...Markus Schwänen; Andrew Duggleby Internal cooling of the trailing edge region in a gas turbine blade is typically achieved with an array of pin fins. In order to better understand the effectiveness of this configuration, high performance computations are performed on cylindrical pin fins...

... or on the momentum thickness. Heat flux and temperature variations along the surface of a turbine blade may cause significant differences between the shapes and sizes of the velocity and thermal boundary layer profiles. Therefore, correlations are needed which relate the states of both the velocity and thermal...

...T. S. Dhanasekaran; Ting Wang Film cooling techniques have been successfully applied to gas turbine blades to protect them from the hot flue gas. However, a continuous demand of increasing the turbine inlet temperature to raise the efficiency of the turbine requires continuous improvement in film...

... the project “Efficient turbomachinery blade cooling with various outlet coolant configurations,” Grant No. N501 367134. These results are very promising for turbomachinery effective cooling applications, whereby concerning the reduction in the holes’ diameter and the thickness of the cooling plate...

... 02 07 2010 21 09 2010 21 09 2010 aerodynamics blades channel flow cooling engines flow visualisation jets liquid crystals shafts stagnation flow turbines turbine cooling heat transfer impingement cooling liquid crystal The increasing operating temperature...

... 07 07 2010 13 08 2010 13 08 2010 blades cooling jets mass transfer rotational flow stagnation flow turbines impingement/effusion cooling gas turbine heat transfer Coriolis force rotation Recent increase in turbine inlet temperatures necessitates more...

...Yao-Hsien Liu; Michael Huh; Je-Chin Han; Hee-Koo Moon Heat transfer and pressure drop have been experimentally investigated in an equilateral triangular channel ( D h = 1.83 cm ) , which can be used to simulate the internal cooling passage near the leading edge of a gas turbine blade. Three...

...Chao Bai; Liqiu Wang We perform a constructal design of heat conduction in a blade-configured disk-shaped domain with uniform heat generation and periphery heat-sink by introducing a transition line from two-path conduction to one-path conduction in the domain. This orderly arranged blade...

... of the initial wall heat flux into cooled rotor blades. During the spinning-up period, the rotor is spun up to nearly its nominal speed (from 0 rpm to 6200 rpm) resulting in preheating due to drag losses. The long duration of this experiment ( ∼ 450 s ) and the magnitude of the wall temperature increase result...

...Akhilesh P. Rallabandi; Huitao Yang; Je-Chin Han Systematic experiments are conducted to measure heat transfer enhancement and pressure loss characteristics on a square channel (simulating a gas turbine blade cooling passage) with two opposite surfaces roughened by 45 deg parallel ribs. Copper...

...Zhihong Gao; Je-Chin Han The effect of film-hole geometry and angle on turbine blade leading edge film cooling has been experimentally studied using the pressure sensitive paint technique. The leading edge is modeled by a blunt body with a semicylinder and an after-body. Two film cooling designs...

..., the heat/mass transfer analogy factor is applied and shows a good agreement between heat transfer and mass transfer results on the endwall with the fillets from the leading edge to the trailing edge. 29 06 2007 08 05 2008 14 10 2008 blades boundary layers gas turbines heat...

...Xianchang Li; Ting Wang Air-film cooling has been widely employed to cool gas turbine hot components, such as combustor liners, combustor transition pieces, turbine vanes, and blades. Studies with flat surfaces show that significant enhancement of air-film cooling can be achieved by injecting water...

...Xianchang Li; Ting Wang Effective cooling of gas turbine combustor liners, combustor transition pieces, turbine vanes (nozzles), and blades (buckets) is a critical task to protect these components from the flue gas at extremely high temperature. Air film cooling has been successfully used to cool...

... considerably extended the previous experiences that offer practical applications to the trailing edge cooling of a gas turbine rotor blade. A selection of experimental data illustrates the individual and interactive influences of Re, Ro, and buoyancy number (Bu) on local heat transfer with and without bleeds...

... blade. This paper experimentally investigates the individual and combined effects of periodic unsteady wake flows and freestream turbulence intensity (Tu) on heat transfer and aerodynamic behavior of the separation zone. Heat transfer experiments were carried out at Reynolds numbers of 110,000, 150,000...

...Jung-ho Choi; Shantanu Mhetras; Je-Chin Han; Sai C. Lau; Ron Rudolph Experiments to study heat transfer and film cooling on the cutback trailing edge of a turbine blade with slot ejection were performed. Heat transfer from two rows of perforated blockage inserts for lateral impingement...

... , T. , 1979 , “ Observations on the Influence of Rotation On Heat Transfer in the Cooling Channels of Gas Turbine Rotor Blades ,” Proc. Inst. Mech. Eng. 0020-3483 , 193 , pp...

... blades cooling jets mass transfer turbulence impingement∕effusion cooling fin crossflow heat∕mass transfer The demand for improvements in the efficiency and power output of gas turbines has led to a continuous increase in the turbine inlet temperature, which...

...Charles W. Booten; John K. Eaton The inverse discrete Green’s function (IDGF) is a heat transfer coefficient that is valid for arbitrarily complex thermal boundary conditions. It was measured using a rapid experimentation technique in a generic serpentine turbine-blade cooling passage with rib...