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NASA NTRS · Contractor Report (CR)
Ultra-High Bypass Engine Aeroacoustic Study
Attribution
This is the abstract and citation. Full text lives at NASA NTRS — we link out rather than host. All credit to the authors and Glenn Research Center.
Abstract
Verbatim from NASA NTRS. Not paraphrased, not summarized.
A system study was carried out to identify potential advanced aircraft engine concepts and cycles which could be capable of achieving a 5 to 10 EPNdB reduction in community noise level relative to current FAR36 Stage 3 limits for a typical large-capacity commercial transport aircraft. The study was directed toward large twin-engine aircraft applications in the 400,000 to 500,000 pound take-off gross weight class. Four single rotation fan engine designs with fan pressure ratios from 1.3 to 1.75, and two counter-rotating fan engine configurations were studied. Several engine configurations were identified which, with further technology development, could achieve the objective of 5 to 10 EPNdB noise reduction. Optimum design fan pressure ratio is concluded to be in the range of 1.4 to 1.55 for best noise reduction with acceptable weight and Direct Operating Cost (DOC) penalties.
Authors
- Gliebe, Philip R. General Electric Aircraft Engines
- Janardan, Bangalore A. General Electric Aircraft Engines
Citation: Gliebe, Philip R., Janardan, Bangalore A. (2019). Ultra-High Bypass Engine Aeroacoustic Study. Glenn Research Center. NASA NTRS ID 20040000741. https://ntrs.nasa.gov/citations/20040000741 ↗