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Analysis of an advanced technology subsonic turbofan incorporating revolutionary materials
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Author and Affiliation:
Knip, Gerald, Jr.(NASA Lewis Research Center, Cleveland, OH, United States)
Abstract: Successful 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).
Publication Date: May 01, 1987
Document ID:
19870013247
(Acquired Nov 04, 1995)
Accession Number: 87N22680
Subject Category: AIRCRAFT PROPULSION AND POWER
Report/Patent Number: NASA-TM-89868, E-3542, NAS 1.15:89868
Document Type: Technical Report
Publisher Information: United States
Contract/Grant/Task Num: RTOP 505-69-41
Financial Sponsor: NASA; United States
Organization Source: NASA Lewis Research Center; Cleveland, OH, United States
Description: 25p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: No Copyright
NASA Terms: AIRCRAFT ENGINES; CERAMICS; METAL MATRIX COMPOSITES; TURBOFAN ENGINES; ENGINE DESIGN; FUEL CONSUMPTION; PRESSURE RATIO; TURBOCOMPRESSORS; WEIGHT REDUCTION
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