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Full 3D Analysis of the GE90 Turbofan Primary FlowpathThe multistage simulations of the GE90 turbofan primary flowpath components have been performed. The multistage CFD code, APNASA, has been used to analyze the fan, fan OGV and booster, the 10-stage high-pressure compressor and the entire turbine system of the GE90 turbofan engine. The code has two levels of parallel, and for the 18 blade row full turbine simulation has 87.3 percent parallel efficiency with 121 processors on an SGI ORIGIN. Grid generation is accomplished with the multistage Average Passage Grid Generator, APG. Results for each component are shown which compare favorably with test data.
Document ID
20000034013
Acquisition Source
Glenn Research Center
Document Type
Contractor Report (CR)
Authors
Turner, Mark G. (General Electric Co. Cincinnati, OH United States)
Date Acquired
September 7, 2013
Publication Date
March 1, 2000
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
E-12205
NASA/CR-2000-209951
NAS 1.26:209951
Funding Number(s)
CONTRACT_GRANT: NAS3-26617
PROJECT: RTOP 509-10-11
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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