Research Papers

Analysis of Radial Migration of Hot-Streak in Swirling Flow Through High-Pressure Turbine Stage

[+] Author and Article Information
L. He

Department of Engineering Science,
University of Oxford,
Oxford, UK

P. Adami

CFD Methods,
Rolls-Royce PLC,
Moor Lane,
Derby, UK

Contributed by International Gas Turbine Institute (IGTI) of ASME for publication in the Journal of Turbomachinery. Manuscript received June 28, 2012; final manuscript received August 19, 2012; published online June 3, 2013. Assoc. Editor: David Wisler.

J. Turbomach 135(4), 041005 (Jun 03, 2013) (11 pages) Paper No: TURBO-12-1089; doi: 10.1115/1.4007505 History: Received June 28, 2012; Revised August 19, 2012

The high pressure (HP) turbine is subject to inlet flow nonuniformities resulting from the combustor. A lean-burn combustor tends to combine temperature variations with strong swirl and, although considerable research efforts have been made to study the effects of a circumferential temperature nonuniformity (hot-streak), there is relatively little known about the interaction between the two. This paper presents a numerical investigation of the transonic test HP stage MT1 behavior under the combined influence of the swirl and hot-streak. The in house Rolls-Royce HYDRA numerical computational fluid dynamics (CFD) suite is used for all the simulations of the present study. Baseline configurations with either hot-streak or swirl at the stage inlet are analyzed to assess the methodology and to identify reference performance parameters through comparisons with the experimental data. Extensive computational analyses are then carried out for the cases with hot-streak and swirl combined, including both the effects of the combustor-nozzle guide vane (NGV) clocking and the direction of the swirl. The present results for the combined hot-streak and swirl cases reveal distinctive radial migrations of hot fluid in the NGV and rotor passages with considerable impact on the aerothermal performance. It is illustrated that the blade heat transfer characteristics and their dependence on the clocking position can be strongly affected by the swirl direction. A further computational examination is carried out on the validity of a superposition of the influences of swirl and hot-streak. It shows that the blade heat transfer in a combined swirl and hot-streak case cannot be predicted by the superposition of each in isolation.

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Fig. 1

Performance calculation for a nonadiabatic process

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Fig. 2

Computational domain and surface mesh distribution

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Fig. 3

Swirl configurations investigated at the vane inlet (downstream view from the combustor)

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Fig. 4

NGV blade streamlines for positive swirling flows at inlet

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Fig. 5

Vane isentropic Mach number at three radial heights (vane-aligned positive swirl case)

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Fig. 6

NGV Nu comparison at three radial heights

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Fig. 7

Rotor Nu comparison at three radial heights

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Fig. 8

Combined swirl and hot-streak profiles (downstream view from the combustor)

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Fig. 10

Convection of hot fluid, upstream view from NGV exit

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Fig. 9

Convection of hot fluid in NGV passage

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Fig. 11

Convection of hot fluid in NGV passage

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Fig. 12

Convection of hot fluid, upstream view from NGV exit

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Fig. 13

Convection of hot fluid and the swirl vortex in the NGV passage, isovolume of T0

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Fig. 14

Pressure loss coefficient (vane aligned)

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Fig. 15

Pressure loss coefficient (passage aligned)

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Fig. 16

Rotor surface streamlines with contours of pressure difference

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Fig. 17

Contours of pressure difference on the rotor blade surface

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Fig. 18

Rotor blade surface heat flux

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Fig. 19

Rotor blade surface heat flux differences

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Fig. 20

Rotor blade surface heat fluxes (left: the direct solution of the combined case; right: the superimposed)




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