[1] Jiang Y., Yue G., Dong P., et al., Investigation on film cooling with swirling coolant flow by optimizing the inflow chamber. International Communications in Heat and Mass Transfer, 2017, 88: 99–107.
[2] Yao Y., Zhang J.-Z., Tan X.-M., Numerical study of film cooling from converging slot-hole on a gas turbine blade suction side. International Communications in Heat and Mass Transfer, 2014, 52: 61–72.
[3] Sunden B., Xie G., Gas turbine blade tip heat transfer and cooling: A literature survey. Heat Transfer Engineering, 2010, 31(7): 527–554.
[4] Zhou C., Hodson H., Lock G., Thermal performance of cooled tips in a high-pressure turbine cascade. Journal of Propulsion and Power, 2012, 28(5): 900–911.
[5] Zhou C., Hodson H., Tibbott I., et al., Effects of winglet geometry on the aerodynamic performance of tip leakage flow in a turbine cascade. Journal of Turbomachinery, 2013, 135(5): 1–10.
[6] Yan X., Huang Y., He K., Investigations into heat transfer and film cooling effect on a squealer-winglet blade tip. International Journal of Heat and Mass Transfer, 2017, 115(Part B): 955–978.
[7] Wang Y., Song Y., Yu J., et al., Effect of the injection orientation and position on the leakage flow in a honeycomb-tip turbine cascade. International Journal of Heat and Mass Transfer, 2019, 144: 118633.
[8] Yang D., Feng Z., Tip leakage flow and heat transfer predictions for turbine blades. Proceedings of the ASME Turbo Expo 2007, 2007, Paper No. GT2007-27728.
[9] Yang D., Yu X., Feng Z., Investigation of leakage flow and heat transfer in a gas turbine blade tip with emphasis on the effect of rotation. Journal of Turbomachinery- Transactions of the ASME, 2010, 132(4): 041010.
[10] 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: 104588.
[11] Volino R.J., Control of tip leakage in a high-pressure turbine cascade using tip blowing. Journal of Turbomachinery, 2017, 139(6): 1–12.
[12] Chung J., Baek S., Hwang W., Experimental investigation of aerodynamic performance due to blade tip clearance in a gas turbine rotor cascade. Journal of Thermal Science, 2022, 31(1): 173–178.
[13] Bi S., Wang L., Wang F., et al., Effect of squealer tip with deep scale depth on the aero-thermodynamic characteristics of tip leakage flow. Journal of Thermal Science, 2022, 31(5): 1773–1789.
[14] 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.
[15] Liu J.-J., Li P., Zhang C., et al., Flowfield and heat transfer past an unshrouded gas turbine blade tip with different shapes. Journal of Thermal Science, 2013, 22(2): 128–134.
[16] Kwak J.S., Han J.C., Heat transfer coefficients and film cooling effectiveness on the squealer tip of a gas turbine blade. Journal of Turbomachinery, 2003, 125(4): 648–657.
[17] Cheng F.-N., Zhang J.-Z., Chang H.-P., et al., Investigations of film-cooling effectiveness on the squealer tip with various film-hole configurations in a linear cascade. International Journal of Heat and Mass Transfer, 2018, 117: 344–357.
[18] Park J.S., Lee D.H., Rhee D.-H., et al., Heat transfer and film cooling effectiveness on the squealer tip of a turbine blade. Energy, 2014, 72: 331–343.
[19] 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.
[20] Arisi A., Phillips J., Ng W.F., et al., An experimental and numerical study on the aerothermal characteristics of a ribbed transonic squealer-tip turbine blade with purge flow. Journal of Turbomachinery, 2016, 138(10): 1–11.
[21] Li F., Feng Z., Liu Z., Film cooling and aerodynamic performance on multi-cavity squealer tip of a turbine blade. ASME Turbo Expo 2021: Turbomachinery Technical Conference and Exposition, Volume 5A: Heat Transfer—Combustors; Film Cooling, American Society of Mechanical Engineers, 2021, Paper No. GT2021-59993.
[22] Li F., Jia Z., Zhang W., et al., Experimental comparisons of film cooling performance for the multi-cavity tips at two different tip gaps. International Journal of Heat and Mass Transfer, 2022, 187: 122566.
[23] Zhang B.L., Zhu H.R., Yao C.Y., et al., Investigation on aerothermal performance of a rib-slot scheme on the multi-cavity tip of a gas turbine blade. International Journal of Heat and Mass Transfer, 2021, 176: 121408.
[24] Ma H., Zhang Q., He L., et al., Cooling injection effect on a transonic squealer tip—part I: Experimental heat transfer results and CFD validation. Journal of Engineering for Gas Turbines and Power, 2017, 139(5): 052506.
[25] Ma H., Wang Z., Wang L., et al., Cooling injection effect on a transonic squealer tip—part II: Analysis of aerothermal interaction physics. Journal of Engineering for Gas Turbines and Power, 2017, 139(5): 052507.
[26] Lin J., Li H., You R., et al., Experimental study on the film cooling characteristics of three complex tip structures. Journal of Thermal Science, 2023, 32(4): 1378–1392.
[27] Zhang L.J., Jaiswal R.S., Turbine nozzle endwall film cooling study using pressure-sensitive paint. Journal of Turbomachinery, 2001, 123(4): 730–738.
[28] Jones T.V., Theory for the use of foreign gas in simulating film cooling. International Journal of Heat and Fluid Flow, 1999, 20(3): 349–354.
[29] Moffat R.J., Describing the uncertainties in experimental results. Experimental Thermal and Fluid Science, 1988, 1(1): 3–17.
[30] Roache P.J., Perspective: A method for uniform reporting of grid refinement studies. Journal of Fluids Engineering, 1994, 116(3): 405–413.