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Compressor Work or Mechanical Energy Input to Gas
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air flow alloys altitude approximately axial compressor blade element blade row blade surfaces blade-element boundary layer calculated cascade centrifugal compressors characteristics choke flow combustion combustor component compressible flow compression constant creep curve decreases defined density determined diffuser dimensional analysis dimensionless distribution energy engine equal equation flow coefficient flow factor flow rate flow surface fluid Free Piston friction loss fuel Gas Turbine head coefficient heat impeller tip increase inlet input loss coefficient Mach number meridional plane NACA NACA TN nozzle obtained operating optimum parameter pressure loss pressure ratio radius reference Reynolds number index rotating rotor rupture shown in figure solution specific stage stall static pressure streamlines stress concentration surface of revolution tangential component tangential velocity tion tip speed total pressure total temperature turbojet upstream values vaneless vanes variables variation weight flow wheel disc friction zero