The influence of compressor blade row interaction modeling on performance estimates from time-accurate, multistage, navier-stokes simulations

Journal of Turbomachinery

Volumn 130, Issue 1, 2008, Pages

  Van Zante, Dale ^a   Chen, Jenping ^b   Hathaway, Michael ^c   Chriss, Randall ^a  

^a NASA GLENN RESEARCH CENTER   (United States)

^b OHIO STATE UNIVERSITY   (United States)

^c Vehicle Technology Directorate   (United States)

Author keywords

Blade row interaction; Multi stage compressor; Numerical modeling

Indexed keywords

BOUNDARY VALUE PROBLEMS; COMPRESSORS; ESTIMATION; FLOW INTERACTIONS; NAVIER STOKES EQUATIONS; PHASE BOUNDARIES; PROCESS DESIGN; PROCESS ENGINEERING; PROJECT MANAGEMENT; THEOREM PROVING; TRANSONIC FLOW; TURBOMACHINE BLADES;

ADIABATIC EFFICIENCY; AXIAL COMPRESSORS; BLADE PASSAGES; BLADE ROW INTERACTIONS; BLADE ROWS; CIRCUM FERENTIAL DIRECTION; COMPLETION TIMES; COMPRESSOR BLADES; CONVERGENCE (MATHEMATICS); DESIGN PROCESSES; FRAME OF REFERENCE; HIGH SPEEDS; MESH DENSITY; MESH TOPOLOGIES; NAVIER - STOKES; NAVIER-STOKES SIMULATIONS; ORDER-OF MAGNITUDES; OVERALL PERFORMANCE; PERIODIC BOUNDARY CONDITIONS (PBC); PERIODIC SIMULATION; PHASE LAGS; REFERENCE FRAMES; RESEARCH PROJECTS; SIMULATION SETUPS; SPATIAL VARIATIONS; STRONG INTERACTIONS; TIME-ACCURATE;

BOUNDARY CONDITIONS;

EID: 47649128063     PISSN: 0889504X     EISSN: None     Source Type: Journal    
DOI: 10.1115/1.2775486     Document Type: Article

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