Skip to main content Accessibility help

Hot-streak effect on internally air-cooled nozzle guide vanes and shrouds

  • L. Y. Jiang (a1), Y. Han (a1), Z. Zhang (a1), X. Wu (a1), M. Clement (a2) and P. Patnaik (a1)...


The effect of hot streaks from a gas turbine combustor on the thermodynamic load of internally air-cooled nozzle guide vanes (NGVs) and shrouds has been numerically investigated under flight conditions. The study follows two steps: one for the high-fidelity 60° combustor sector with simplified ten NGVs and three thermocouples attached; and the other for the NGV sectors where each sector consists of one high-fidelity NGV (probe NGV) and nine dummy NGVs. The first step identifies which NGV has the highest thermal load and provides the inlet flow boundary conditions for the second step. In the second step, the flow fields and thermal loads of the probe NGVs are resolved in detail.

With the systematically validated physical models, the two-phase flowfield of the combustor-NGVs sector has been successfully simulated. The predicted mean and maximum temperature at the combustor sector exit are in excellent agreement with the experimental data, which provides a solid basis for the hot-streak effect investigation. The results indicate that the second NGV, looking upstream from left, has the highest thermal load. Its maximum surface temperature is 8.4% higher than that for the same NGV but with the mean inlet boundary conditions, and 14.1% higher than the ninth NGV. The finding is consistent with the field-observed NGV damage pattern. To extend the service life of these vulnerable NGVs, some protection methods should be considered.


Corresponding author


Hide All

A version of this paper was first presented at the 24th ISABE Conference in Canberra, Australia.



Hide All
1. Saravanamuttoo, H.I.H., Rogers, G.F.C. and Cohen, H. Gas Turbine Theory, 5th Ed, Pearson Education Limited, 2001, Edinburgh, UK.
2. Graeme, F.E., Cheeseman, K., Maxwell, M., Davison, C. and Patnaik, P.C. Integrated vehicle health management in the Royal Canadian Air force, NATO STO AVT-223 Workshop on Cross-Domain Integrated System Health Management Capability, 2014, Brussels, Belgium.
3. Salvadori, S., Montomoli, F., Martelli, F., Chana, K.S., Qureshi, I. and Povey, T. Analysis on the effect of a non-uniform inlet profile on heat transfer and fluid flow in turbine stages, J Turbomach, 2012, 134, 011012-1.
4. Jenkins, S.C. and Bogard, D.G. Superposition predictions of the reduction of hot-streaks by coolant from a film-cooled guide vane, J Turbomach, 2009, 131, 041002-3.
5. Qureshi, I., Beretta, A. and Povey, T. Effect of simulated combustor temperature non-uniformity on HP vane and end wall heat transfer: an experimental and computational investigation, J Eng Gas Turbines Power, 2011, 133, 031901-1.
6. Khanal, B., He, L., Northall, J. and Adami, P. Analysis of radial migration of hot-streak in swirling flow through high-pressure turbine stage, J Turbomach, 2013, 135, 041005-3.
7. Barigozzi, G., Mosconi, S., Perdichizzi, A. and Ravelli, S. The effect of hot streaks on a high-pressure turbine vane cascade with showerhead film cooling, Int J Turbomach Propulsion Power, 2017, 2, 15, doi:10.3390/ijtpp2030015.
8. Jiang, L.Y., Wu, X. and Zhong Zhang, Z. Conjugate heat transfer of an internally air-cooled nozzle guide vane and shrouds, Adv Mech Eng, 2014, Article ID 146523, 11,
9. Harsqama, S.P., Burton, C.D. and Chana, K.S. Measurements and computations of external heat transfer and film cooing in turbines, the proceedings of the 10th International Symposium on Air Breathe Engines (ISABE), 1991, pp 12761284.
10. Jiang, L.Y. and Corber, P.A. Air Distribution over a Combustor Liner, 2014, IGTI paper, GT-2014-25405.
11. Stiesch, G. Modeling Engine Spray and Combustion Processes, Springer, New York, 2003.10.1007/978-3-662-08790-9
12. ANSYS Fluent Inc. Fluent 19 documentation, 10 Cavendish Court, ANSYS Fluent Inc., ANSYS Fluent Inc., Lebanon, NH, USA, 2018.
13. Jiang, L.Y. and Campbell, I. Radiation benchmarking in a model combustor, J Eng Gas Turbine Power, 2009, 131, 011501.
14. Jiang, L.Y. and Campbell, I. Application of three combustion models to a model combustor, Can Aeronaut Space J, 2005, 51, (1), pp 111.10.5589/q05-001
15. Jiang, L.Y. RANS Modeling of Turbulence in Combustors, Chapter 7, In The book of Turbulence Modelling Approaches – Current State, Development Prospects, Applications, Edited by Dr. Konstantin, V., 2017, IntechOpen Limited, London, UK, ISBN: 978-953-51-5311-5.
16. Menter, F.R. Two-equation eddy-viscosity turbulence models for engineering applications, AIAA J, 1994, 32, (8), pp 15981605.
17. Charbonnier, D., Ott, P., Jonsson, M., Th, Köbke . and Cottier, F. Comparison of numerical investigations with measured heat transfer performance of a film cooled turbine vane, 2008, ASME IGTI paper, GT2008-50623.
18. Oechsle, V.L., Ross, P.T. and Mongia, H.C. High density fuel effects on gas turbine engines, 1987, AIAA-87-1829.
19. Rizk, N.K., Oechsle, V.L., Ross, P.T. and Mongia, H.C. High Density Fuel Effects, 1988, Technical Report AFWAL-TR-88-2046, Wright-Patterson Air Force Base, Aero Propulsion Laboratory, USA.
20. Wilcox, D.C. Turbulence Modeling for CFD, 2nd Ed, DCW Industries Inc., 2002, La Canada, California, USA.
21. Snedden, G., Roos, T. and Naidoo, K. Detailed disc assembly temperature prediction: comparison between CFD and simplified engineering Methods, 2005, ISABE paper 2005-1130.
22. Brown, W.F. Jr. and Setlak, S.J. Aerospace Structural Materials Handbook, 38th Ed, CINDA/USAF CRDA Handbooks Operation, 2004, Purdue University, US.
23. Incropera, F.P. and DeWitt, D.P. Fundamentals of Heat and Mass Transfer, 5th Ed, John Wiley & Sons, 2002, USA.
24. Jiang, L.Y. and Corber, A. Benchmark Modeling of a Gas Turbine Combustor – Phase I, CFD Model, Flow Features, Air Distribution and Combustor Can Temperature Distribution, 2010, LTR-GTL-2010-0088.
25. Robertson, S., Seo, D., Lupandina, O. and Carregie, C. Investigation of T56 First Stage Nozzle Guide Vanes, Mid-Span Cracks – Phase 1, 2015, LTR-SMM-2015-0418.


Related content

Powered by UNSILO

Hot-streak effect on internally air-cooled nozzle guide vanes and shrouds

  • L. Y. Jiang (a1), Y. Han (a1), Z. Zhang (a1), X. Wu (a1), M. Clement (a2) and P. Patnaik (a1)...


Full text views

Total number of HTML views: 0
Total number of PDF views: 0 *
Loading metrics...

Abstract views

Total abstract views: 0 *
Loading metrics...

* Views captured on Cambridge Core between <date>. This data will be updated every 24 hours.

Usage data cannot currently be displayed.