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High-Fidelity Three-Dimensional Simulation of the GE90A full-engine simulation of the three-dimensional flow in the GE90 94B high-bypass ratio turbofan engine has been achieved. It would take less than 11 hr of wall clock time if starting from scratch through the exploitation of parallel processing. The simulation of the compressor components, the cooled high-pressure turbine, and the low-pressure turbine was performed using the APNASA turbomachinery flow code. The combustor flow and chemistry were simulated using the National Combustor Code (NCC). The engine simulation matches the engine thermodynamic cycle for a sea-level takeoff condition. The simulation is started at the inlet of the fan and progresses downstream. Comparisons with the cycle point are presented. A detailed look at the blockage in the turbomachinery is presented as one measure to assess and view the solution and the multistage interaction effects.
Document ID
20040045342
Acquisition Source
Glenn Research Center
Document Type
Conference Paper
Authors
Turner, Mark G. (Cincinnati Univ. OH, United States)
Norris, Andrew (Ohio Aerospace Inst. Brook Park, OH, United States)
Veres, Josphe P. (NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
September 7, 2013
Publication Date
March 1, 2004
Subject Category
Aerodynamics
Report/Patent Number
NASA/TM-2004-212981
E-14456
NAS 1.15:212981
AIAA Paper 2003-3996
Meeting Information
Meeting: 33rd Fluid Dynamics Conference and Exhibit
Location: Orlando, FL
Country: United States
Start Date: June 23, 2003
End Date: June 26, 2003
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 22-708-87-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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