[1]
Sunden B., Xie G.N., Gas turbine blade tip heat transfer and cooling: a literature survey. Heat Transfer Engineering, 2010, 31: 527–554.
[2]
Denton J.D., Loss mechanisms in turbomachines. ASME Journal of Turbomachinery, 1993, 115: 621–656.
[3]
Bunker R.S., A review of turbine blade tip heat transfer. Annals of the New York Academy of Sciences, 2001, 934: 64–79.
[4]
Bunker R.S., Axial turbine blade tips: function, design, and durability. AIAA Journal of Propulsion and Power, 2012, 22: 271–285.
[5]
Han J.C., Fundamental gas turbine heat transfer. Journal of Thermal Science and Engineering Applications, 2013, 5(2): 021007.
[6]
Lee S.W., Moon H.S., Lee S.E., Tip gap height effects on flow structure and heat/mass transfer over plane tip of a high-turning turbine rotor blade. International Journal of Heat and Fluid Flow, 2009, 30(2): 198–210.
[7]
Bindon J.P., The measurement and formation of tip clearance loss. Journal of Turbomachinery, 1989, 3(111): 257–263.
[8]
Kwak J.S., Han J.C., Heat-transfer coefficients of a turbine blade-tip and near-tip regions. Journal of Thermophysics and Heat Transfer, 2003, 17(3): 297–303.
[9]
Gao J., Fu W., Wang F., Experimental and numerical investigations of tip clearance flow and loss in a variable geometry turbine cascade. Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy, 2018, 232(2): 157–169.
[10]
Kwak J.S., Han J.C., Heat transfer coefficients on the squealer tip and near squealer tip regions of a gas turbine blade. Journal of Heat Transfer, 2003, 125(4): 669–677.
[11]
Lee S.W., Kim S.U., Tip gap height effects on the aerodynamic performance of a cavity squealer tip in a turbine cascade in comparison with plane tip results: Part 1—tip gap flow structure. Experiments in Fluids, 2010, 49(5): 1039–1051.
[12]
Lee S.W., Choi M.Y., Tip gap height effects on the aerodynamic performance of a cavity squealer tip in a turbine cascade in comparison with plane tip results: Part 2—aerodynamic losses. Experiments in Fluids, 2010, 49(3): 713–723.
[13]
Maral H., Senel C.B., Kavurmacioglu L., A parametric and computational aerothermal investigation of squealer tip geometry in an axial turbine: a parametric approach suitable for future advanced tip carving optimizations. Turbo Expo: Power for Land, Sea, and Air, 2016, Paper No. GT2016-58107.
[14]
Maral H., Senel C.B., Deveci K., et al., A genetic algorithm based multi-objective optimization of squealer tip geometry in axial flow turbines: a constant tip gap approach. Journal of Fluids Engineering, 2020, 142(2): 021402.
[15]
Jin J., Song Y., Yu J., et al., Effect of arbitrary blade tip design on tip leakage flow. Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy, 2020, 234(1): 19–30.
[16]
Huang T., Li H., Yuan X., et al., Influences of depth and rim width of squealer tip on the leakage flow and heat transfer. Global Power and Propulsion Society, 2021. DOI: 10.33737/gpps21-tc-181.
[17]
Nasir H., Ekkad S.V., Kontrovitz D.M., Effect of tip gap and squealer geometry on measured heat transfer over a HPT rotor blade tip. ASME International Mechanical Engineering Congress and Exposition, 2003, Paper No. IMECE2003-41294.
[18]
Kwak J.S., Ahn J., Han J.C., et al., Heat transfer coefficients on the squealer tip and near-tip regions of a gas turbine blade with single or double squealer. Journal of Turbomachinery, 2003, 125(4): 778–787.
[19]
Ledezma G.A., Allen J., Bunker R.S., An experimental and numerical investigation into the effects of squealer blade tip modifications on aerodynamic performance. ASME Turbine Blade Tip Symposium, 2013, Paper No. TBTS2013-2004.
[20]
Krishnababu S.K., Newton P.J., Dawes W.N., Aerothermal investigations of tip leakage flow in axial flow turbines-part I: effect of tip geometry and tip clearance gap. Journal of turbomachinery, 2009, 131(1): 55–68.
[21]
Ma H., Tian Y., Numerical investigation of effects of non-uniform tip clearance on flow field inside a turbine cascade. ASME International Mechanical Engineering Congress and Exposition, 2016, Paper No. IMECE2016-66509.
[22]
Park J.S., Lee S.H., Lee W.S., et al., Heat transfer and secondary flow with a multi-cavity gas turbine blade tip. Journal of Thermophysics and Heat Transfer, 2016, 30(1): 120–129.
[23]
Kaczyński P., Szwaba R., Wasilczuk F., Leakage flow reduction in different configuration of labyrinth seal on a turbine blade tip. Journal of Physics: Conference Series, 2018, 1101(1): 012012.
[24]
Du K., Li Z., Li J., et al., Influences of a multi-cavity tip on the blade tip and the over tip casing aerothermal performance in a high pressure turbine cascade. Applied Thermal Engineering, 2019, 147: 347–360.
[25]
Tong F., Gou W., Li L., et al., Numerical investigation of high pressure turbine blade tip-shaping effects on the aerothermal a dynamic performance. Multidiscipline Modeling in Materials and Structures, 2019, 6(15): 1121–1135.
[26]
Zou Z., Shao F., Li Y., et al., Dominant flow structure in the squealer tip gap and its impact on turbine aerodynamic performance. Energy, 2017, 138: 167–184.
[27]
Zou Z., Xuan L., Chen Y., et al., Effects of flow structure on heat transfer of squealer tip in a turbine rotor blade. International Communications in Heat and Mass Transfer, 2020, 114: 10458.
[28]
Zeng F., Zhang W., Wang Y., et al., Effects of squealer geometry of turbine blade tip on the tip-leakage flow and loss. Journal of Thermal Science, 2021, 30(4): 1376–1387.
[29]
Jiang S., Yu J., Wang H., et al., Experimental investigation of the bending clearance on the aerodynamic performance in turbine blade tip region. Energy, 2020, 197: 117234.
[30]
Kim J., Seo W., Chung H., et al., Effect of shelf squealer tip configuration on aerothermal performance of gas turbine blade. International Journal of Thermal Sciences, 2021, 168: 107056.
PDF(8795 KB)
