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Direct numerical simulations of a high pressure turbine vane

Direct numerical simulations of a high pressure turbine vane
Direct numerical simulations of a high pressure turbine vane
In this paper we establish a benchmark data set of a generic high-pressure turbine vane generated by direct numerical simulation (DNS) to resolve fully the flow. The test conditions for this case are a Reynolds number of 0.57 million and an exit Mach number of 0.9, which is representative of a modern transonic high-pressure turbine vane. In this study we first compare the simulation results with previously published experimental data. We then investigate how turbulence affects the surface flow physics and heat transfer. An analysis of the development of loss through the vane passage is also performed. The results indicate that free-stream turbulence tends to induce streaks within the near wall flow, which augment the surface heat transfer. Turbulent breakdown is observed over the late suction surface, and this occurs via the growth of two-dimensional Kelvin-Helmholtz spanwise roll-ups, which then develop into lambda vortices creating large local peaks in the surface heat transfer. Turbulent dissipation is found to significantly increase losses within the trailing-edge region of the vane.
0889-504X
1-23
Wheeler, A.P.S.
83dfe34b-1668-4905-a4a7-6fe08e0f763a
Sandberg, R.D.
353c42e9-dd2c-4779-8160-27681561adf5
Sandham, N.
0024d8cd-c788-4811-a470-57934fbdcf97
Pichler, R.
5150d90a-340b-4ebd-aac0-3d4c977e996b
Michelasso, V.
830c6cbf-02f2-4d93-822b-efffca6249ff
Laskowski, G.
36ddea7e-c98b-4f06-bf90-5491a7527bea
Wheeler, A.P.S.
83dfe34b-1668-4905-a4a7-6fe08e0f763a
Sandberg, R.D.
353c42e9-dd2c-4779-8160-27681561adf5
Sandham, N.
0024d8cd-c788-4811-a470-57934fbdcf97
Pichler, R.
5150d90a-340b-4ebd-aac0-3d4c977e996b
Michelasso, V.
830c6cbf-02f2-4d93-822b-efffca6249ff
Laskowski, G.
36ddea7e-c98b-4f06-bf90-5491a7527bea

Wheeler, A.P.S., Sandberg, R.D., Sandham, N., Pichler, R., Michelasso, V. and Laskowski, G. (2016) Direct numerical simulations of a high pressure turbine vane. Journal of Turbomachinery, 138 (7), 1-23. (doi:10.1115/1.4032435).

Record type: Article

Abstract

In this paper we establish a benchmark data set of a generic high-pressure turbine vane generated by direct numerical simulation (DNS) to resolve fully the flow. The test conditions for this case are a Reynolds number of 0.57 million and an exit Mach number of 0.9, which is representative of a modern transonic high-pressure turbine vane. In this study we first compare the simulation results with previously published experimental data. We then investigate how turbulence affects the surface flow physics and heat transfer. An analysis of the development of loss through the vane passage is also performed. The results indicate that free-stream turbulence tends to induce streaks within the near wall flow, which augment the surface heat transfer. Turbulent breakdown is observed over the late suction surface, and this occurs via the growth of two-dimensional Kelvin-Helmholtz spanwise roll-ups, which then develop into lambda vortices creating large local peaks in the surface heat transfer. Turbulent dissipation is found to significantly increase losses within the trailing-edge region of the vane.

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Accepted/In Press date: 24 October 2015
Published date: 7 February 2016
Organisations: Aeronautics, Astronautics & Comp. Eng

Identifiers

Local EPrints ID: 384645
URI: https://eprints.soton.ac.uk/id/eprint/384645
ISSN: 0889-504X
PURE UUID: 8d624f12-0c69-4243-a9f6-0e1f6d30839c
ORCID for N. Sandham: ORCID iD orcid.org/0000-0002-5107-0944

Catalogue record

Date deposited: 02 Dec 2015 15:34
Last modified: 10 Sep 2019 00:49

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