... is designed to impose experimental conditions which simulate those which exist within combustor liner components of gas turbine engines, with streamwise varying distributions of static pressure, freestream velocity, freestream flow mass flux, coolant flow mass flux, and local film cooling blowing ratio...

...Minking K. Chyu The performance goal of modern gas turbine engines, both land-base and air-breathing engines, can be achieved by increasing the turbine inlet temperature (TIT). The level of TIT in the near future can reach as high as 1700 °C for utility turbines and over 1900 °C for advanced...

...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...

...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...

... factors increased with rotation number due to the increased Sherwood number ratios and decreased friction factor ratios. 30 08 2010 12 08 2011 27 10 2011 27 10 2011 channel flow gas turbines heat transfer mass transfer rotational flow swirling flow turbulence gas...

...Nawaf Y. Alkhamis; Akhilesh P. Rallabandi; Je-Chin Han Heat transfer coefficients and friction factors are measured in a 45 deg V-shaped rib roughened square duct at high Reynolds numbers, pertaining to internal passages of land-based gas turbine engines. Reynolds numbers in this study range from...

..., depending on the wall-gas temperature difference. Heat transfer is more significantly altered. The Nusselt number between slip and no-slip cases at the outlet of the microchannel is increased by about 10%. Bunker , R. S. , 2007 , “ Gas Turbine Heat Transfer: Ten Remaining Hot Gas Path Challenges...

... in the laboratory under low pressure and temperature conditions. However, whether or not mist/steam cooling is applicable under actual gas turbine operating conditions is still subject to further verification. Recognizing the difficulties of conducting experiments in an actual high-pressure, high-temperature...

...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...

... by Bunker ( 31 ) Performance comparison of various tips under Case 2 25 02 2009 29 05 2009 30 12 2009 30 12 2009 channel flow convection cooling engines gas turbines tip wall pin fins enhancement computation gas turbine cooling...

... gauges heat conduction rotors temperature distribution thin film devices ventilation gas turbines thin-film gauges convective heat flux Thin-film gauges are used in short-duration facilities for gas turbine aerothermal research since the 1970s. These resistive temperature detectors...

...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...

... effectiveness on the leading edge region than the three-row design at the same average blowing ratio or same amount coolant flow. 04 06 2007 04 12 2008 30 03 2009 aerodynamics blades cooling flow measurement gas turbines turbulence wind tunnels leading edge film cooling...

...J. Bons The effect of lateral conduction on convective heat transfer measurements using a transient infrared technique over a rough surface is evaluated. The rough surface is a scaled model of gas turbine surface deposits. Comparisons are made between a full 3D finite volume analysis and a simpler...

..., 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...

...Yao-Hsien Liu; Michael Huh; Je-Chin Han; Sanjay Chopra This paper experimentally investigated the rotational effects on heat transfer in a two-pass rectangular channel ( AR = 1 : 4 ) , which is applicable to the channel near the leading edge of the gas turbine blade. The test channel has radially...

...Manosh C. Paul We have carried out a three-dimensional numerical study to investigate the radiative heat transfer in a model gas turbine combustor. The combustion chamber is a representative of the Rolls-Royce Tay engine combustor. The discrete ordinate method ( S n ) in general body-fitted...

... 05 2008 cooling film flow gas turbines turbulence vortices forced convection film cooling gas turbine heat transfer As economies across the world continue to grow, the demand for power also continues to increase. Commercial, industrial, and residential customers have come...