Woodward et al., 2001 - Google Patents

Benefits of swept-and-leaned stators for fan noise reduction

Woodward et al., 2001

View PDF
Document ID
4909846292811215519
Author
Woodward R
Elliott D
Hughes C
Berton J
Publication year
Publication venue
Journal of Aircraft

External Links

Snippet

An advanced high bypass ratio fan model was tested in the NASA John H. Glenn Research Center 9££ 15 Foot Low-Speed Wind Tunnel. The primary focus of this test was to quantify the acoustic bene ts and aerodynamic performance of sweep and lean in stator vane design …
Continue reading at ntrs.nasa.gov (PDF) (other versions)

Classifications

    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies
    • Y02T50/67—Relevant aircraft propulsion technologies
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING ENGINES OR PUMPS
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING ENGINES OR PUMPS
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function

Similar Documents

Publication Publication Date Title
Woodward et al. Benefits of swept-and-leaned stators for fan noise reduction
Woodward et al. Fan Noise Source Diagnostic Test--Far-field Acoustic Results
Kingan et al. Relative importance of open rotor tone and broadband noise sources
Stephens et al. Acoustic shielding for a model scale counter-rotation open rotor
Akatsuka et al. System noise assessment of NASA supersonic technology concept aeroplane using JAXA’s noise prediction tool
Sinnige et al. Aerodynamic and aeroacoustic performance of a propeller propulsion system with swirl-recovery vanes
Nesbitt et al. Flight test results for uniquely tailored propulsion-airframe aeroacoustic chevrons: community noise
Woodward et al. Acoustic benefits of stator sweep and lean for a high tip speed fan
Woodward et al. Noise benefits of increased fan bypass nozzle area
Rizzi et al. Auralization of Flyover Noise from Open-Rotor Engines Using Model-Scale Test Data
Hughes et al. The effect of bypass nozzle exit area on fan aerodynamic performance and noise in a model turbofan simulator
Bonneau et al. Turbofan broadband noise predictions using a 3-D ZDES rotor blade approach
Crichton et al. Preliminary fan design for a silent aircraft
Heidelberg Comparison of tone mode measurements for a forward swept and baseline rotor fan
Magliozzi Noise characteristics of model counter-rotating Prop-Fans
Woodward Noise of two high-speed model counter-rotation propellers at takeoff/approach conditions
Woodward et al. Fan noise reduction with increased bypass nozzle area
Stephens Data Summary Report for the Open Rotor Propulsion Rig Equipped With F31/A31 Rotor Blades
Guo et al. Open rotor noise shielding by blended-wing-body aircraft
Kissner et al. The Challenge of Tonal Fan Noise Prediction for an Aircraft Engine in Flight
Joseph et al. Aircraft noise
Moore et al. Reflection of noise from aero engines installed under an aircraft wing
Woodward Comparison of far-field noise for three significantly different model turbofans
Woodward et al. Far-field acoustic characteristics of multiple blade-vane configurations for a high tip speed fan
Woodward et al. Aeroacoustic analysis of fan noise reduction with increased bypass nozzle area