... one surface of a contraction passage. This passage 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...

...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...

... and leads to significant changes in the mean temperature field. 29 09 2009 30 07 2010 02 11 2010 02 11 2010 blades flow instability flow simulation gas turbines heat transfer Knudsen flow laminar flow microchannel flow numerical analysis slip flow microchannel...

... 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...

... that the application of pin fins on the tip could substantially increase the heat transfer intensity associated with low additional pressure loss. Therefore, from Figs. 15 16 , the pin-finned tip two-pass channels (especially for Case 7) provide good performance for gas turbine blade tip cooling. Performance...

... flux with such an initial condition appears to be the superposition of the wall heat flux at the end of the spinning up before the test and the flux due to the blow-down itself. Thin-film gauges are used in short-duration facilities for gas turbine aerothermal research since the 1970s...

...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...

.... aerodynamics blades cooling flow measurement gas turbines turbulence wind tunnels leading edge film cooling pressure sensitive paint (PSP) shaped hole compound angle Thermal efficiency and power output of gas turbine engines increase with increasing rotor inlet temperatures...

...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...

... = 3.57 × 10 5 and Tu = 8.5 % , Han and Goldstein ( 10 ) Sherwood number contour plot with Re ex = 4.97 × 10 5 and Tu = 8.5 % , Han and Goldstein ( 10 ) blades boundary layers gas turbines heat transfer heat/mass transfer analogy...

...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...

... the discrete film cooling holes, the increased turbulence decreases the film cooling effectiveness. Finally, combining upstream slot flow with downstream discrete film holes should be cautiously done to ensure coolant is not wasted by overcooling regions on the platform. cooling film flow gas turbines...