Aircraft Noise Reduction Subproject Overview

National Aeronautics and Space Administration

Aircraft Noise Reduction Subproject Overview

Aircraft Noise Reduction Subproject

Advanced Air Transport Technology Project

Subproject Manager: Hamilton Fernandez (LaRC) Subproject Technical Lead: Douglas Nark (LaRC) Subproject Technical Lead: Dale Van Zante (GRC) Acoustics Technical Working Group Meeting April 19-20, 2016 NASA LaRC, Hampton, VA www.nasa.gov Advanced Air Transport Technology Project Advanced Air Vehicles Program

Outline

• Background/Motivation

• Objective

• Technical Areas

• Benefit/Pay-off

• Noise Reduction Concepts

• Quiet High Lift

• Multi-Degree of Freedom (MDOF) Liners

• Additional Noise Reduction Concepts

• System Noise Assessments

• Concluding Remarks and Future Plans

Advanced Air Transport Technology Project Advanced Air Vehicles Program

NASA Subsonic Transport System-Level Metrics

v2013.1 TECHNOLOGY GENERATIONS Strategic Focus (Technology Readiness Level = 4-6) TECHNOLOGY BENEFITS* N+1 (2015) N+3 (2025) N+2 (2020**) 1. Energy Efficiency Noise -42 dB -52 dB -32 dB (cum margin rel. to Stage 4) LTO NOx Emissions -75% -80% -60% (rel. to CAEP 6) 2. Environmental Cruise NOx Emissions Compatibility -70% -80% -55% (rel. to 2005 best in class) + + Aircraft Fuel/Energy Consumption -50% -33% -60% (rel. to 2005 best in class) Projected benefits once technologies are matured and implemented by industry. Benefits vary by vehicle size and mission. N+1 and N+3 values are * referenced to a 737-800 with CFM56-7B engines. N+2 values are referenced to a 777-200 with GE90 engines.

ERA’s time-phased approach includes advancing “long-pole” technologies to TRL 6 by 2015 CO2 emission benefits dependent on life-cycle CO2e per MJ for fuel and/or energy source used ** + + N+3 values are referenced to a 737-800 with CFM56-7B engines Research addressing revolutionary far-term goals with opportunities for near-term impact Advanced Air Transport Technology Project Advanced Air Vehicles Program

Aircraft Noise Reduction (ANR) Technologies

Objective Explore and develop aero-structural-acoustic technologies to directly reduce perceived community noise without impacting performance Technical Areas and Approaches large-scale test aero-acoustic Acoustic Liners and Duct Propagation – Advanced, low-drag liner concepts Airframe Noise – Flap/Slat and landing gear noise reduction Propulsion Noise – Fan and core noise reduction Propulsion Airframe Aeroacoustics (PAA) – Installation effects on perceived noise bench-top demo hardware main Benefit/Pay-off element Component noise reduction with minimal impact on cove filler assembly slat weight and performance – Direct contribution to Ultra-Efficient Commercial High Lift System Advanced Vehicles Strategic Thrust Noise Reduction Liner Concepts – Liner and non-active-flow-control high-lift system technology may have early insertion potential Advanced Air Transport Technology Project Advanced Air Vehicles Program

Aircraft Noise Reduction Technical Areas

• Li#ing&components&

Airframe&

• Landing&components&

Li

n

• Propulsor&

Propulsion&

e

• Core&(combustor&&&turbine)&

r

s&

Propulsion/

• Installa<on&Effects&on&Noise&Sources&

Airframe&

• Shielding/ScaCering&

Aeroacous<cs&(PAA)&

System&Noise&Impact&Assessments&

Advanced Air Transport Technology Project Advanced Air Vehicles Program

Quiet High-Lift

Aero-Structural-Acoustic High-Lift System Test (14x22)

Slat Cove Filler (SCF)

Conventional High-Lift (CHL)

Common Research Model (CRM)

LE Slat Noise o (3D CFD, α =5.5 ) Slat Gap Filler (SGF)

• CHL/CRM: Open geometry high-lift configuration based on the high-speed CRM

• Testbed for slat, flap side-edge, and landing gear noise reduction technology

• SCF and SGF will be tested in the 14x22 in FY18

• Modified slats fabricated using realistic materials, but non-articulating

Advanced Air Transport Technology Project Advanced Air Vehicles Program

Quiet High-Lift

CHL/CRM V2.0 Wind Tunnel Model

Slat Model in Wind Tunnel

• 6.25% scale model of a section at mid-span of the CRM outboard slat

• Lift and drag measurements at various angles of attack and flow speeds

• Deployable slat and flap via embedded actuators

• Study fluid-structure interaction (FSI) of slat treatment during articulation

• Risk reduction for 14x22 test and beyond

• Validation of computational models and overall design process

Advanced Air Transport Technology Project Advanced Air Vehicles Program

MDOF Liner Concept

NASA/Honeywell 9x15 Test

Broadband Benefit Demonstrated Sideline OASPL Attenuation at 80% RPM Multi-Degree of Freedom (MDOF) Single-Degree of 0 30 60 90 120 150 180 (OASPL, 1kHz-25kHz) Freedom (SDOF) Acoustic Attenuation, dB Directivity Angle, degrees from upstream NASA MDOF Honeywell SDOF Nacelle Liner Attenuation Spectra, 80% RPM 135 degrees from upstream Attenuation, dB 0 5 10 15 20 25 Frequency, kHz Hub Liner – 1 Hub Liner - 2 Advanced Air Transport Technology Project Advanced Air Vehicles Program

Additional Concepts

Soft Vane Over-The-Rotor Acoustic Treatment Integrated Tests Isolated Rig Tests TRL Notable&benefits&possible:&Need&further&development DGEN Aero-propulsion Lean nine-point fuel injector (LDI) Research Turbofan (DART) Swirler Air Fuel Fuel injector tip Air Understand&combustorIdesign&change&impacts& Advanced Air Transport Technology Project Advanced Air Vehicles Program

Low-Drag Liner Concepts

Grazing Flow Impedance Tube (GFIT) Test

(Phase&1&–&No&Sound)& Baseline&

Objective

• Reduced liner drag for internal/external applications

Technical Areas and Approaches

• Acoustic benefits and improved aerodynamic performance (fuel burn)

Advanced Air Transport Technology Project Advanced Air Vehicles Program

Fan Acoustic Casing Treatment

Objective

Evaluate fan acoustic casing treatments noise reduction potential of up to TRL 3

R4/SDT (

Technical Areas and Approaches

Series of progressively higher TRL testing • Normal Incidence Tube Testing (LaRC) • Low Speed Fan Testing (ANCF, GRC) • Scaled UHB Fan Testing (W-8, GRC) Acoustics: In-duct array testing Aero: Determine aerodynamic impact

Benefit/Pay-off

• Benefits up to 4-5dB reduction have been demonstrated in previous testing Advanced Air Transport Technology Project Advanced Air Vehicles Program

Soft Vane Technology

Objective

Evaluate soft vane broadband noise reduction

Technical Areas and Approaches

Series of progressively higher TRL testing • Generate and characterize noise generated by interaction with upstream turbulence Acoustics: Improve acoustic benefit Aero: Quantify and reduce aerodynamic impact

Benefit/Pay-off

• Soft vanes have shown a significant noise reduction potential on the Source Diagnostic Test hardware.

• ERA assessments predict potential 1.5 EPNdB system noise reduction Advanced Air Transport Technology Project Advanced Air Vehicles Program

Objective

Further validate and improve acoustic

scattering prediction capabilities

noise source

• Employ well-defined sound source

Turbulent wake

• Utilize open, generic geometry

flow

Benefit/Pay-off

• Establish validation database

Shield/fuselage

• Characterize effect of flow, model

wake, and source location

Scattering of sound by an aircraft fuselage Advanced Air Transport Technology Project Advanced Air Vehicles Program Laser-induced

Technical Areas and Approaches

noise source

Acoustic scattering test to be performed

in QFF

• with 2-D NACA0012 airfoil

• using non-intrusive, laser-induced, Laser-induced noise source - bench test monopole source.

• Test repeated at DLR and ONERA

In & out of flow mics turn table

Status: Test preparations are on-going

with glass

• Test hardware fabrication is nearly

insert noise complete.

sourc e

• Laser and optics set-up needed to meet

test requirements has been established.

airfoil Laser

• Traverse systems for the microphones

and

and laser/optic assembly have been

optics flow

developed and controls integrated in the

QFF data acquisition system.

nozzle

• Data acquisition expected to run May-

Quiet Flow Facility (QFF) test set-up June.

Advanced Air Transport Technology Project Advanced Air Vehicles Program

Technical Areas and Approaches

Laser-induced

QFF acoustic scattering test

noise source

• 2-D NACA0012 airfoil

• Non-intrusive, monopole source.

• Test repeated at DLR and ONERA

Laser-induced noise source - bench test

Status

Test preparations are on-going

In & out of

flow mics • Hardware fabrication is nearly complete

turn table with glass

• Laser and optics set-up needed to meet

insert

test requirements established

noise sourc

• Traverse systems for the microphones

e

and laser/optic assembly have been

airfoil

developed and controls integrated in the

Laser QFF data acquisition system.

and optics • Data acquisition expected in May-June.

flow nozzle Quiet Flow Facility (QFF) test set-up Advanced Air Transport Technology Project Advanced Air Vehicles Program

Propulsion Airframe Aeroacoustics

Source Shielding/Scattering Acoustically Treated Tail (External Liners) Preliminary Prediction of Shielding Impact Jet-Surface Interaction Test (JSIT) Predicted Noise Goal Gap (EPNL)

• Conceptual Stage (Initial Feasibility Study)

• No N+2/N+3 Noise Technologies Applied

• FSC: Improved Shielding Model • FSC-A+: Refined Fan Prediction Advanced Air Transport Technology Project Advanced Air Vehicles Program

System Noise Impact Assessment

SA

LTA

Overall(system(noise(impacts(of(various(component(technologies(assessed(through(

periodic(system(noise(studies(for(baseline(and(unconven>onal(aircra?(configura>ons.(

Advanced Air Transport Technology Project Advanced Air Vehicles Program

Concluding Remarks and Future Plans (1/2)

ANR Subproject is well poised within the AATT Project to support Ultra-Efficient

Commercial Vehicles Strategic Thrust

• Technical Challenge, TC 3.1, to be concluded in FY18 with results from

MDOF Liners and Quiet High-Lift Test in 14x22

• Technical Challenge, TC 3.2, to be formulated and proposed with technical

investments to close current predicted noise goal gap with associated

impact/benefits to performance goals

• Acoustic Liners and Duct Propagation: Low-drag advanced liners

• Airframe Noise: High-lift system/gear interaction

Integrated&&

• Propulsion Noise: Fan and core noise reduction

PAA&Test&

• PAA: Installation effects on sources

• System Noise Impact Assessments

Advanced Air Transport Technology Project Advanced Air Vehicles Program

Concluding Remarks and Future Plans (2/2)

Technical Challenge, TC 3.3, to be formulated and proposed with technical

investments in propulsors for FY18-22 within the AATT Project.

Background:

• At the conclusion of ERA, there was still a need for higher TRL, advanced

propulsor research.

• The new TC 3.3 is intended to have significant partner cost share and to

focus on maturing propulsor technologies for N+3 systems.

Technical investment areas:

• Benchmark low PR fan test case (aero/acoustic/aeromechanic)

• Advanced ducted and/or unducted propulsor systems (To duct or not to duct?)

• Propulsion Airframe Installation/ Aeroacoustics for low PR fan systems

Engine Architecture Road Map Ref Fuel Burn 500Nm Ref CFM56 - 5B/P 1st Generation Advanced Turbo Fan Cert 2015 - 10% nd 2 Generation Cert 2020 - 20% Cert 2025 Open Rotor Ultimate Green - 30% Engine Cert 2030+ EPNdB vs Ch4 - 5 - 15 - 25 Snecma Research & Technology / September 2011 
  

 
  
 
 


 

 


  


 

 

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Better Noise 16 16 16 Advanced Air Transport Technology Project Advanced Air Vehicles Program Your(Title(Here(

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Advanced Air Transport Technology Project Advanced Air Vehicles Program

Backup Slides

Advanced Air Transport Technology Project Advanced Air Vehicles Program

Flight Demo Plan

Hybrid Electric Propulsion Demonstrators Transport Scale Total Demonstration Cost: $700M Preliminary Ground Test Risk Reduction Design Design & Build Flight Test Small Scale “Build, Fly, Learn” Design & Build Flight Test Design & Build Flight Test Life Cycle Cost: $400-500M Ground Test Preliminary Design & Build Flight Test Risk Reduction Design “Purpose-Built” Preliminar UEST Potential y Demonstrators Candidates Life Cycle Cost: $400-500M Design Preliminary Ground Test Design & Build Flight Test Design Risk Reduction Life Cycle Cost: $850M Preliminary Design & Build Flight Test Design Fully integrated UEST Demonstrator Life Cycle Cost: $430M Flight Test Design & Build

FY17( FY18( FY19( FY20( FY21( FY22( FY23( FY24( FY25( FY26(

Advanced Air Transport Technology Project Advanced Air Vehicles Program

Aircraft Noise Reduction (ANR)

AATT TC3.1 (FY18) Fan & High-Lift Noise Reduce fan (lateral and flyover) and high-lift system (approach) noise on a component basis by 4 dB with minimal impact on weight and performance (TRL5) TC3.1 Investment • Acoustic Liners & Duct Propagation – Multi-Degree of Freedom (MDOF) • Airframe Noise – High-Lift System AATT eTC3 Quieter Low-Speed Performance Develop, quantify and assess the impact of component noise reduction technologies across the airframe noise, acoustic liner technology, propulsion noise, and propulsion airframe aeroacoustics technical areas. Overall system noise impacts of various component technologies will also be assessed through periodic system noise studies for candidate conventional and unconventional aircraft configurations.

eTC3 Investment • Acoustic Liners & Duct Propagation – Low-Drag Advanced Liners • Airframe Noise - • Propulsion Noise • Propulsion-Airframe Aeroacoustics (PAA) Advanced Air Transport Technology Project Advanced Air Vehicles Program

ANR Research Approach

Example: Single Aisle (SA) - Baseline Example: Large Twin Aisle (LTA) - Baseline 10 dB EPNL Approach Reference Sideline Reference “dB&Math”& 2x(Source(Acous>c(Power(=(3(dB(Increase( 10x(Source(Acous>c(Power(=(10(dB(Increase ( Cutback Reference Advanced Air Transport Technology Project Advanced Air Vehicles Program

ANR Research Approach

D8 - Baseline N3-X 10 dB EPNL Jet Jet Core Core Main Gear Gear Gear Nose Slats Total Total Flaps Flaps Ex) Edge Edge Trailing Trailing Fan (In.)

Fan (In + Fan (Ex.)

Approach Reference Sideline Reference “dB&Math”& 2x(Source(Acous>c(Power(=(3(dB(Increase( 10x(Source(Acous>c(Power(=(10(dB(Increase ( Cutback Reference Advanced Air Transport Technology Project Advanced Air Vehicles Program

Propulsion Noise: Possible Concepts

Over-the-Rotor acoustic Concepts for Study treatment fan case Distributed Fans Counter-Rotating Shrouded Fans Open Rotor Advanced Air Transport Technology Project Advanced Air Vehicles Program

Propulsion Airframe Aeroacoustics

Source Shielding/Scattering Jet-Surface Interaction Test (JSIT)

Acoustically Treated Tail (External Liners) Advanced Air Transport Technology Project Advanced Air Vehicles Program

MIT D8.5 System Noise Assessment

NASA systems analysis on the MIT D8.5 configuration - update

Sept 2015

• Fast Scattering Code (FSC) for shielding/scattering predictions

• Updated fan and airframe source level predictions

70$ 62.6$ 60$

52 dB

50$ 44.1$ 39.0$ 36.8$ 40$ D8.5.MIT 30$ D8.5.201 20$ D8.5.201 10$ D8.5.201 0$ CUM)EPNL)Below)Stage)4) D8.5%MIT) D8.5%2014) D8.5%2015%FSC) D8.5%2015%FSC%A+) NASA Team: Berton, Burley, Guynn, Nark, Welstead Advanced Air Transport Technology Project Advanced Air Vehicles Program