Works matching IS 00778923 AND DT 2001 AND VI 934 AND IP 1
Results: 54
NUMERICAL INVESTIGATION OF HEAT TRANSFER ON FILM-COOLED TURBINE BLADES.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 377, doi. 10.1111/j.1749-6632.2001.tb05873.x
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The Detailed Structure and Behavior of Discrete Cooling Jets in a Turbine.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 95, doi. 10.1111/j.1749-6632.2001.tb05845.x
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Transition to Turbulence Under Low-Pressure Turbine Conditions.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 37, doi. 10.1111/j.1749-6632.2001.tb05841.x
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Synopsis.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 1, doi. 10.1111/j.1749-6632.2001.tb05838.x
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Combustor Liner Cooling Technology in Scope of Reduced Pollutant Formation and Rising Thermal Efficiencies.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 135, doi. 10.1111/j.1749-6632.2001.tb05848.x
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Effect of Reynolds Number, Turbulence Level and Periodic Wake Flow on Heat Transfer on Low Pressure Turbine Blades.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 249, doi. 10.1111/j.1749-6632.2001.tb05857.x
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Heat Transfer and Flow Characteristics on a Gas Turbine Shroud.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 289, doi. 10.1111/j.1749-6632.2001.tb05862.x
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Heat Transfer Technology for Internal Passages of Air-Cooled Blades for Heavy-Duty Gas Turbines.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 179, doi. 10.1111/j.1749-6632.2001.tb05851.x
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Verifying Heat Transfer Analysis of High Pressure Cooled Turbine Blades and Disk.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 505, doi. 10.1111/j.1749-6632.2001.tb05889.x
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Preface.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. xi, doi. 10.1111/j.1749-6632.2001.tb05837.x
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Mass/Heat Transfer in Dimpled Two-Pass Coolant Passages with Rotation.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 424, doi. 10.1111/j.1749-6632.2001.tb05879.x
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EXPERIMENTAL DETERMINATION OF AVERAGE TURBULENT HEAT TRANSFER AND FRICTION FACTOR IN STATOR INTERNAL RIB- ROUGHENED COOLING CHANNELS.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 464, doi. 10.1111/j.1749-6632.2001.tb05884.x
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Film cooling from rows of holes-effect of cooling hole shape and row arrangement on adiabatic effectiveness.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 321, doi. 10.1111/j.1749-6632.2001.tb05866.x
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The Variation of Heat Transfer Coefficient, Adiabatic Effectiveness and Aerodynamic Loss with Film Cooling Hole Shape.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 361, doi. 10.1111/j.1749-6632.2001.tb05871.x
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Numerical Investigation of Combined Impingement and Convection Heat Transfer.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 417, doi. 10.1111/j.1749-6632.2001.tb05878.x
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Numerical Modelling of Flow and Heat Transfer in the Rotating Disc Cavities of a Turboprop Engine.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 497, doi. 10.1111/j.1749-6632.2001.tb05888.x
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Selection of a Turbine Cooling System Applying Multi-Disciplinary Design Considerations.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 222, doi. 10.1111/j.1749-6632.2001.tb05854.x
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Analysis of Particle Laden Flow and Heat Transfer in Cascade and Rocket Nozzle.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 233, doi. 10.1111/j.1749-6632.2001.tb05855.x
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A Conjugate Heat Transfer Procedure for Gas Turbine Blades.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 273, doi. 10.1111/j.1749-6632.2001.tb05860.x
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Experimental Investigation of Film Cooling Flow Induced by Shaped Holes on a Turbine Blade.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 313, doi. 10.1111/j.1749-6632.2001.tb05865.x
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Numerical Investigation of Film Cooling Flow Induced by Cylindrical and Shaped Holes.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 369, doi. 10.1111/j.1749-6632.2001.tb05872.x
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Effects of Entrance Crossflow Directions to Film Cooling Holes.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 401, doi. 10.1111/j.1749-6632.2001.tb05876.x
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SECONDARY FLOW EFFECT TO HEAT TRANSFER OF A DUCT WITH DISCRETE RIB TURBULATORS.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 481, doi. 10.1111/j.1749-6632.2001.tb05886.x
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Numerical Simulation of Local Heat Transfer in Rotating Two-Pass Square Channels.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 456, doi. 10.1111/j.1749-6632.2001.tb05883.x
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Effects of Bulk Flow Pulsations on Film Cooling with Shaped Holes.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 329, doi. 10.1111/j.1749-6632.2001.tb05867.x
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FILM COOLING PERFORMANCE ON CURVED WALLS WITH COMPOUND ANGLE HOLE CONFIGURATION.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 353, doi. 10.1111/j.1749-6632.2001.tb05870.x
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Finite Element Analysis of Flowfield in the Single Hole Film Cooling Technique.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 393, doi. 10.1111/j.1749-6632.2001.tb05875.x
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Mach Number Effect On Jet Impingement Heat Transfer.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 409, doi. 10.1111/j.1749-6632.2001.tb05877.x
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Development of Non-destructive Inspection Method for the Performance of Thermal Barrier Coating.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 489, doi. 10.1111/j.1749-6632.2001.tb05887.x
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A Review of Turbine Blade Tip Heat Transfer.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 64, doi. 10.1111/j.1749-6632.2001.tb05843.x
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STUDIES ON FREE STREAM TURBULENCE AS RELATED TO GAS TURBINE HEAT TRANSFER.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 265, doi. 10.1111/j.1749-6632.2001.tb05859.x
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Recent Developments in Turbine Blade Internal Cooling.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 162, doi. 10.1111/j.1749-6632.2001.tb05850.x
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Film Cooling: What did we learn from our measurements?
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 126, doi. 10.1111/j.1749-6632.2001.tb05847.x
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Analyses of Heat Transfer in Stationary and Rotating Ribbed Blade Cooling Passages using Computational Fluid Dynamics.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 440, doi. 10.1111/j.1749-6632.2001.tb05881.x
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Contribution of Heat Transfer to Turbine Blades and Vanes for High Temperature Industrial Gas Turbines Part 2: Heat Transfer on Serpentine Flow Passage.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 473, doi. 10.1111/j.1749-6632.2001.tb05885.x
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Prediction of pressure loss and heat transfer in internal cooling passages.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 448, doi. 10.1111/j.1749-6632.2001.tb05882.x
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Contribution of Heat Transfer to Turbine Blades and Vanes for High Temperature Industrial Gas Turbines Part 1: Film Cooling.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 305, doi. 10.1111/j.1749-6632.2001.tb05864.x
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Characteristics of Various Film Cooling Jets Injected in a Conduit.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 345, doi. 10.1111/j.1749-6632.2001.tb05869.x
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Comparison between two models of cooling surfaces using blowing.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 385, doi. 10.1111/j.1749-6632.2001.tb05874.x
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Turbulence Modeling in Simulation of Gas-Turbine Flow and Heat Transfer.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 52, doi. 10.1111/j.1749-6632.2001.tb05842.x
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Flow and Heat Transfer Predictions for Film Cooling.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 110, doi. 10.1111/j.1749-6632.2001.tb05846.x
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Some Current Research in Rotating-Disc Systems.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 206, doi. 10.1111/j.1749-6632.2001.tb05853.x
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Heat Transfer near Turbine Nozzle Endwall.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 27, doi. 10.1111/j.1749-6632.2001.tb05840.x
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SURFACE TEMPERATURE MAPPING OF GAS TURBINE BLADING BY MEANS OF HIGH RESOLUTION PYROMETRY.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 257, doi. 10.1111/j.1749-6632.2001.tb05858.x
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A Novel Digital Image Processing System for the Transient Liquid Crystal Technique applied for Heat Transfer and Film Cooling Measurements.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 297, doi. 10.1111/j.1749-6632.2001.tb05863.x
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Cooling Systems for Ultra-High Temperature Turbines.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 194, doi. 10.1111/j.1749-6632.2001.tb05852.x
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Jet-Impingement Heat Transfer in Gas Turbine Systems.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 147, doi. 10.1111/j.1749-6632.2001.tb05849.x
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COMPUTATION OF FLOW AND HEAT TRANSFER IN ROTATING CAVITIES WITH PERIPHERAL FLOW OF COOLING AIR.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 513, doi. 10.1111/j.1749-6632.2001.tb05890.x
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Detailed Heat/Mass Transfer Distributions in a Rotating Two Pass Coolant Channel With Engine-Near Cross Section and Smooth Walls.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 432, doi. 10.1111/j.1749-6632.2001.tb05880.x
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Unsteady Flow Modelling in Turbine Stage.
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- Annals of the New York Academy of Sciences, 2001, v. 934, n. 1, p. 80, doi. 10.1111/j.1749-6632.2001.tb05844.x
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