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.

Copyright © 2013 by ASME
Your Session has timed out. Please sign back in to continue.


Butler, T., Joslyn, O. S. H., and Dring, R., 1989, “Redistribution of Inlet Temperature Distortion in an Axial Flow Turbine Stage,” J. Propul. Power, 5(1), pp. 64–71. [CrossRef]
Dorney, D., Davis, R., Edwards, D., and Madhavan, N., 1992, “Unsteady Analysis of Hot-Streak Migration in a Turbine Stage,” J. Propul. Power, 8(2), pp. 520–529. [CrossRef]
Kerrebrock, J. L., and Mikolajczak, A. A., 1970, “Intra-Stator Transport of Rotor Wakes and Its Effects on Compressor Performance,” ASME J. Eng. Power, 92(4), pp. 359–368. [CrossRef]
Gundy-Burlet, K., and Dorney, D., 1997, “Three-Dimensional Simulations of Hot Streak Clocking in 1-1/2 Stage Turbine,” Int. J. Turbo Jet Eng., 14(3), pp. 133–144. [CrossRef]
Takahashi, R., Ni, R., Sharma, O., and Staubach, J., 1996, “Effects of Hot-Streak Indexing in a 1-1/2 Stage Turbine,” AIAA Paper No. 96-2796.
Roback, R., and Dring, R., 1992, “Hot-Streaks and Phantom Cooling in a Turbine Rotor Passage: Part 1—Separate Effects,” ASME Paper No. 92–GT–75.
He, L., Menshikova, V., and Haller, B., 2007, “Effect of Hot-Streak Counts on Turbine Blade Heat Load and Forcing,” J. Propul. Power, 23(6), pp. 1235–1241. [CrossRef]
Zilli, A., Pachidis, V., Jackson, A., and Pilidis, P., 2005, “CFD Investigation of the Performance of a Military HP Axial Turbine Subjected to Inlet Temperature Distortion,” ASME Paper No. GT2005-68503. [CrossRef]
Salvadori, S., Montomoli, F., Martelli, F., Chana, K. S., Qureshi, I., and Povey, T., 2012, “Analysis on the Effect of a Nonuniform Inlet Profile on Heat Transfer and Fluid Flow in Turbine Stages,” ASME J. Turbomach., 134(1), pp. 714–722. [CrossRef]
Gupta, A., Lewis, M., and Daurer, M., 2001, “Swirl Effects on Combustion Characteristics of Premixed Flames,” ASME J. Eng. Gas Turb. Power, 123, pp. 619–626. [CrossRef]
Li, G., and Gutmark, E., 2004, “Effects of Swirler Configurations on Flow Structures and Combustion Characteristics,” ASME Paper No. GT2004-53674. [CrossRef]
Huang, Y., and Yang, V., 2005, “Effect of Swirl on Combustion Dynamics in a Lean-Premixed Swirl-Stabilized Combustor,” Proc. Combust. Inst., 30, pp. 1775–1782. [CrossRef]
Qureshi, I., Smith, A. D., and Povey, T., 2011, “HP Vane Aerodynamics and Heat Transfer in the Presence of Aggressive Inlet Swirl,” ASME Paper No. GT2011-46037. [CrossRef]
Qureshi, I., Beretta, A., Chana, K. S., and Povey, T., 2011, “Effect of Aggressive Inlet Swirl on Heat Transfer and Aerodynamics in an Unshrouded Transonic HP Turbine,” ASME Paper No. GT2011-46038. [CrossRef]
Takahashi, R., and Ni, R., 1990, “Unsteady Euler Analysis of the Redistribution of an Inlet Temperature Distortion in a Turbine,” AIAA Paper No. 90-2262.
Khanal, B., and He, L., 2011, “Influence of Hot Streak Profile on Integrated Heat Load and Stage Performance,” Project Report April-HS, Rolls-Royce, UK.
He, L., 2010, “Fourier Methods for Turbomachinery Applications,” Prog. Aerosp. Sci., 46, pp. 329–341. [CrossRef]
Erdos, J., Alzner, E., and McNally, W., 1977, “Numerical Solution of Periodic Transonic Flows Through a Fan Stage,” AIAA J., 15(11), pp. 1559–1568. [CrossRef]
He, L., 1990, “An Euler Solution for Unsteady Flows Around Oscillating Blades,” ASME J. Turbomach., 112(4), pp. 714–722. [CrossRef]
He, L., 1992, “Method of Simulating Unsteady Turbomachinery Flows With Multiple Perturbations,” AIAA J., 30(11), pp. 2730–2735. [CrossRef]
Li, H., and He, L., 2005, “Towards Intra-Row Gap Optimization for 1 & 1/2 Stage Transonic Compressor,” ASME J. Turbomach, 127(3), pp. 589–598. [CrossRef]
Salvadori, S., Martelli, F., and Adami, P., 2010, “Development of a Phase Lag Approach for the Numerical Evaluation of Unsteady Flows,” Tenth International Congress of Fluid Dynamics, Cairo, Egypt, December 16–19, Paper No. ICFD10-EG-3702.
Gerolymos, G., Michon, G., and Neubauer, J., 2002, “Analysis and Application of Chorochronic Periodicity in Turbomachinery Rotor/Stator Interaction Computations,” J. Propul. Power, 18(5), pp. 1139–1152. [CrossRef]
Spalart, P. R., and Allmaras, S. R., 1992, “A One Equation Turbulence Model for Aerodynamic Flows,” 30th AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, January 6–9, Paper No. AIAA-1992-0439.
Young, J. B., and Horlock, J. H., 2006, “Defining the Efficiency of a Cooled Turbine,” ASME J. Turbomach., 128, pp. 658–667. [CrossRef]
Chana, K., Patel, T., and Mole, A., 2001, “A Summary of Measurements With a Non-Uniform Inlet Temperature Profile From the MT1 Single Stage HP Turbine,” Technical report DERA/AS/PPD/CR010116, Qinetiq, UK.
Khanal, B., and He, L., 2011, “Influence of Inlet Swirl/Hot-Streak Profiles on Integrated Heat Load and Stage Performance,” Project Report, July-SWHS, Rolls-Royce, UK.


Grahic Jump Location
Fig. 1

Performance calculation for a nonadiabatic process

Grahic Jump Location
Fig. 2

Computational domain and surface mesh distribution

Grahic Jump Location
Fig. 3

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

Grahic Jump Location
Fig. 4

NGV blade streamlines for positive swirling flows at inlet

Grahic Jump Location
Fig. 5

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

Grahic Jump Location
Fig. 6

NGV Nu comparison at three radial heights

Grahic Jump Location
Fig. 7

Rotor Nu comparison at three radial heights

Grahic Jump Location
Fig. 8

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

Grahic Jump Location
Fig. 10

Convection of hot fluid, upstream view from NGV exit

Grahic Jump Location
Fig. 9

Convection of hot fluid in NGV passage

Grahic Jump Location
Fig. 11

Convection of hot fluid in NGV passage

Grahic Jump Location
Fig. 12

Convection of hot fluid, upstream view from NGV exit

Grahic Jump Location
Fig. 13

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

Grahic Jump Location
Fig. 14

Pressure loss coefficient (vane aligned)

Grahic Jump Location
Fig. 15

Pressure loss coefficient (passage aligned)

Grahic Jump Location
Fig. 16

Rotor surface streamlines with contours of pressure difference

Grahic Jump Location
Fig. 17

Contours of pressure difference on the rotor blade surface

Grahic Jump Location
Fig. 18

Rotor blade surface heat flux

Grahic Jump Location
Fig. 19

Rotor blade surface heat flux differences

Grahic Jump Location
Fig. 20

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



Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In