Document
National Aeronautics and Space
NASA Jet Noise Research
Administration
Brenda Henderson and
NASA Glenn Research Center Turbine Engine Technology Symposium September 15, 2016 www.nasa.gov Dayton, OH www.nasa.gov
Outline
• NASA Program Overview
• NASA Jet Noise Facilities
• Highlights of current jet noise research
NASA’s Aeronautics Research Mission
Directorate (ARMD)
Six thrust areas
• Safe, efficient growth in global operations
• Innovation in commercial supersonic aircraft
• Ultra - efficient commercial vehicles
• Transition to low - carbon propulsion
• Real - time system safety assurance
• Assured autonomy for aviation transformation
Four programs to address these areas
• Advanced Air Vehicles Programs (AAVP)
• Airspace Operations and Safety Program (AOSP)
• Integrated Aviation Systems Program (IASP)
• Transformative Aeronautics Concepts Program (TACP)
Advanced Air Vehicles Program ( AAVP)
Studies, evaluates, and develops technologies and capabilities that can be
integrated into fixed wing and vertical lift aircraft as well as explores far -
future concepts that hold revolutionary improvements to air travel
Aeronautics Evaluation and Test Capabilities Advanced Revolutionary Vertical Lift • Ground test capabilities Composites Project Technology Project • Subsonic, transonic, supersonic, hypersonic wind tunnels and propulsion test facilities • Ames, Glenn, and Langley Commercial Supersonic Advanced Air Transport Technology Project Technology Project • Revolutionize energy efficiency and environmentally • Low Noise Propulsion for compatible fixed wing transport aircraft Low Boom Aircraft • Fan and High - lift Noise
Commercial Supersonic Technology
(CST) Project
Develop tools, technologies, and knowledge to help eliminate
today’s technical barriers to practical commercial supersonic
flight: sonic boom, fuel efficiency, airport community noise, high - altitude emissions, structural weight and flexibility,
airspace operations, and the ability to design future vehicles
in an integrated, multidisciplinary manner
Concluding with new technical challenge beginning FY2017
Integrated Aviation Systems (IAS)
Program
Conducts flight oriented, integrated, system - level research and technology
development that supports the flight research needs across the ARMD
strategic thrusts, the programs, and their projects
Environmentally Responsible Aviation Project Unmanned Aircraft Systems Integration in the • Explores and assesses new vehicle concepts and National Air Space System enabling technologies through system - level experimentation to simultaneously reduce fuel burn, noise and emissions • Research Challenges • Advanced UHB Engine Designs for Specific Flight Demonstrations and Capabilities Project Fuel Consumption and Noise Reduction • Conducts complex and integrated small scale • Advanced Airframe and Engine Integration flight research demonstrations Concepts for Community Noise and Fuel • Operates, sustains, and enhances flight research Burn Reduction test capabilities
NASA Jet Facilities
Aero - Acoustic Propulsion Lab (AAPL)
Glenn Research Center • 65’ radius anechoic dome • Nozzle Acoustic Test Rig (NATR) – A three - stream jet - engine simulator (HFJER) with simulated forward flight • Small Hot Jet Acoustic Rig (SHJAR) – Single - stream, specialty jet rig • Far - field acoustics, phased arrays, flow rakes, hotwire, schlieren , PIV, IR, Rayleigh, Raman, PSP
NASA Jet Facilities
Low Speed Aeroacoustic Wind Tunnel (LSAWT)
Langley Research Center Twin jet aeroacoustic test with nozzles near aft deck fuselage section of Hybrid Wing Body
NASA Aircraft Noise Prediction Program (ANOPP2)
Len Lopes: Leonard.V.Lopes@nasa.gov
• Total aircraft noise prediction capability for subsonic and supersonic aircraft
– ANOPP2: mixed - fidelity prediction framework that includes ANOPP and high - fidelity, physics - based analyses – Predict aircraft source noise, propagation and impact at receiver in near or far - field
• Specific Capabilities for Supersonic Aircraft Applications
– Coupling with Model Center for high speed aircraft noise optimizations – Comprehensive ability to predict high speed jet mixing & broadband shock noise (JeNo, MDOE) – Methodologies for mixer - ejector configurations Recent focus on Jet/surface interaction Jet/jet interaction Propagation Effects • Spherical spreading • Atmospheric absorption • Ground absorption/reflection • Refraction/scattering • Wind profile • Temperature profile • Atmospheric turbulence • Terrain effects Receptor • human • electronic Receiver Propagation Source
ANOPP2: Mixed - Fidelity System Noise Framework
Semi - empirical CAA MIT UCI FSC shielding Jet - scattering ANOPP scattering Brooks Self Engine Trailing edge Airframe Brooks Self + CFD Shielding Trailing Edge Boeing TFAN+BFAN/CDUCT Slat, TE, Flap, LG Fan + duct propagation Effect of Chevron, JENO ANOPP - Stone Jet nozzle aspect ratio Jet ANOPP - PAS CRPFAN Py - ASSPIN (ORAS)++ Open rotor Open rotor Open rotor Open rotor * Noise reduction predictions * Semi - empirical based on surrogate model single and dual developed from experiments stream jet * Single and dual stream jet predictions mixing noise predictions using an acoustic analogy Jet/surface interaction effects Jet3D: PAA Jet/jet interaction effects Jet & Pylon * Twin and Tri - stream jet and jet * Jet - pylon interaction surface interaction measurements predictions using an acoustic and predictions analogy POC: Len Lopes: Leonard.V.Lopes@nasa.gov
Subsonic Jet Noise Prediction with JENRE
Daniel Ingraham, daniel.j.ingraham@nasa.gov N3 - X,
• JENRE: Jet Engine Noise Reduction code from the Naval Research Lab
NASA
• Monotonically Integrated Large - Eddy Simulation (MILES) code using the
Concept
flux - corrected transport (FCT) method to combine low - and high - order finite
element schemes on unstructured meshes
• Proven capability predicting noise from realistic supersonic jets, including
chevrons, multiple streams, pylons.
• Current work at NASA Glenn: validate JENRE capability against Glenn's
considerable experimental database of subsonic jet experiments
• Long - term plan: use JENRE to investigate flows of interest to NASA, (tone
producing jets , jet - surface interaction, offset streams, etc .)
Subsonic Jet Noise Prediction with JENRE
Daniel Ingraham, daniel.j.ingraham@nasa.gov N3 - X,
NASA
• Preliminary test case: set point 3 from the Tanna Matrix
Concept
• Axisymmetric nozzle, unheated jet, exit Ma = 0.513
• Axial velocity statistics show good agreement with experiment, despite
relatively coarse grids (15e6 and 27e6 nodes)
• Noise predictions in process.
Centerline Lip Line
JSI - High Aspect Ratio Nozzle
Clifford Brown, clifford.a.brown@nasa.gov
• 16:1 aspect ratio nozzle
• Flush mounted surface – vary lengths
• Acquired: – Far - field noise – Phased array noise source localizations
JSI trailing edge noise combined with
– In - flow total pressure
resonance
– Static pressure on surface
Resonance depends on
geometry and jet condition
Surface at nozzle lip 1 0 0 x / h = 9 . 5 E I s o l a t e d 9 0 8 0 ) B d ( D 7 0 S P PSD (dB) 6 0
Θ =90º
5 0 - 1 0 1 2 1 0 1 0 1 0 1 0 3 0 6 2 8 2 S t
St
h h
Jet Surface Interaction Noise – Planar Exhaust
Abbas Khavaran, abbas.khavaran@nasa.gov N3 - X,
Interaction of exhaust noise with a nearby solid surface
NASA
An acoustic analogy simulation approach
Concept
Predict mixing (scrubbing) noise and Trailing Edge Noise (TEN)
Assumptions
High aspect ratio rectangular exhaust Locally parallel mean flow Generalized Acoustic Analogy (GAA) to predict scrubbing noise Rapid Distortion Theory (RDT) to predict TEN Measurement: M=0.72, 8:1 AR Exhaust
Approach
Mean flow and turbulence – Steady RANS
θ
Map RANS solution to acoustic grid Source/GF volume integration for scrubbing noise Source/GF area integration at the plate tip for TEN Superimpose two component noise Reference: AIAA - 2016 - 2863
Jet Surface Interaction Noise – Planar Exhaust
8:1 Rectangular Exhaust, Abbas Khavaran, abbas.khavaran@nasa.gov N8ZH19XTE12 Set Point NPR NTR M N3 - X, M=0.72
NASA
SP03 1.19 1.0 0.51 SP05 1.42 1.0 0.72
Concept
SP07 1.86 1.0 0.98 M=0.72
Near End of Plate
Three - Stream Nozzle Experiments
Brenda Henderson, brenda.s.henderson@nasa.gov Core Cowl Length Tertiary Cowl Length Tertiary Nozzle
AOA
Investigations Investigations Core Nozzle c /A t A Plug Bypass Nozzle
Axisymmetric Nozzle System
A /A b c Thick Side
Nozzle Design Space
Jet Conditions
Condition NPR NPR NTR NPR Jet Type c b c t Designation 1.0 Two 1.6 1.6 3.0 10% PLR 1.4 , 1.8, 2.1 Three Thin Side 1.0 Two 1.8 1.8 3.0 Full Throttle
Offset Nozzle System
1.4, 1.8, 2.1 Three
Offset Stream Results
Center Plane
Thick Side
Thin Side
Thin Side Thick Side
Thin Side
Thick Side
U/U e
w
n
x/D = 1 . 6
eqA
x/D = 0 . 2
x/D = 0 . 9
eqA eqA
Azimuthal variation in
peak jet noise direction
Noise Predictions for Offset Three - Stream Jets
Stewart Leib Stewart.J.Leib@nasa.gov
Improved turbulence modeling for three - stream jet RANS
Improved predictions of azimuthal
using Explicit Algebraic Stress Model
variation of sound field
(Nicholas Georgiadis & Dennis Yoder)
Thick Side 110 120 Thin Side o SST = 60 = 120 SST 105 115 New EASM, Recal New EASM, Recal 100 110 95 105 90 100 PSD (dB) 85 95 Predictions 80 90 75 85 70 80 -2 -1 0 1 10 10 10 10 St 110 120 o = 30 = 150 105 115 100 110 95 105 90 100 PSD (dB) 85 95 Predictions 80 90 75 85 70 80 -2 -1 0 1 10 10 10 10 St
JSI - Multi - Stream Nozzle
Clifford Brown, clifford.a.brown@nasa.gov
• 2 and 3 stream nozzle systems
• Vary surface length and standoff
• Acquired: – Far - field noise – Phased array noise source localizations
• Empirical modeling of JSI noise spectra
Shielded Side
(Model) - Data d P S D ( d B ) 1 2 0 1 0 0 P 0 S - 1 D - 2 ( d 8 0 - 3 B - 4 ) - 5 - 6 - 6 6 0 1 5 0 ) .
g e 4 0 d ( e - 0 . 5 l 1 0 0 g n A r l o g a l ( 0 . 5 1 S 0 o t ) P D e 5 0 8 5 7 7 8 5 7 7
Aircraft Noise Assessments
Dennis Huff, Dennis.L.Huff@nasa.gov
Offset Nozzle Orientations Lockheed Martin “1044” Aircraft
Morgenstern, J., et al., “Advanced Concept Studies for Supersonic Commercial Transports Engine Service in the 2018 - 2020 Period Phase 2,” NASA CR - 2015 - 218719, July 2015.
Engine Parametric Study
Each symbol represents a different combination of engine Overall Pressure Ratio (OPR), main engine bypass and throttle ratio, and design bypass ratio of the third stream (BPRt).
Effective Perceived Noise Levels
Programmed Lapse Rate (PLR) * NPRc = 1.8 NPRt = 1.6 Ab/Ac = 2.5 Estimated to meet jet noise requirements for new Chapter 14 noise regulations with no margin * Not approved by the FAA
Low Noise Propulsion for Low Boom Aircraft
To Be
Technical Challenge Completed Sep. 2016
James Bridges james.e.bridges@nasa.gov Design tools and innovative concepts for integrated supersonic propulsion systems with noise levels of 10 EPNdB less than FAR 36 Stage 4 demonstrated in ground test.
Deliverables: 1) Validate noise prediction and system modeling tools for prediction & optimization of N+2 supersonic airliner 2) Integrated aircraft solutions meeting airport noise requirements with viable range and low boom 3) Validation of acoustic performance and predicted design trades.
2013 2014 2015 2016 Multiple jet acoustic Three - stream nozzle and Aft - deck noise Final isolated nozzles, effect documented, IVPv2 tests completed. database acquired. system models modeled. validated.
Optimized engine IVPv2 tests meet Non - axisymmetric jet cycle determined. Integrated acoustic test expectations noise code created. articles created and Final candidate First empirical models for tested. System nozzles created.
three - stream and IVP IVPv2 design predictions, acoustic nozzle systems confirmed with LES. goal validated.
Integration of noise prediction, innovative nozzles, and system
modeling to achieve aggressive goals.