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NASA/CR—2003-212525
Ultra-High Bypass Engine Aeroacoustic Study
Philip R. Gliebe and Bangalore A. Janardan GE Aircraft Engines, Cincinnati, Ohio
October 2003
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NASA/CR—2003-212525
Ultra-High Bypass Engine Aeroacoustic Study
Philip R. Gliebe and Bangalore A. Janardan GE Aircraft Engines, Cincinnati, Ohio Prepared under Contract NAS3–25269, Task Order 4 National Aeronautics and Space Administration Glenn Research Center
October 2003
Acknowledgments The following people contributed substantially to the study reported herein. Christopher J. Smith provided integration of the cycle analysis, flowpath design, mission analysis, and carried out the DOC analyses.
Paul Feig and Valerie McKay provided the mission analysis. Larry Dunbar and Michael Salay carried out the engine flowpath designs. Rick Donaldson, Mark Wagner, and Charlotte Salay provided the engine cycle analyses.
Dr. Bangalore Janardan and George Kontos provided the engine system noise predictions.
Trade names or manufacturers’ names are used in this report for identification only. This usage does not constitute an official endorsement, either expressed or implied, by the National Aeronautics and Space Administration.
Contents were reproduced from the best available copy as provided by the authors.
Note that at the time of research, the NASA Lewis Research Center was undergoing a name change to the NASA John H. Glenn Research Center at Lewis Field.
Both names may appear in this report.
Available from NASA Center for Aerospace Information National Technical Information Service 7121 Standard Drive 5285 Port Royal Road Hanover, MD 21076 Springfield, VA 22100 Available electronically at http://gltrs.grc.nasa.gov NASA/CR—2003-212525 iii NASA/CR—2003-212525 1 NASA/CR—2003-212525 2 NASA/CR—2003-212525 3 NASA/CR—2003-212525 4 NASA/CR—2003-212525 5 NASA/CR—2003-212525 6 NASA/CR—2003-212525 7 NASA/CR—2003-212525 8 NASA/CR—2003-212525 9 NASA/CR—2003-212525 10 NASA/CR—2003-212525 11 NASA/CR—2003-212525 12 NASA/CR—2003-212525 13 NASA/CR—2003-212525 14 NASA/CR—2003-212525 15 NASA/CR—2003-212525 16 NASA/CR—2003-212525 17 NASA/CR—2003-212525 18 NASA/CR—2003-212525 19 NASA/CR—2003-212525 20 NASA/CR—2003-212525 21 NASA/CR—2003-212525 22 NASA/CR—2003-212525 23 NASA/CR—2003-212525 24 NASA/CR—2003-212525 25 NASA/CR—2003-212525 26 NASA/CR—2003-212525 27 NASA/CR—2003-212525 28 NASA/CR—2003-212525 29 NASA/CR—2003-212525 30 NASA/CR—2003-212525 31 NASA/CR—2003-212525 32 NASA/CR—2003-212525 33 NASA/CR—2003-212525 34 NASA/CR—2003-212525 35 NASA/CR—2003-212525 36 NASA/CR—2003-212525 37 NASA/CR—2003-212525 38 NASA/CR—2003-212525 39 NASA/CR—2003-212525 40 NASA/CR—2003-212525 41 NASA/CR—2003-212525 42 NASA/CR—2003-212525 43 NASA/CR—2003-212525 44 NASA/CR—2003-212525 45 NASA/CR—2003-212525 46 NASA/CR—2003-212525 47 NASA/CR—2003-212525 48 NASA/CR—2003-212525 49 NASA/CR—2003-212525 50 NASA/CR—2003-212525 51 NASA/CR—2003-212525 52 NASA/CR—2003-212525 53 NASA/CR—2003-212525 54 NASA/CR—2003-212525 55 NASA/CR—2003-212525 56 NASA/CR—2003-212525 57 NASA/CR—2003-212525 58 NASA/CR—2003-212525 59 NASA/CR—2003-212525 60 NASA/CR—2003-212525 61 NASA/CR—2003-212525 62 NASA/CR—2003-212525 63 NASA/CR—2003-212525 64 NASA/CR—2003-212525 65 NASA/CR—2003-212525 66 NASA/CR—2003-212525 67 NASA/CR—2003-212525 68 NASA/CR—2003-212525 69 NASA/CR—2003-212525 70 NASA/CR—2003-212525 71 NASA/CR—2003-212525 72 NASA/CR—2003-212525 73 NASA/CR—2003-212525 74 NASA/CR—2003-212525 75 NASA/CR—2003-212525 76 NASA/CR—2003-212525 77 NASA/CR—2003-212525 78 NASA/CR—2003-212525 79 NASA/CR—2003-212525 80 NASA/CR—2003-212525 81 NASA/CR—2003-212525 82 NASA/CR—2003-212525 83 NASA/CR—2003-212525 84 NASA/CR—2003-212525 85 NASA/CR—2003-212525 86 NASA/CR—2003-212525 87 NASA/CR—2003-212525 88 NASA/CR—2003-212525 89 NASA/CR—2003-212525 90 NASA/CR—2003-212525 91 NASA/CR—2003-212525 92 NASA/CR—2003-212525 93 NASA/CR—2003-212525 94 NASA/CR—2003-212525 95 NASA/CR—2003-212525 96 NASA/CR—2003-212525 97 NASA/CR—2003-212525 98 NASA/CR—2003-212525 99 NASA/CR—2003-212525 100 NASA/CR—2003-212525 101 NASA/CR—2003-212525 102 NASA/CR—2003-212525 103 Form Approved REPORT DOCUMENTATION PAGE OMB No. 0704-0188 Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden, to Washington Headquarters Services, Directorate for Information Operations and Reports, 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302, and to the Office of Management and Budget, Paperwork Reduction Project (0704-0188), Washington, DC 20503.
2. REPORT DATE 3. REPORT TYPE AND DATES COVERED 1. AGENCY USE ONLY ( Leave blank) Final Contractor Report October 2003 4. TITLE AND SUBTITLE 5. FUNDING NUMBERS Ultra-High Bypass Engine Aeroacoustic Study WBS–22–781–30–12 6. AUTHOR(S) NAS3–25269, Task Order 4 Philip R. Gliebe and Bangalore A. Janardan 8. PERFORMING ORGANIZATION 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) REPORT NUMBER GE Aircraft Engines Advanced Engineering Programs Department E–14087 1 Neumann Way, Mail Drop A304 Cincinnati, Ohio 45215 10. SPONSORING/MONITORING 9. SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES) AGENCY REPORT NUMBER National Aeronautics and Space Administration Washington, DC 20546– 0001 NASA CR—2003-212525 11. SUPPLEMENTARY NOTES Project Manager, James H. Dittmar (retired). Responsible person, Dennis Huff, Structures and Acoustics Division, NASA Glenn Research Center, organization code 5940, 216–433–3913.
12b. DISTRIBUTION CODE 12a. DISTRIBUTION/AVAILABILITY STATEMENT Unclassified - Unlimited Subject Category: 07 Distribution: Nonstandard Available electronically at http://gltrs.grc.nasa.gov This publication is available from the NASA Center for AeroSpace Information, 301–621–0390.
13. ABSTRACT (Maximum 200 words) 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.
14. SUBJECT TERMS 15. NUMBER OF PAGES Engine noise reduction; Turbofan engines; Ultra high bypass ratio; Fans; 16. PRICE CODE Aerodynamics; Aeroacoustics 19. SECURITY CLASSIFICATION 18. SECURITY CLASSIFICATION 17. SECURITY CLASSIFICATION 20. LIMITATION OF ABSTRACT OF ABSTRACT OF THIS PAGE OF REPORT Unclassified Unclassified Unclassified NSN 7540-01-280-5500 Standard Form 298 (Rev. 2-89) Prescribed by ANSI Std. Z39-18 298-102