Role of tip-leakage vortices and passage shock in stall inception in a swept transonic compressor rotor

Proceedings of the ASME Turbo Expo 2004

Volumn 5 A, Issue , 2004, Pages 545-555

  Hah, Chunill ^a   Rabe, Douglas C ^b   Wadia, Aspi R ^c  

^a NASA GLENN RESEARCH CENTER   (United States)

^b AIR FORCE RESEARCH LABORATORY   (United States)

^c GET Aircraft Engines   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

AERODYNAMICS; BOUNDARY LAYERS; ROTORS; SHOCK WAVES; TURBOMACHINE BLADES; VORTEX FLOW;

FLOW FIELDS; MOMENTUM; SWIRL INTENSITY; TIP LEAKAGE;

COMPRESSORS;

EID: 10244259238     PISSN: None     EISSN: None     Source Type: Conference Proceeding    
DOI: 10.1115/gt2004-53867     Document Type: Conference Paper

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