The impact of turbine guide vanes on a three-dome combustor’s lean blowout limit and blowout process was experimentally investigated. The parameters studied include the presence of the turbine guide vanes or not and the blockage ratio of turbine guide vanes. It is shown that the presence of turbine guide vanes and an increase in the blockage ratio increase the lean blowout fuel-to-air ratio. From the images of flame spontaneous emission captured by the high-speed camera, the coupling of the combustor with turbine guide vanes can alter the sequence of the blowout among the three domes, and localized tiny flame lumps have been observed to develop into larger flames during lean blowout. However, flames within the combustor are established independently near blowout, and no reignition is observed. Furthermore, the turbine guide vanes have been found to shorten the duration of the blowout process and enhance the likelihood of blowout by increasing the lean fuel-to-air ratio.
ZHANG Xiaoyan
,
LIU Fuqiang
,
LI Ziyan
,
WANG Kaixing
,
RUAN Changlong
,
YANG Jinhu
,
MU Yong
,
LIU Cunxi
,
XU Gang
. Influence of Turbine Guide Vanes on the Lean Blowout Characteristics of a Three-Dome Combustor[J]. Journal of Thermal Science, 2025
, 34(5)
: 1569
-1582
.
DOI: 10.1007/s11630-025-2139-9
[1] Stabe R., Whitney W., Moffitt T., Performance of a high-work low aspect ratio turbine tested with a realistic inlet radial temperature profile. 20th Joint Propulsion Conference, Cincinnati, America, 1984, Paper No: AIAA-84-1161.
DOI: https://doi.org/10.2514/6.1984-1161.
[2] Whitney W., Stabe R., Moffitt T., Description of the warm core turbine facility and the warm annular cascade facility recently installed at NASA Lewis Research Center. Aerospace Congress and Exposition, Los Angeles, America, 1980, SAE Technical Paper 801122.
DOI: https://ntrs.nasa.gov/citations/19810049754.
[3] Joslyn H.D., Dring R.P., A trace gas technique to study mixing in a turbine stage. Journal of Turbomachinery, 1988, 110(1): 38–43.
[4] Roux S., Cazalens M., Poinsot T., Outlet-boundary- condition influence for large eddy simulation of combustion instabilities in gas turbines. Journal of Propulsion and Power, 2008, 24(3): 541–546.
[5] Jiang L.Y., Carscallen B., Okulov P., et al., Effect of nozzle guide vanes on flow parameters at the exit of a micro gas turbine combustor. Proceedings of the ASME Turbo Expo 2009: Power for Land, Sea, and Air, Orlando, America, 2009, Paper No: GT2009-59694.
[6] Klapdor E.V., Simulation of combustor-turbine interaction in a jet engine. Technische Universität Darmstadt, Darmstadt, German, 2011.
[7] Raynaud F., Eggels R.L.G.M., Staufer M., et al., Towards unsteady simulation of combustor-turbine interaction using an integrated approach. ASME Tutbo Expo 2015: Turbine Conference and Exposition, Montreal, Canada, 2015, Paper No: GT2015-42110.
DOI: https://doi.org/10.1115/GT2015-42110.
[8] Hilgert J., Martin B., Holger W., et al., Numerical studies on combustor-turbine interaction at the large scale turbine rig (LSTR). ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition, Charlotte, America, 2017, Paper No: GT2017-64504.
DOI: https://doi.org/10.1115/GT2017-64504.
[9] Cha M., Sungkook H., Peter I., et al., Experimental and numerical investigation of combustor-turbine interaction using an isothermal, nonreacting tracer. Engineering for Gas Turbines Power, 2012, 134(8): 081501.
[10] Alexander K., Marc T., Steffen G., Design, integration and operation of a rotating combustor-turbine-interaction test rig within the scope of EC FP7 project factor. Proceedings of 13th European Conference on Turbomachinery Fluid dynamics & Thermodynamics, Lausanne, Switzerland, 2019.
[11] Koupper C., Guillaume B., Laurent G., et al., Large eddy simulations of the combustor turbine interface: Study of the potential and clocking effects. ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition, Seoul, South Korea, 2016, Paper No: GT2016-56443.
DOI: https://doi.org/10.1115/GT2016-56443.
[12] Koupper C., Gianluca C., Laurent G., et al., Development of an engine representative combustor simulator dedicated to hot streak generation. Journal of Turbomachinery, 2014, 136(11): 111007.
[13] Koupper C., Unsteady multi-component simulations dedicated to the impact of the combustion chamber on the turbine of aeronautical gas turbines. Institute National Polytechnique de Toulouse, France, 2015.
[14] Morata E.C., Impact of the unsteady aerothermal environment on the turbine blades temperature. Institute National Polytechnique de Toulouse, France, 2012.
[15] Andreini A., Tommaso B., Massimiliano I., et al., Hybrid RANS-LES modeling of the aerothermal field in an annular hot streak generator for the study of combustor-turbine interaction. Journal of Engineering for Gas Turbines and Power, 2017, 139(2): 021508.
[16] Miki K., Jeffrey M., Meng-Sing L., Computational study of combustor-turbine interactions. Journal of Propulsion and Power, 2018, 34(6): 1529–1541.
[17] Yoko M.J., Sun S.J., Van der Spuy S.J., et al., Multi-fidelity modelling of an impingement/effusion cooled gas turbine combustor liner. Applied Thermal Engineering, 2021, 185: 116318.
[18] Wang G.F., Xia. Y.F., Ye C.R. Progress on light-round ignition dynamics in annular combustor. Journal of Experiments in Fluid Mechanics, 2019, 33(1): 14–28.
[19] Ye C.R., Wang G.F., Fang Y., et al., Ignition dynamics in annular combustor with turbine guide vanes. Journal of Combustion Science and Technology, 2020, 26: 75–80. (in Chinese)
[20] Wu Y.W., Weng C.S., Zheng Q., et al., Experimental research on the performance of a rotating detonation combustor with a turbine guide vane. Energy, 2021, 218: 119580.
