.... The can combustor was equipped with an industrial engine swirler and gaseous fuel (methane), subjecting the liner walls to engine representative flow and combustion conditions. In this study, three different effusion cooling liners with spanwise spacings of r/d = 6, 8, and 10 and streamwise spacing of z/d...

... for relatively higher-pressure coolant flows. This leakage is intended to prevent ingestion of the hot combustion flow in the primary gas path. At the vane endwall, this leakage flow can interfere with the complex vortical flow present there and thus affect the heat transfer to that surface. To determine...

... recirculation zone near the combustor liner remains the same for all Reynolds numbers and hence the location of shear layer impingement and peak augmentation does not change. 06 07 2009 08 11 2009 28 09 2010 28 09 2010 combustion convection gas turbines swirling flow turbulence...

...Satoshi Hada; Karen A. Thole Turbines are designed to operate with high inlet temperatures to improve engine performance. To reduce NO x resulting from combustion, designs for combustors attempt to achieve flat pattern factors that results in high levels of heat transfer to the endwall of the first...

... volcanic dust clouds. aircraft combustion cooling film condensation gas turbines 03 03 2009 04 03 2009 25 03 2010 25 03 2010 2010 American Society of Mechanical Engineers ...

.... Film-cooling is often employed on the external surface by providing a coolant film along the exterior. aerospace engines combustion coolants cooling turbines 01 02 2009 04 02 2009 21 01 2010 21 01 2010 Stokes number is commonly used to define how well a given...

... negligible compared with the primary variables such as the suction ratio and extraction angle.o 07 12 2007 31 08 2008 30 06 2009 blades boundary layers channel flow combustion computational fluid dynamics cooling gas turbines heat conduction jet engines thin film devices...

... 08 2007 30 06 2009 blades combustion combustion equipment confined flow engines film condensation gas turbines nozzles temperature distribution film cooling hot streak superposition Modeling of “hot streaks” downstream of the combustor in the turbine section...

... Isentropic Light Piston Turbine Test Facility, is presented. 12 09 2007 23 07 2008 09 04 2009 aerodynamics blades combustion combustion equipment heat exchangers life testing mechanical testing reliability temperature distribution turbines Turbine inlet temperature...

... that are nonuniform in temperature is also discussed. 26 07 2007 05 12 2007 23 01 2009 aerospace components aerospace engines aerospace propulsion blades combustion combustion equipment convection gas turbines The performance and durability of the hot section within gas turbine...

... at the inlet of the vane can alter the redistribution of stagnation enthalpy through the airfoil passage significantly. Total pressure loss and exit flow angle variations are also examined for the different inlet profiles. 26 07 2007 03 01 2008 23 01 2009 blades combustion engines gas...

... 10 2006 03 12 2007 23 01 2009 aerodynamics aerospace engines blades chemically reactive flow combustion combustion equipment gas turbines heat transfer The desire to continuously improve the performance and working life of aircraft gas turbine engines has led...

...S. P. Lynch; K. A. Thole To enable turbine components to withstand high combustion temperatures, they are cooled by air routed from the compressor, which can leak through gaps between components. These gaps vary in size from thermal expansions that take place. The leakage flow between the interface...

... in the main premixed combustion (premixed fuel injection (PMI)) or, alternatively, in the secondary pilot fuel. PMI included symmetric and asymmetric fuel injection. The symmetric instability mode responded to symmetric excitation only when the two frequencies matched. The helical fuel injection affected...

... can produce significantly different flow and thermal field conditions entering the turbine. Engine designers should place emphasis on obtaining accurate knowledge of the flow distribution within the combustion chamber. Turbine inlet conditions with significantly different profile shapes can result...

...Valter Bellucci; Bruno Schuermans; Dariusz Nowak; Peter Flohr; Christian Oliver Paschereit In this work, the TA3 thermoacoustic network is presented and used to simulate acoustic pulsations occurring in a heavy-duty ALSTOM gas turbine. In our approach, the combustion system is represented...

...J. R. Christophel; E. Couch; K. A. Thole; F. J. Cunha The clearance gap between the tip of a turbine blade and the shroud has an inherent leakage flow from the pressure side to the suction side of the blade. This leakage flow of combustion gas and air mixtures leads to severe heat transfer rates...

... temperature: if the hot-streak migration process is not fully understood the designer must effectively design for the peak gas temperature, and budget for this in the overall engine performance calculation. blades cooling gas turbines combustion jet engines flow visualisation flow simulation...

...Sarah Stitzel; Karen A. Thole The current demands for high-performance gas turbine engines can be reached by raising combustion temperatures to increase power output. High combustion temperatures create a harsh environment that leads to the consideration of the durability of the combustor...

..., then at high coolant flow rates the increase in heat transfer was 21%, 47%, and 25% for X ∕ D of 4.66, 3.06, and 1.86, respectively. combustion cooling boundary layers gas turbines mass transfer The experimental techniques have been fully detailed previously ( 10 12 23 ) and shown to have...