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Research Papers

Aerothermal Performance of Shielded Vane Design

[+] Author and Article Information
Ioanna Aslanidou

Osney Thermofluids Laboratory,
Department of Engineering Science,
University of Oxford,
Oxford OX2 0ES, UK
e-mail: ioanna.aslanidou@mdh.se

Budimir Rosic

Osney Thermofluids Laboratory,
Department of Engineering Science,
University of Oxford,
Oxford OX2 0ES, UK

1Present address: Future Energy Centre, Mälardalen University, Västerås 721 23, Sweden.

2Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received October 2, 2016; final manuscript received May 30, 2017; published online July 19, 2017. Assoc. Editor: Rolf Sondergaard.

J. Turbomach 139(11), 111003 (Jul 19, 2017) (11 pages) Paper No: TURBO-16-1267; doi: 10.1115/1.4037126 History: Received October 02, 2016; Revised May 30, 2017

This paper presents an experimental investigation of the concept of using the combustor transition duct wall to shield the nozzle guide vane leading edge. The new vane is tested in a high-speed experimental facility, demonstrating the improved aerodynamic and thermal performance of the shielded vane. The new design is shown to have a lower average total pressure loss than the original vane, and the heat transfer on the vane surface is overall reduced. The peak heat transfer on the vane leading edge–endwall junction is moved further upstream, to a region that can be effectively cooled as shown in previously published numerical studies. Experimental results under engine-representative inlet conditions showed that the better performance of the shielded vane is maintained under a variety of inlet conditions.

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References

Figures

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Fig. 1

Schematic view of experimental facility including details of the working section [21]

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Fig. 2

CAD sketch with original and shielded cascade for the experimental facility: (a) original cascade and (b) shielded cascade

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Fig. 3

View points of the cascade for IR measurements: (a) view points from the sides (1 and 2) and downstream (3) and (b) view points from above and upstream (4) and above and downstream (5)

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Fig. 4

Views of the cascade for IR measurements, corresponding to the viewpoints depicted in Fig. 3: (a) vane pressure side (view 1), (b) vane leading edge (view 2), (c) vane suction side (view 3), (d) hub endwall, viewed from upstream (view 4), and (e) hub endwall, viewed from downstream (view 5)

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Fig. 5

Total pressure loss coefficient downstream of the cascade for the new shielded vane compared to the datum case, experimental result

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Fig. 6

Spatially resolved total pressure loss coefficient downstream of the cascade for low inlet turbulence, experimental result: (a) original vane cascade and (b) shielded vane cascade

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Fig. 7

Mass-weighted average total pressure loss coefficient for the original and the new shielded vane, experimental result

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Fig. 8

Spatially resolved total pressure loss coefficient on the endwall for the original and shielded case, for low inlet turbulence, experimental result: (a) original case and (b) shielded case

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Fig. 9

Isentropic Mach number distribution on the vane surface for 50% span, experimental and numerical result

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Fig. 10

Comparison of yaw angle downstream of the original and the new shielded vane, experimental result: (a) mass-weighted pitchwise average, (b) original vane, and (c) shielded vane

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Fig. 11

Nondimensional temperature contours for the original and the new shielded vane at 50% span, numerical result

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Fig. 12

Nusselt number on the pressure and the suction side of the original and the new shielded vane, numerical result

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Fig. 13

Isentropic Mach number distribution on the original and the new shielded vane at 5% span, numerical result

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Fig. 14

Nusselt number on the vane pressure side for the original and shielded vane (view 1, Fig. 4(a)), experimental result: (a) original vane and (b) shielded vane

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Fig. 15

Leading edge fillet for the original and shielded vane: (a) pressure side and (b) suction side

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Fig. 16

Nusselt number on the vane leading edge for the original and shielded vane (view 2, Fig. 4(b)), experimental result: (a) original vane and (b) shielded vane

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Fig. 17

Nusselt number on the vane suction side for the original and shielded vane (view 3, Fig. 4(c)), experimental result: (a) original vane and (b) shielded vane

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Fig. 18

Comparison of the Nusselt number on the vane suction side for the shielded vane relative to the original (view 3, Fig. 4(c)), experimental result

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Fig. 19

Nusselt number on the vane endwall viewed from upstream for the original and shielded vane (view 4, Fig. 4(d)), experimental result: (a) original vane and (b) shielded vane

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Fig. 20

Nusselt number on the vane endwall viewed from downstream for the original and shielded vane (view 5, Fig. 4(e)), experimental result: (a) original vane and (b) shielded vane

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Fig. 21

Comparison of Nusselt number on the vane endwall viewed from downstream for the shielded vane relative to the original (view 5, Fig. 4(e)), experimental result

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Fig. 22

Nusselt number on the vane endwall between vanes 2 and 3 (view from downstream) for the original and shielded vane, experimental result: (a) original vane and (b) shielded vane

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Fig. 23

Comparison of Nusselt number on the endwall between vanes 2 and 3 (view from downstream) for the shielded vane relative to the original, experimental result

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Fig. 24

Swirl profile upstream of the cascade (viewed from downstream), experimental measurement: (a) total pressure loss, (b) orientation, (c) yaw angle, and (d) pitch angle

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Fig. 25

Comparison of the Nusselt number on the vane suction side between the original and shielded vane with different inlet conditions (view 3, Fig. 4(c)), experimental result: (a) high inlet turbulence and (b) inlet swirl

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Fig. 26

Comparison of the Nusselt number on the vane endwall viewed from downstream between the original and shielded vane with different inlet conditions (view 5, Fig. 4(e)), experimental result: (a) high inlet turbulence and (b) inlet swirl

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