Symposium Papers, Volumes 1-2; Volume 12National Aeronautical Laboratory, 1995 - Aircraft gas-turbines |
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Page 222
... measurements . The clearances between the pads and the rotor disc were measured using non - contacting eddy - current displacement transducers , ( Kaman Instrumentation Corporation KDM - 8200 ) . The displacement readings were returned ...
... measurements . The clearances between the pads and the rotor disc were measured using non - contacting eddy - current displacement transducers , ( Kaman Instrumentation Corporation KDM - 8200 ) . The displacement readings were returned ...
Page 440
... measured in the nozzle . Both the pressures inside this region and in the lip region between the nozzle and combustor are measured with every tunnel shot and have been found to contribute at most 5 % of the thrust on the nozzle during ...
... measured in the nozzle . Both the pressures inside this region and in the lip region between the nozzle and combustor are measured with every tunnel shot and have been found to contribute at most 5 % of the thrust on the nozzle during ...
Page 559
... measured from schlieren photographs are known to be somewhat different from thicknesses determined from in- stream measurements . In comparison to shear layer thicknesses calculated from measured velocity profiles , visual thicknesses ...
... measured from schlieren photographs are known to be somewhat different from thicknesses determined from in- stream measurements . In comparison to shear layer thicknesses calculated from measured velocity profiles , visual thicknesses ...
Contents
Computer Environment for Aircraft Engines of Arbitrary Schemes | 9 |
Years of Gas Turbine Engineering | 29 |
Condition Based Monitoring | 39 |
Copyright | |
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aerodynamic AIAA Air Breathing aircraft analysis angle ASME ATREX axial axial compressor blade booster borescope boundary layer calculation cascade centrifugal compressor circumferential combustor component computation configuration coordinates crack cycle distribution effect engine equation equivalence ratio exit experimental Figure flight test flow coefficient flow field flow rate fluid fuel fuel injection gas turbine geometry grid heat transfer impeller increase injection inlet ISABE iterative loading Mach number mass flow measured method mixing momentum monitoring nozzle operation parameters performance precooler predicted pressure ratio problem propellant propulsion system radial ramjet region rocket rotation rotor S₂ surface scramjet shear layer shock shown simulation solution specific impulse speed squeeze film stage STAR-CD static pressure stator stream function streamsurfaces subsonic suction surface supersonic surface of revolution temperature three-dimensional flow thrust total pressure transonic turbomachinery turbulent vehicle velocity viscous wall әх