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Thermodynamics of Gas Flow
IMPELLER ANALYSES APPROXIMATE SOLUTIONS
10 other sections not shown
acceleration afterburner air flow airfoil altitude angle angle of attack annulus approximately axial compressor axial velocity blade elements blade row blade surfaces blade-element boundary layer burner calculation cascade centrifugal compressors chamber characteristics choke flow combustion component compressible flow compression compressor inlet compressor stall constant corrected curve deceleration decrease defined density determined distribution effect enthalpy equal equation flow coefficient flow rate flow surface fluid fuel flow Fuel Systems function gas turbine given grid heat addition impeller tip increase isentropic losses Mach number machine maximum meridional plane method NACA NACA TN nozzle obtained operating parameter performance potential flow pressure drop pressure ratio Pt,l radial Reynolds number index rotating rotor shown in figure solution stage stall static pressure streamlines surface of revolution thrust tion tip speed total pressure total temperature turbojet upstream valve vaneless diffuser variables variation weight flow zero