NTRS - NASA Technical Reports Server

Back to Results
Analysis of an advanced technology subsonic turbofan incorporating revolutionary materialsSuccessful implementation of revolutionary composite materials in an advanced turbofan offers the possibility of further improvements in engine performance and thrust-to-weight ratio relative to current metallic materials. The present analysis determines the approximate engine cycle and configuration for an early 21st century subsonic turbofan incorporating all composite materials. The advanced engine is evaluated relative to a current technology baseline engine in terms of its potential fuel savings for an intercontinental quadjet having a design range of 5500 nmi and a payload of 500 passengers. The resultant near optimum, uncooled, two-spool, advanced engine has an overall pressure ratio of 87, a bypass ratio of 18, a geared fan, and a turbine rotor inlet temperature of 3085 R. Improvements result in a 33-percent fuel saving for the specified misssion. Various advanced composite materials are used throughout the engine. For example, advanced polymer composite materials are used for the fan and the low pressure compressor (LPC).
Document ID
Document Type
Technical Memorandum (TM)
Knip, Gerald, Jr.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 5, 2013
Publication Date
May 1, 1987
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NAS 1.15:89868
Accession Number
Funding Number(s)
PROJECT: RTOP 505-69-41
Distribution Limits
Work of the US Gov. Public Use Permitted.
No Preview Available