NDLI: Analysis of an advanced technology subsonic turbofan incorporating revolutionary materials

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Analysis of an advanced technology subsonic turbofan incorporating revolutionary materials

Content Provider	NASA Technical Reports Server (NTRS)
Author	Knip Jr., Gerald
Copyright Year	1987
Description	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).
File Size	1191614
Page Count	25
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19870013247
Archival Resource Key	ark:/13960/t7zm07g75
Language	English
Publisher Date	1987-05-01
Access Restriction	Open
Subject Keyword	Aircraft Propulsion And Power Turbocompressors Engine Design Weight Reduction Pressure Ratio Fuel Consumption Metal Matrix Composites Turbofan Engines Aircraft Engines Ceramics Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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