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Rome Univ. 28/05/ CFMI Proprietary Information - Unauthorized Disclosure, Use, or Export are Prohibited. AIRCRAFT ENGINE AIRCRAFT ENGINE NOISE NOISE ROME AERONAUTICAL ENGINEERING UNIVERSITY May the 28 th , 2004

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Rome Univ. 28/05/2004 - 1CFMI Proprietary Information -Unauthorized Disclosure, Use, or Export are Prohibited.

AIRCRAFT ENGINE AIRCRAFT ENGINE NOISENOISE

ROME AERONAUTICAL ENGINEERING UNIVERSITY

May the 28th, 2004

Rome Univ. 28/05/2004 - 2CFMI Proprietary Information -Unauthorized Disclosure, Use, or Export are Prohibited.

* Entry Into Service Year

2000 *1970 1980 1990

B737 CL / CFM56-3

B737 NG / CFM56-7

B727-200

5 dB

B737-200

A320 / CFM56-5A

A320 / CFM56-5B

110-130 paxoptimization of noise

reduction technologies 1.5 dBreduction per

operation

high bypass ratio enginesentry into service

7 to 8 dBreduction per

operation

140-160 pax

Average Noise Reduction in Decibels per OperationNoise Reduction Trends

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Noise Footprint Example

SAME AIRCRAFT : GENERATION 1 ENGINES vs NEW GENERATION ENGINES

Rome Univ. 28/05/2004 - 4CFMI Proprietary Information -Unauthorized Disclosure, Use, or Export are Prohibited.

INTRODUCTIONACOUSTIC REGLEMENTATIONCFMI NOISE SITUATIONNOISE INSIDE A NEW ENGINE PROJECTNOISE CERTIFICATIONTODAY'S NOISE TECHNOLOGIESFOR A QUIET FUTUREQUESTIONS

Rome Univ. 28/05/2004 - 5CFMI Proprietary Information -Unauthorized Disclosure, Use, or Export are Prohibited.

Noise Certification Scheme

Thrust Reduction

≈1000ft

Approach 2000 m3°

450 m Sideline

Take-Off (with cut-back)

6500 m

AVIATION ENVIRONMENTAL PROTECTION ICAO ANNEX 16 Vol.1 Chapter 3 (THIRD EDITION 1993)JOINT AVIATION REQUIREMENTS : JAR 36 (1997)FEDERAL AVIATION REGULATIONS : FAR 36 (1993)RUSSIAN AVIATION REGISTRATION : AP-36 (AVIATION REGULATION - 36)

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EPNL : the noise aeronautical unit

10 dB

TPNL max

Temps de survol avion

TPNL (dB)

T

t (s)

Measure Physical Unit : the décibel (dB)dB = 10 log10 (acoustic pressure / 20 µPa)

Physiological Correction

Annoyance curves

Acoustic unit usedFor aircraft noise certification

EPNL = Noise integration on T

Physical unitsRepresenting annoyance

iso-sonical lines :same perception For human earVs frequency

PNL (PerceivedNoise Level)

EPNL (Effective Perceived Noise Level)

TPNL (Tone corrected

Perceived Noise Level)

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85

90

95

100

105

110

10 100 1000Airplane MTOW (Tons)

EPN

L

APPROACH

CUT-BACK 4 ENGINES

CUT-BACK 3 ENGINES

CUT-BACK 2 ENGINES

SIDELINE

ICAO Acoustic Certification - Stage 3 Limits

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ICAO Noise Rules Evolution

Stage 2 Phaseout

US Europe

Stage 2Production

Stop

1970 1975 1980 1985 1990 1995 2000 2005 2010 2015

Stage 3

« Stage 1 » Phaseout

Stage 2

« Stage 1 »Production

Stop

ICAO Decision

Stage 4 (St3 - 10 dB Cum)

Uncertified Aircraft (« Stage 1 »)

ICAO Decision

ICAO Decision

CAEP V (2001)

Noi

se L

evel

NOISE STRINGENCY IS INCREASING WITH YEARS

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Stage 4 Noise Regulation

2006Date of application

STAGE 3 REGULATION

AIRCRAFT CERTIFIED AFTER

OCTOBER 06 , 1977

CAEP V PROPOSAL FORSTAGE 4

• STAGE 4 LIMIT FOR CUMULATIVE MARGIN 10 EPNdB MORE STRINGENT THAN STAGE 3 LIMIT

• NO TRADES ALLOWED re. to STAGE 3

• ANY 2 POINTS MUST HAVE MARGINS VS STAGE 3 THAT SUM TO AT LEAST 2 EPNdB

• APPLICABLE BY JANUARY 1ST, 2006 TO CERTIFICATION OF NEW TYPES ( NEW OR DERIVATIVE A/C)

• NO GLOBAL PHASE-OUT

1977 2001

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INTRODUCTIONACOUSTIC REGLEMENTATIONCFMI NOISE SITUATIONNOISE INSIDE A NEW ENGINE PROJECTNOISE CERTIFICATIONTODAY'S NOISE TECHNOLOGIESFOR A QUIET FUTUREQUESTIONS

Rome Univ. 28/05/2004 - 11CFMI Proprietary Information -Unauthorized Disclosure, Use, or Export are Prohibited.

CFM Internationalis a Joint Company of

Snecma Moteurs, France and

General Electric Co., U.S.A.

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CFM56-5A & 5B

CFM56-7B

CFM56-3B/C

CFM56-5C

Snecma Moteurs hasprime responsibilty

for Noise Engineeringon all CFM56 Programmes

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Certification Year

-20

-15

-10

-5

0

1985 1990 1995 2000

Cum

ulat

ed M

argi

n (

EP

NdB

)

ICAO CHAPTER 3 LIMIT

Noise improvement on A320 engined by CFM56

Noise margin improved by

50%over

10 years

A Continued Effort To Reduce Noise

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0

5

10

15

20

25

30

0 50 100 150 200 250 300

MTOW (t)

CUMULATIVE MARGIN (EPNdB)

STAGE 4

CFMI Engines Certified Noise Cumulative Margin

STAGE 3

A321 / CFM56-5B acoustic kit

Rome Univ. 28/05/2004 - 15CFMI Proprietary Information -Unauthorized Disclosure, Use, or Export are Prohibited.

INTRODUCTIONACOUSTIC REGLEMENTATIONCFMI NOISE SITUATIONNOISE INSIDE A NEW ENGINE PROJECTNOISE CERTIFICATIONTODAY'S NOISE TECHNOLOGIESFOR A QUIET FUTUREQUESTIONS

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Strong Integration in Engine and Aircraft Development Processes

22 44 553311

ThrustReduction

≈1000ft

Approach2000 m3°

450 mSideline

FlyOver

6500 m

AdvancedProject

Engine ComponentDefinition

NoiseGuarantees Development Certification

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22 44 553311

FanNoise

CombustorNoise

TurbineNoise

JetNoise

Propagation Effects

Installation / Flight Effects

Perceived Noise Level

AirframeNoise

Community Noise Impact

AdvancedProject

Engine ComponentDefinition

NoiseGuarantees Development Certification

Specific Prediction Tools to support all Engine Programme Steps

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Engine NoiseSources

AircraftFactors

Atmosphere

ForwardFan Noise

Aft FanNoise

CoreNoise

TurbineNoise

JetNoise

PROPAGATION EFFECTS

FLIGHT & INSTALLATION EFFECTS

EPNL

AirframeNoise

Noise Sources & EPNL Calculation

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Low Noise Engine Component Design

44 553311

Aérodynamics

Mécanical Design

AcousticsAcoustics

AdvancedModels &Prediction

Techniques

22

Fan Module Nozzles

AdvancedProject

Engine ComponentDefinition

NoiseGuarantees Development Certification

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AdvancedModels &Prediction

Techniques

Optimisation of Noise Reduction Systems

44 553311 22

80 dB

85 dB

75 dB

70 dB

65 dB

Demi-Sphère3 Diametres

Entréed ’Air

3DOF MultilayerLiner Design

Aérodynamics

Mécanical Design

AcousticsAcoustics

3D Duct Propagation Method

AdvancedProject

Engine ComponentDefinition

NoiseGuarantees Development Certification

Rome Univ. 28/05/2004 - 21CFMI Proprietary Information -Unauthorized Disclosure, Use, or Export are Prohibited.

Experimental Validation

22 44 553311

Anechoic Wind Tunnel Outdoor Engine Test Facility

AdvancedProject

Engine ComponentDefinition

NoiseGuarantees Development Certification

Rome Univ. 28/05/2004 - 22CFMI Proprietary Information -Unauthorized Disclosure, Use, or Export are Prohibited.

Experimental Validation

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Experimental Validation

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CFMI Noise Experience / Experimental Database

• Jet noise model in wind tunnel– 12 campaigns since 1985, more than 60 configurations

• Engine static test– more than 15 static engine acoustic certification– more than 20 campaigns– more than 120 configurations including acoustic liners

• Flight test– 9 engineering flight tests– 6 certification flight tests

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INTRODUCTIONACOUSTIC REGLEMENTATIONCFMI NOISE SITUATIONNOISE INSIDE A NEW ENGINE PROJECTNOISE CERTIFICATIONTODAY'S NOISE TECHNOLOGIESFOR A QUIET FUTUREQUESTIONS

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Noise Family Plan ConceptBASELINE AIRCRAFT

FLIGHT DATA

BASELINE ENGINE

STATIC DATA

DERIVED ENGINE

STATIC DATA

BASELINE AIRCRAFTFLIGHT NPD (EPNL)

BASELINE AIRCRAFTSTATIC TO FLIGHT

PROJECTION NPD (EPNL)

DERIVED AIRCRAFTSTATIC TO FLIGHT

PROJECTION NPD (EPNL)

DERIVED AIRCRAFTFLIGHT NPD (EPNL)+

-RESIDUAL

NOISE

ANNEXE 16 PROCEDURES

& CORRECTIONS

STATIC TO FLIGHTPROJECTION

STATIC TO FLIGHTPROJECTION

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Noise Family Plan Application

Changeon propulsion system

Acoustic impact study

IndividualImpact

< 0.3 EPNdB

OutdoorAcoustic

Engine StaticTest

AnalysisDossier Flight Test

YES NO

CumulativeImpact

< 5.0 EPNdBYES NO

1st Version : Certification using an acoustic flight test

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B737NG / CFM56- 7B Example2 CERTIFICATION STATIC TEST + 1 CERTIFICATION FLIGHT TEST

= SEVERAL AIRCRAFT / ENGINE NOISE CERTIFICATION

8

10

12

14

16

18

20

45 50 55 60 65 70 75 80 85

MTOW (t)

STAGE 4

CUMULATIVE MARGIN (EPNdB)

Rome Univ. 28/05/2004 - 29CFMI Proprietary Information -Unauthorized Disclosure, Use, or Export are Prohibited.

INTRODUCTIONACOUSTIC REGLEMENTATIONCFMI NOISE SITUATIONNOISE INSIDE A NEW ENGINE PROJECTNOISE CERTIFICATIONTODAY'S NOISE TECHNOLOGIESFOR A QUIET FUTUREQUESTIONS

Rome Univ. 28/05/2004 - 30CFMI Proprietary Information -Unauthorized Disclosure, Use, or Export are Prohibited.

Current CFMI Engines Typical Noise Signature

Forward Fan

Noise

AftFan

Noise

CombustorNoise

TurbineNoise

JetNoise

0%10%20%30%40%50%60%70%80%90%

100%

1 2 3Approach SidelineCutback

Engine NoiseSources

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Current Noise Reduction Technologies

BLADES NUMBER OPTIMISATIONBLADES / VANES SPACING OPTIMISATION

MIXER

CYCLE OPTIMISATION Speed Reduction

ACOUSTIC LINING

CYCLE OPTIMISATION Rotating Speed Reduction

CYCLE OPTIMISATION Fan Pressure Ratio Reduction

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Improvement of Current CFM56 Engines

Jet Noise Reduction through Chevron Nozzle Design

Fan Noise Reductionthrough 3D OGV Aeracoustic Design

Rome Univ. 28/05/2004 - 33CFMI Proprietary Information -Unauthorized Disclosure, Use, or Export are Prohibited.

Nacelle Noise Reduction Systems

-5

0

5

10

15

20

315 630 1250 2500 5000 10000

3DOF-SDOF

Frequency [Hz]

∆L

[dB

]

Improvement of Liner Efficiency through 3D Impedance Optimisation

Extension of Attenuation Bandwidthtowards Low Frequency Range

3 Degree-of-FreedomInlet Liner

Hollow Sphere Exhaust Liner

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Finite Element Duct Progation Model to support Negatively Scarfed Inlet Design

80 dB

85 dB

75 dB

70 dB

65 dB

3-Diameter Sphere

Observer Plane

INLET

Nacelle Noise Reduction Systems

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Future Engine Applications

Full Implementation of CAA capabilitiesto achieve Low Broadband Noise Fan Design

t = O t = 1/4 T t = 2/4 T t = 3/4 T

OGVStaticPressure

Active Technologies applied to Low Frequency Fan Tones Reduction

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Low Noise Aircraft Design - Engine installation

• Optimisation of future aircraft designs should consider powerplantinstallation factors as an opportunity for further noise reduction

• Significant development of aerocoustics modelling and appropriate testing facilities will support such activities

TurbomachineryNoise

ReductionTechnology

Noise Reductionat Source

Noise ReductionSystems

Nozzle Design &Liner Technology

ExhaustNoise

ReductionTechnology

Basic Tools& Source

Understanding

Airframe noiseReduction

Techniques

High Lift Devices & Landing Gear

Advanced CFD Models

Source Models

Propagation Models

Technologies Panel to support Optimum Aircraft System Definition

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INTRODUCTIONACOUSTIC REGLEMENTATIONCFMI NOISE SITUATIONNOISE INSIDE A NEW ENGINE PROJECTNOISE CERTIFICATIONTODAY'S NOISE TECHNOLOGIESFOR A QUIET FUTUREQUESTIONS

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Upcoming Challenges

• Goal to introduce in service by 2010 products allowing traffic growth at no environmental cost (Ex : 10 dB cumulative margin re Chapter 4 for a typical

90 Tons MTOW Twin Engine Aircraft) :

⇒ Development of appropriate panel of noise reduction technologies tosupport individual optimisation of aircraft system components:

- Engine

- Nacelle

- Landing Gear

- High Lift Devices

⇒ Combined optimisation of powerplant and aircraft taking into consideration installation factors and flight performance

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93 94 95 96 97 98 99 00 01 02 03 04 05

TurbomachineryNoise

ReductionTechnology

Noise Reductionat Source

Noise Reductionsystems

Nozzle Design &Liner Technology

ExhaustNoise

ReductionTechnology

Basic Tools& Source

Understanding

DUCAT

FANPAC

FANPAC RESOUND

RANNTACFANPAC

Airframe noiseReduction

Techniques

High Lift Devices & Landing Gear

RAIN

RAIN

Advanced CFD Models

Source Models

Propagation Models

TurboNoise CFD

JEAN

RESOUND

Years

National / Industry Research

National / Industry ResearchSILENCE(R)Technology

Platform

European Aircraft Noise Research Initiative

Project Coordinator : Snecma MoteursMain Innovations :Noise Evaluation of Advanced Engine ConceptsValidation of Novel Noise Reduction Solutions:

- Low Noise Engine Component Design- Nacelle and Nozzle Liner Concepts- Active Noise Control Applications- Inlet and Nozzle Advanced Design

Adaptation of Solutions to Helicopter EngineValidations of Airframe Noise Reduction Solutions;

- Landing Gear- High Lift Devices

Project Duration : 4 years (Start 04/01)Total Budget: 112 MEuros (50% EC Support)Participation: 51 partners from 14 EU countries

+ 2 Associated States.

SILENCE(R) Technology Platform

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