online February 13, 2018. Editor: Kenneth Hall.

J. Turbomach 140(4), 041008 (Feb 13, 2018) (10 pages) Paper No: TURBO-17-1148; doi: 10.1115/1.4038833 History: Received September 05, 2017; Revised September 22, 2017

An optimal design of film cooling is a key factor in the effort of producing high-efficiency gas turbine. Understanding of the fluid dynamics interaction between cooling holes can help engineers to improve overall thermal effectiveness. Correct prediction through modeling is a very complex problem since multiple phenomena are involved such as mixing, turbulence, and heat transfer. The present work performs an investigation of different cooling configurations ranging from single hole up to two rows. The main objective is to evaluate the double-rows interaction and the effect on film cooling. Strong nonlinear effects are underlined by different simulations, while varying blowing ratio (BR) and geometrical configuration of cooling holes. Meanwhile an initial analysis is performed using flat plate geometry, verification and validation is then extended to realistic stage of high pressure (HP) turbine. Multiple cooling holes configurations are embedded on the pressure side (PS) and suction side (SS) of the single stage. The main outcome is the verification of the thermal effectiveness improvement obtained by cooling jets interaction of multiple rows design. The effects of curvature surface and frame of reference rotation are also evaluated, underlying the differences with standard flat plate test cases.

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Figures

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Fig. 10

Mesh and configuration for the cooled HP stage: (a) stage mesh, (b) mesh blocks after mapped, and (c) wall mesh on vane PS (left) and its close up (right)

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Fig. 11

Comparison of the wall temperature at low BR: (a) single row and (b) double rows

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Fig. 9

Comparison of the averaged effectiveness between single row and double rows

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Fig. 8

Comparison of the vorticity at high BR (3.0): (a) single row and (b) double rows

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Fig. 7

Comparison of the vorticity at low BR (0.5): (a) single row and (b) double rows

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Fig. 6

Comparison of the effectiveness between single row and double rows: (a) single row and (b) double rows

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Fig. 5

Strength of the vortex pair varies with BR: (a) BR = 0.5, (b) BR = 1.5, and (c) BR = 3.0

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Fig. 4

Film cooling results varies with different BRs: (a) flow pattern and temperature contour and (b) comparisons of effectiveness

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Fig. 3

Temperature field: (a) PS, (b) SS, (c) slice at around middle span, and (d) close-up of leading edge

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Fig. 2

Comparison between calculation and measurement

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Fig. 1

Mesh generation of CIMB method: (a) mesh block generated on flat plate, (b) close-up view of a shaped hole, (c) mapped wall mesh and the close-up on PS, (d) a side view of the mapped mesh block on the vane, and (e) a mesh slice near middle span and the close-up

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Fig. 12

Comparison of wall temperature at high BR: (a) single row and (b) double rows

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Fig. 13

Comparison of the averaged effectiveness: (a) NGV and (b) rotor

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