The film-cooling performance in a low-speed rotor blade of a 1-1/2 turbine stage has been examined using LES approach. Two rows of film holes were positioned on the rotor blade surface, one on the pressure surface and the other one the suction surface, with axial locations of 24.2% and 22.6% of the chord length, respectively. Each row has three cylindrical film-cooling holes with a diameter (D) of 4 mm and a tangential injection angle of 28o on the pressure side and 36o on the suction side. The Reynolds number, based on the mainstream velocity of the turbine outlet and axial length of the turbine, was fixed at Re=1.92×105, the coolant-to-mainstream density ratio (DR) was about 2.0, and the speed of the rotor blade was taken to be 1800 rpm. ...
Experimental investigations were performed to measure the local heat transfer coefficient (hg ) dist...
Increasing the rotor inlet temperature is one of the key technologies in raising gas turbine engine ...
Film cooling effectiveness on a gas turbine blade tip on the near tip pressure side and on the squea...
Film cooling is one of the cooling techniques to cool the hot section components of a gas turbine en...
In gas turbines, the operating temperature of the primary fluid is very high. In order to lessen the...
AbstractFilm cooling of turbine blades is an effective way to cool the blade and ensure the long lif...
MasterRecently desired for more efficient, turbine inlet total temperature has been increased, but t...
Detailed film cooling effectiveness distributions were measured on the stationary blade tip and on t...
High turbine inlet temperature becomes necessary for increasing thermal efficiency of modern gas tur...
In order to increase thermal efficiency of a gas turbine, higher turbine inlet temperature (TIT) is ...
The hot gas temperature in gas turbine engines is far above the permissible metal temperatures. Adva...
The performance of gas turbine engines can be improved by increasing the inlet gas temperature. Turb...
In order to increase thermal efficiency of a gas turbine, higher turbine inlet temperature (TIT) is ...
ABSTRACT A computational analysis was carried out to comprehend the mechanism of rotation on the fil...
Turbine blades operate under a harsh environmental condition, and the inlet temperature of gas turbi...
Experimental investigations were performed to measure the local heat transfer coefficient (hg ) dist...
Increasing the rotor inlet temperature is one of the key technologies in raising gas turbine engine ...
Film cooling effectiveness on a gas turbine blade tip on the near tip pressure side and on the squea...
Film cooling is one of the cooling techniques to cool the hot section components of a gas turbine en...
In gas turbines, the operating temperature of the primary fluid is very high. In order to lessen the...
AbstractFilm cooling of turbine blades is an effective way to cool the blade and ensure the long lif...
MasterRecently desired for more efficient, turbine inlet total temperature has been increased, but t...
Detailed film cooling effectiveness distributions were measured on the stationary blade tip and on t...
High turbine inlet temperature becomes necessary for increasing thermal efficiency of modern gas tur...
In order to increase thermal efficiency of a gas turbine, higher turbine inlet temperature (TIT) is ...
The hot gas temperature in gas turbine engines is far above the permissible metal temperatures. Adva...
The performance of gas turbine engines can be improved by increasing the inlet gas temperature. Turb...
In order to increase thermal efficiency of a gas turbine, higher turbine inlet temperature (TIT) is ...
ABSTRACT A computational analysis was carried out to comprehend the mechanism of rotation on the fil...
Turbine blades operate under a harsh environmental condition, and the inlet temperature of gas turbi...
Experimental investigations were performed to measure the local heat transfer coefficient (hg ) dist...
Increasing the rotor inlet temperature is one of the key technologies in raising gas turbine engine ...
Film cooling effectiveness on a gas turbine blade tip on the near tip pressure side and on the squea...