Aero-thermal optimization of a gas turbine blade endwall with non-axisymmetric contouring and purge flow

2021 ◽  
Vol 178 ◽  
pp. 121626
Author(s):  
Zhi Tao ◽  
Zhendong Guo ◽  
Boyang Yu ◽  
Liming Song ◽  
Jun Li
Keyword(s):  
Gas Turbine ◽  
Turbine Blade ◽  
Gas Turbine Blade ◽  
Thermal Optimization ◽  
Purge Flow

Effects of the positive pre-swirl purge flow on endwall aero-thermal performance of a gas turbine blade

2021 ◽  
Vol 163 ◽  
pp. 106805
Author(s):  
Zhi Tao ◽  
Fengchao Li ◽  
Boyang Yu ◽  
Peiyuan Zhu ◽  
Liming Song ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Turbine Blade ◽  
Thermal Performance ◽  
Gas Turbine Blade ◽  
Purge Flow

scholarly journals An alternative coating material for gas turbine blade for aerospace applications

2020 ◽  
Vol 1706 ◽  
pp. 012183
Author(s):  
Yajnesh M Poojari ◽  
Koustubh S Annigeri ◽  
Nilesh Bandekar ◽  
Kiran U Annigeri ◽  
Vinayak badiger ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Turbine Blade ◽  
Coating Material ◽  
Gas Turbine Blade ◽  
Aerospace Applications

Defect assessment in gas turbine blade coatings using non-contact thermography

2020 ◽  
Author(s):  
M. Mahesh Kumar ◽  
A.H.V. Pavan ◽  
R. Markandeya ◽  
Kulvir Singh
Keyword(s):  
Gas Turbine ◽  
Turbine Blade ◽  
Gas Turbine Blade ◽  
Defect Assessment

Recent Advances in the Study of Film Cooling on the Gas Turbine Blade

2014 ◽  
Vol 971-973 ◽  
pp. 143-147 ◽  
Author(s):  
Ping Dai ◽  
Shuang Xiu Li
Keyword(s):  
Gas Turbine ◽  
Turbine Blade ◽  
Film Cooling ◽  
Gas Turbines ◽  
High Performance ◽  
Leading Edge ◽  
Development Trend ◽  
Research Progress ◽  
Gas Turbine Blade ◽  
New Generation

The development of a new generation of high performance gas turbine engines requires gas turbines to be operated at very high inlet temperatures, which are much higher than the allowable metal temperatures. Consequently, this necessitates the need for advanced cooling techniques. Among the numerous cooling technologies, the film cooling technology has superior advantages and relatively favorable application prospect. The recent research progress of film cooling techniques for gas turbine blade is reviewed and basic principle of film cooling is also illustrated. Progress on rotor blade and stationary blade of film cooling are introduced. Film cooling development of leading-edge was also generalized. Effect of various factor on cooling effectiveness and effect of the shape of the injection holes on plate film cooling are discussed. In addition, with respect to progress of discharge coefficient is presented. In the last, the future development trend and future investigation direction of film cooling are prospected.

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