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Research Papers

Shower Head and Trailing Edge Cooling Influence on Transonic Vane Aero Performance

[+] Author and Article Information
Ranjan Saha

Heat and Power Technology,
KTH Royal Institute of Technology,
Stockholm SE-100 44, Sweden
e-mail: ranjan.saha@energy.kth.se

Jens Fridh, Torsten H. Fransson

Heat and Power Technology,
KTH Royal Institute of Technology,
Stockholm SE-100 44, Sweden

Boris I. Mamaev

Energy Oil & Gas Design Department,
Siemens LLC,
B. Tatarskaya str., 9,
Moscow 115184, Russia

Mats Annerfeldt, Esa Utriainen

Siemens Industrial Turbomachinery AB,
Finspong SE-612 83, Sweden

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received June 29, 2014; final manuscript received July 8, 2014; published online August 5, 2014. Editor: Ronald Bunker.

J. Turbomach 136(11), 111001 (Aug 05, 2014) (11 pages) Paper No: TURBO-14-1098; doi: 10.1115/1.4028024 History: Received June 29, 2014; Revised July 08, 2014

An experimental investigation on a cooled nozzle guide vane (NGV) has been conducted in an annular sector to quantify aerodynamic influences of shower head (SH) and trailing edge (TE) cooling. The investigated vane is a typical high pressure gas turbine vane, geometrically similar to a real engine component, operated at a reference exit Mach number of 0.89. The investigations have been performed for various coolant-to-mainstream mass–flux ratios. New loss equations are derived and implemented regarding coolant aerodynamic losses. Results lead to a conclusion that both TE cooling and SH film cooling increase the aerodynamic loss compared to an uncooled case. In addition, the TE cooling has higher aerodynamic loss compared to the SH cooling. Secondary losses decrease with inserting SH film cooling compared to the uncooled case. The TE cooling appears to have less impact on the secondary loss compared to the SH cooling. Area-averaged exit flow angles around midspan increase for the TE cooling.

Copyright © 2014 by ASME
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References

Figures

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Fig. 7

Spanwise exit flow angle distributions at nominal conditions

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Fig. 6

Vane profile loading distribution

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Fig. 5

Mach number distribution at 50% span

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Fig. 4

View of five-hole probe

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Fig. 3

Cooling hole location (distorted view)

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Fig. 2

Axial section view of test sector

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Fig. 1

Test sector with three NGVs

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Fig. 8

Spanwise exit flow angle distributions for various SH cases

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Fig. 9

Spanwise exit flow angle distributions for various TE cases

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Fig. 10

(a)–(c) Vorticity distributions

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Fig. 11

(a)–(c) Total pressure ratio

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Fig. 12

Mass-averaged kinetic energy loss distribution at nominal conditions

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Fig. 13

Mass-averaged primary loss distribution at nominal conditions

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Fig. 18

Integrated kinetic energy loss for various Y values

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Fig. 19

Circumferential loss distribution around midspan zone

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Fig. 14

Mass-averaged kinetic energy loss distribution for various SH film cooling cases

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Fig. 20

Circumferential primary loss distribution around midspan zone

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Fig. 15

Mass-averaged primary loss distribution for various SH film cooling cases

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Fig. 16

Mass-averaged kinetic energy loss distribution for various TE cooling cases

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Fig. 17

Mass-averaged primary loss distribution for various TE cooling cases

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Fig. 21

Comparison of loss equations in pitchwise direction

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Fig. 22

Comparison of loss equations in spanwise direction

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