NUMERICAL STUDY ON AERODYNAMIC LOSS OF A TURBINE BLADE WITH FILM COOLING OF FORWARD AND BACKWARD INJECTIONS

2018 ◽  
Author(s):  
Anil Prajapati ◽  
Xianchang Li
Keyword(s):  
Turbine Blade ◽  
Film Cooling ◽  
Numerical Study ◽  
Aerodynamic Loss

Numerical Study of Heat Transfer and Cooling Effectiveness on a Flat-Tip Turbine Blade

2013 ◽  
Author(s):  
Qihe Huang ◽  
Jiao Wang ◽  
Lei He ◽  
Qiang Xu
Keyword(s):  
Heat Transfer ◽  
Turbine Blade ◽  
Film Cooling ◽  
Numerical Study ◽  
Leakage Flow ◽  
Tip Leakage Flow ◽  
Cooling Effectiveness ◽  
Blowing Ratio ◽  
Flow And Heat Transfer ◽  
Blade Tip

A numerical study is performed to simulate the tip leakage flow and heat transfer on the first stage rotor blade tip of GE-E3 turbine, which represents a modern gas turbine blade geometry. Calculations consist of the flat blade tip without and with film cooling. For the flat tip without film cooling case, in order to investigate the effect of tip gap clearance on the leakage flow and heat transfer on the blade tip, three different tip gap clearances of 1.0%, 1.5% and 2.5% of the blade span are considered. And to assess the performance of the turbulence models in correctly predicting the blade tip heat transfer, the simulations have been performed by using four different models (the standard k-ε, the RNG k-ε, the standard k-ω and the SST models), and the comparison shows that the standard k-ω model provides the best results. All the calculations of the flat tip without film cooling have been compared and validated with the experimental data of Azad[1] and the predictions of Yang[2]. For the flat tip with film cooling case, three different blowing ratio (M = 0.5, 1.0, and 1.5) have been studied to the influence on the leakage flow in tip gap and the cooling effectiveness on the blade tip. Tip film cooling can largely reduce the overall heat transfer on the tip. And the blowing ratio M = 1.0, the cooling effect for the blade tip is the best.

A Numerical Study on the Film-Cooling Characteristics of Gas Turbine Blade using CO2

2012 ◽  
Vol 15 (2) ◽  
pp. 41-44
Author(s):  
Sang-Gwon Kim ◽  
Jong-Chul Lee ◽  
Youn-Jea Kim
Keyword(s):  
Gas Turbine ◽  
Turbine Blade ◽  
Film Cooling ◽  
Numerical Study ◽  
Gas Turbine Blade

Experimental and Numerical Study on the Flat-Plate Film Cooling Enhancement Using the Vortex Generator Downstream for the Fan-Shaped Hole Configuration

2020 ◽  
Vol 142 (3) ◽  
Author(s):  
Chao Zhang ◽  
Jie Wang ◽  
Xuebin Liu ◽  
Liming Song ◽  
Jun Li ◽  
...  
Keyword(s):  
Film Cooling ◽  
Numerical Study ◽  
Infrared Camera ◽  
Vortex Generator ◽  
Cylindrical Hole ◽  
Film Cooling Effectiveness ◽  
Aerodynamic Loss ◽  
Blowing Ratio ◽  
Cooling Enhancement ◽  
Shaped Hole

Abstract The shaped hole is the significant advancement for improving film cooling that has been practically achieved. This present study puts forward a new design combining the vortex generator (VG) with the shaped hole (FV). To investigate the effect of the new design, experiments were carried out to measure the film cooling performance of the four different configurations including the baseline cylindrical hole (CH) model, the model combing the cylindrical hole with VG (CV), shaped hole model (FAN), and FV model, at the blowing ratio varying at M = 0.5, 1.0, 1.5, 2.0, 2.5, and 3.0 by the infrared camera. Experimental results show that the FV model performs the best among the four models at each blowing ratio. The FV model could improve the area-averaged film effectiveness at most 25.5% than that of the CH model at M = 2.0. Moreover, the FV model could improve the area-averaged film cooling effectiveness at most 431% than that of the CH model at M = 3.0. Besides, the aerodynamic analysis of the four models at different blowing ratios was carried out by the numerical study. The simulation results show that the introduction of VG causes slightly more aerodynamic loss while the fan-shaped hole improves it. The aerodynamic performance of the FV model is almost the same as the CH model when M < 2 and smaller than that of the CH model when M > 2.

Experimental and numerical study of supersonic film cooling

AIAA Journal ◽  
1998 ◽  
Vol 36 ◽  
pp. 915-923 ◽  
Author(s):  
B. Aupoix ◽  
A. Mignosi ◽  
S. Viala ◽  
F. Bouvier ◽  
R. Gaillard
Keyword(s):  
Film Cooling ◽  
Numerical Study

scholarly journals Comparison of turbine blade film cooling efficiency between PSP and TLC techniques in a stationary wind tunnel

AIP Advances ◽  
2021 ◽  
Vol 11 (1) ◽  
pp. 015333
Author(s):  
Xiaojian He ◽  
Haiwang Li ◽  
Guoqin Zhao ◽  
Ruquan You
Keyword(s):  
Wind Tunnel ◽  
Turbine Blade ◽  
Film Cooling ◽  
Cooling Efficiency ◽  
Film Cooling Efficiency
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