Heat transfer coefficient on the squealer tip and near squealer tip regions of a gas turbine blade

ASME International Mechanical Engineering Congress and Exposition, Proceedings

Volumn 4, Issue , 2002, Pages 245-254

  Kwak, Jae Su ^a   Han, Je Chin ^a  

^a Department of Electrical and Computer Engineering   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

GAS TURBINE LOCOMOTIVES; GAS TURBINES; HEAT TRANSFER COEFFICIENTS; HELICOPTER ROTORS; LIQUID CRYSTALS; MACH NUMBER; MECHANICAL ENGINEERING; REYNOLDS NUMBER;

AIRCRAFT GAS TURBINE ENGINES; BLADE SPAN; BLOW-DOWN FACILITY; CHORD LENGTHS; DIMENSIONAL MODEL; EXIT VELOCITY; GAP CLEARANCE; GAS TURBINE BLADES; GAS TURBINE ROTORS; HEAT TRANSFER COEFFICIENT DISTRIBUTION; HEAT TRANSFER MEASUREMENTS; LINEAR CASCADE; OVERALL HEAT TRANSFER COEFFICIENT; OVERALL PRESSURE RATIOS; PRESSURE SIDE; ROTOR BLADES; SQUEALER TIP; SUCTION SIDE; TURBULENCE INTENSITY LEVEL; TURNING ANGLES;

TURBOMACHINE BLADES;

EID: 78249285610     PISSN: None     EISSN: None     Source Type: Conference Proceeding    
DOI: 10.1115/IMECE2002-32109     Document Type: Conference Paper

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