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Keywords: combustion
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Journal Articles
Article Type: Research Papers
J. Turbomach. July 2022, 144(7): 071015.
Paper No: TURBO-21-1168
Published Online: May 27, 2022
.... 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...
Journal Articles
Article Type: Research Papers
J. Turbomach. October 2011, 133(4): 041002.
Published Online: April 19, 2011
... 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...
Journal Articles
Article Type: Research Papers
J. Turbomach. January 2011, 133(1): 011028.
Published Online: September 28, 2010
... 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...
Journal Articles
Article Type: Research Papers
J. Turbomach. January 2011, 133(1): 011024.
Published Online: September 24, 2010
...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...
Journal Articles
Article Type: Research Papers
J. Turbomach. July 2010, 132(3): 031011.
Published Online: March 25, 2010
.... The possibility also exists for particles to be ingested at cruising altitude, which was further investigated in studies performed by Kim et al. ( 2 ) on aircraft flying through volcanic dust clouds. aircraft combustion cooling film condensation gas turbines 03 03 2009 04 03 2009 25...
Journal Articles
Article Type: Research Papers
J. Turbomach. April 2010, 132(2): 021020.
Published Online: January 21, 2010
.... 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 An electric oven, set at 150 ° C , was used to dry...
Journal Articles
Article Type: Technical Briefs
J. Turbomach. October 2009, 131(4): 044501.
Published Online: June 30, 2009
... a decrease in enhancement of approximately 45% in the near-hole region at S R = 5 , which decreases to approximately 25% in the same region for S R = 2.5 . blades boundary layers channel flow combustion computational fluid dynamics cooling gas turbines heat conduction jet...
Journal Articles
Article Type: Research Papers
J. Turbomach. October 2009, 131(4): 041002.
Published Online: June 30, 2009
... 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...
Journal Articles
Article Type: Research Papers
J. Turbomach. July 2009, 131(3): 031009.
Published Online: April 9, 2009
... 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...
Journal Articles
Article Type: Research Papers
J. Turbomach. April 2009, 131(2): 021010.
Published Online: January 23, 2009
... 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...
Journal Articles
Article Type: Research Papers
J. Turbomach. April 2009, 131(2): 021008.
Published Online: January 23, 2009
... 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...
Journal Articles
Article Type: Research Papers
J. Turbomach. April 2009, 131(2): 021009.
Published Online: January 23, 2009
... 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...
Journal Articles
Article Type: Research Papers
J. Turbomach. October 2008, 130(4): 041019.
Published Online: August 4, 2008
...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...
Journal Articles
Article Type: Research Papers
J. Turbomach. January 2008, 130(1): 011012.
Published Online: January 25, 2008
... 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...
Journal Articles
Article Type: Technical Papers
J. Turbomach. April 2007, 129(2): 382–393.
Published Online: July 31, 2006
... 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...
Journal Articles
Article Type: Technical Papers
J. Turbomach. April 2005, 127(2): 372–379.
Published Online: May 5, 2005
...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...
Journal Articles
Article Type: Technical Papers
J. Turbomach. April 2005, 127(2): 251–262.
Published Online: May 5, 2005
...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...
Journal Articles
Article Type: Technical Papers
J. Turbomach. January 2007, 129(1): 32–43.
Published Online: February 1, 2005
... blades cooling gas turbines combustion jet engines flow visualisation flow simulation boundary layers Heat transfer rates in the first stage turbine have been studied for many years. Increases in turbine inlet temperature, to achieve higher thrust and efficiency, have been made possible...
Journal Articles
Article Type: Technical Papers
J. Turbomach. January 2004, 126(1): 122–129.
Published Online: March 26, 2004
...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...
Journal Articles
Article Type: Technical Papers
J. Turbomach. April 2006, 128(2): 321–331.
Published Online: March 1, 2004
..., 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 Impingement cooling is used in gas turbine blade internal cooling for platform and airfoil surfaces...