AIRCRAFT ENGINE NOISE ROME AERONAUTICAL ENGINEERING UNIVERSITY May

Noise Reduction Trends Average Noise Reduction in Decibels per Operation B 737 -200 B

Noise Footprint Example SAME AIRCRAFT : GENERATION 1 ENGINES vs NEW GENERATION ENGINES CFMI

( INTRODUCTION ( ACOUSTIC REGLEMENTATION ( CFMI NOISE SITUATION ( NOISE INSIDE A NEW

Noise Certification Scheme AVIATION ENVIRONMENTAL PROTECTION ICAO ANNEX 16 Vol. 1 Chapter 3 (THIRD

EPNL : the noise aeronautical unit Measure Physical Unit : the décibel (d. B)

ICAO Acoustic Certification - Stage 3 Limits 110 CUT-BACK 4 ENGINES APPROACH 105 CUT-BACK

ICAO Noise Rules Evolution Noise Level Uncertified Aircraft ( « Stage 1 » )

Stage 4 Noise Regulation CAEP V PROPOSAL FOR STAGE 4 STAGE 3 REGULATION •

CFM International is a Joint Company of Snecma Moteurs, France and General Electric Co.

CFM 56 -3 B/C Snecma Moteurs has prime responsibilty for Noise Engineering on all

A Continued Effort To Reduce Noise Cumulated Margin (EPNd. B) ICAO CHAPTER 3 LIMIT

CFMI Engines Certified Noise Cumulative Margin A 321 / CFM 56 -5 B acoustic

Strong Integration in Engine and Aircraft Development Processes Advanced Project 1 Engine Component

Specific Prediction Tools to support all Engine Programme Steps Advanced Project Engine Component

Noise Sources & EPNL Calculation Engine Noise Sources Aircraft Factors Atmosphere Forward Fan Noise

Low Noise Engine Component Design Advanced Project 1 Engine Component Definition 2 Noise

Optimisation of Noise Reduction Systems Advanced Project 1 Engine Component Definition 2 Noise

Experimental Validation Advanced Project 1 Engine Component Definition 2 Anechoic Wind Tunnel Noise

Experimental Validation CFMI Proprietary Information Unauthorized Disclosure, Use, or Export are Prohibited. Rome

CFMI Noise Experience / Experimental Database • Jet noise model in wind tunnel –

Noise Family Plan Concept BASELINE AIRCRAFT FLIGHT DATA ANNEXE 16 PROCEDURES & CORRECTIONS BASELINE

Noise Family Plan Application 1 st Version : Certification using an acoustic flight test

B 737 NG / CFM 56 -7 B Example 2 CERTIFICATION STATIC TEST +

Current CFMI Engines Typical Noise Signature Engine Noise Sources Forward Fan Noise Approach Aft

Current Noise Reduction Technologies CYCLE OPTIMISATION Rotating Speed Reduction BLADES NUMBER OPTIMISATION BLADES /

Improvement of Current CFM 56 Engines Fan Noise Reduction through 3 D OGV

Nacelle Noise Reduction Systems Extension of Attenuation Bandwidth towards Low Frequency Range Improvement

Nacelle Noise Reduction Systems Finite Element Duct Progation Model to support Negatively Scarfed

Future Engine Applications Full Implementation of CAA capabilities to achieve Low Broadband Noise

Low Noise Aircraft Design - Engine installation • Optimisation of future aircraft designs should

Technologies Panel to support Optimum Aircraft System Definition Advanced CFD Models Basic Tools &

Upcoming Challenges • Goal to introduce in service by 2010 products allowing traffic growth

European Aircraft Noise Research Initiative Years 93 94 95 96 97 98 99

SILENCE(R) Technology Platform Project Coordinator : Snecma Moteurs Main Innovations : Noise Evaluation of

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

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AIRCRAFT ENGINE NOISE ROME AERONAUTICAL ENGINEERING UNIVERSITY May the 28 th, 2004 CFMI Proprietary Information Unauthorized Disclosure, Use, or Export are Prohibited. Rome Univ. 28/05/2004 - 1

Noise Reduction Trends Average Noise Reduction in Decibels per Operation B 737 -200 B 727 -200 140 -160 pax A 320 / CFM 56 -5 A B 737 NG / CFM 56 -7 high bypass ratio engines entry into service 5 d. B 7 to 8 d. B reduction per operation B 737 CL / CFM 56 -3 A 320 / CFM 56 -5 B 110 -130 pax optimization of noise reduction technologies 1. 5 d. B * Entry Into Service Year 1970 1980 1990 CFMI Proprietary Information Unauthorized Disclosure, Use, or Export are Prohibited. reduction per operation 2000 * Rome Univ. 28/05/2004 - 2

Noise Footprint Example SAME AIRCRAFT : GENERATION 1 ENGINES vs NEW GENERATION ENGINES CFMI Proprietary Information Unauthorized Disclosure, Use, or Export are Prohibited. Rome Univ. 28/05/2004 - 3

( INTRODUCTION ( ACOUSTIC REGLEMENTATION ( CFMI NOISE SITUATION ( NOISE INSIDE A NEW ENGINE PROJECT ( NOISE CERTIFICATION ( TODAY'S NOISE TECHNOLOGIES ( FOR A QUIET FUTURE ( QUESTIONS CFMI Proprietary Information Unauthorized Disclosure, Use, or Export are Prohibited. Rome Univ. 28/05/2004 - 4

Noise Certification Scheme 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) Thrust Reduction Take-Off (with cut-back) » 1000 ft 450 m 3° Approach 650 0 m Sideline 0 m 200 CFMI Proprietary Information Unauthorized Disclosure, Use, or Export are Prohibited. Rome Univ. 28/05/2004 - 5

EPNL : the noise aeronautical unit Measure Physical Unit : the décibel (d. B) d. B = 10 log 10 (acoustic pressure / 20 µPa) Physiological Correction Acoustic unit used For aircraft noise certification Physical units Representing annoyance Annoyance curves EPNL = Noise integration on T PNL (Perceived Noise Level) TPNL (d. B) TPNL max 10 d. B TPNL (Tone corrected Perceived Noise Level) T Temps de survol avion t (s) EPNL (Effective Perceived Noise Level) iso -sonical lines : same perception For human ear Vs frequency CFMI Proprietary Information Unauthorized Disclosure, Use, or Export are Prohibited. Rome Univ. 28/05/2004 - 6

ICAO Acoustic Certification - Stage 3 Limits 110 CUT-BACK 4 ENGINES APPROACH 105 CUT-BACK 3 ENGINES SIDELINE EPNL 100 CUT-BACK 2 ENGINES 95 90 85 10 100 Airplane MTOW (Tons) CFMI Proprietary Information Unauthorized Disclosure, Use, or Export are Prohibited. 1000 Rome Univ. 28/05/2004 - 7

ICAO Noise Rules Evolution Noise Level Uncertified Aircraft ( « Stage 1 » ) « Stage 1 » Phaseout « Stage 1 » Production Stop Stage 2 ICAO Decision Stage 3 ICAO Decision Stage 2 Production Stop Stage 2 Phaseout ICAO Decision US Europe Stage 4 (St 3 - 10 d. B Cum) CAEP V (2001) 1970 1975 1980 1985 1990 1995 2000 2005 2010 2015 NOISE STRINGENCY IS INCREASING WITH YEARS CFMI Proprietary Information Unauthorized Disclosure, Use, or Export are Prohibited. Rome Univ. 28/05/2004 - 8

Stage 4 Noise Regulation CAEP V PROPOSAL FOR STAGE 4 STAGE 3 REGULATION • STAGE 4 LIMIT FOR CUMULATIVE MARGIN 10 EPNd. B 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 EPNd. B AIRCRAFT CERTIFIED AFTER OCTOBER 06 , 1977 • APPLICABLE BY JANUARY 1 ST, 2006 TO CERTIFICATION OF NEW TYPES ( NEW OR DERIVATIVE A/C) • NO GLOBAL PHASE-OUT 1977 2001 Date of application 2006 CFMI Proprietary Information Unauthorized Disclosure, Use, or Export are Prohibited. Rome Univ. 28/05/2004 - 9

CFM International is a Joint Company of Snecma Moteurs, France and General Electric Co. , U. S. A. CFMI Proprietary Information Unauthorized Disclosure, Use, or Export are Prohibited. Rome Univ. 28/05/2004 - 11

CFM 56 -3 B/C Snecma Moteurs has prime responsibilty for Noise Engineering on all CFM 56 Programmes CFM 56 -7 B CFM 56 -5 A & 5 B CFM 56 -5 C CFMI Proprietary Information Unauthorized Disclosure, Use, or Export are Prohibited. Rome Univ. 28/05/2004 - 12

A Continued Effort To Reduce Noise Cumulated Margin (EPNd. B) ICAO CHAPTER 3 LIMIT Noise improvement on A 320 engined by CFM 56 Noise margin improved by 50% over 10 years Certification Year CFMI Proprietary Information Unauthorized Disclosure, Use, or Export are Prohibited. Rome Univ. 28/05/2004 - 13

CFMI Engines Certified Noise Cumulative Margin A 321 / CFM 56 -5 B acoustic kit STAGE 3 CFMI Proprietary Information Unauthorized Disclosure, Use, or Export are Prohibited. Rome Univ. 28/05/2004 - 14

Strong Integration in Engine and Aircraft Development Processes Advanced Project 1 Engine Component Definition 2 Noise Guarantees Development Certification 4 3 5 Thrust Reduction Fly. Over » 1000 ft 450 m 3° Approach 0 m 650 Sideline 0 m 200 CFMI Proprietary Information Unauthorized Disclosure, Use, or Export are Prohibited. Rome Univ. 28/05/2004 - 16

Specific Prediction Tools to support all Engine Programme Steps Advanced Project Engine Component Definition 2 1 Fan Noise Combustor Noise Turbine Noise Guarantees Development 3 4 Certification 5 Jet Noise Installation / Flight Effects Airframe Noise Propagation Effects Perceived Noise Level CFMI Proprietary Information Unauthorized Disclosure, Use, or Export are Prohibited. Community Noise Impact Rome Univ. 28/05/2004 - 17

Noise Sources & EPNL Calculation Engine Noise Sources Aircraft Factors Atmosphere Forward Fan Noise Aft Fan Noise Core Noise Turbine Noise Jet Noise FLIGHT & INSTALLATION EFFECTS Airframe Noise PROPAGATION EFFECTS EPNL CFMI Proprietary Information Unauthorized Disclosure, Use, or Export are Prohibited. Rome Univ. 28/05/2004 - 18

Low Noise Engine Component Design Advanced Project 1 Engine Component Definition 2 Noise Guarantees Development Certification 4 3 5 Aérodynamics Advanced Models & Prediction Techniques Acoustics Mécanical Design Fan Module CFMI Proprietary Information Unauthorized Disclosure, Use, or Export are Prohibited. Nozzles Rome Univ. 28/05/2004 - 19

Optimisation of Noise Reduction Systems Advanced Project 1 Engine Component Definition 2 Noise Guarantees Development 4 3 Aérodynamics Advanced Models & Prediction Techniques Certification 5 85 d. B Entrée d ’Air 80 d. B 75 d. B Acoustics 70 d. B 65 d. B Mécanical Design Demi-Sphère 3 Diametres 3 DOF Multilayer Liner Design 3 D Duct Propagation Method CFMI Proprietary Information Unauthorized Disclosure, Use, or Export are Prohibited. Rome Univ. 28/05/2004 - 20

Experimental Validation Advanced Project 1 Engine Component Definition 2 Anechoic Wind Tunnel Noise Guarantees Development Certification 4 3 5 Outdoor Engine Test Facility CFMI Proprietary Information Unauthorized Disclosure, Use, or Export are Prohibited. Rome Univ. 28/05/2004 - 21

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

Experimental Validation CFMI Proprietary Information Unauthorized Disclosure, Use, or Export are Prohibited. Rome Univ. 28/05/2004 - 23

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 CFMI Proprietary Information Unauthorized Disclosure, Use, or Export are Prohibited. Rome Univ. 28/05/2004 - 24

Noise Family Plan Concept BASELINE AIRCRAFT FLIGHT DATA ANNEXE 16 PROCEDURES & CORRECTIONS BASELINE AIRCRAFT FLIGHT NPD (EPNL) RESIDUAL NOISE - BASELINE ENGINE STATIC DATA STATIC TO FLIGHT PROJECTION BASELINE AIRCRAFT STATIC TO FLIGHT PROJECTION NPD (EPNL) DERIVED ENGINE STATIC DATA STATIC TO FLIGHT PROJECTION DERIVED AIRCRAFT STATIC TO FLIGHT PROJECTION NPD (EPNL) + CFMI Proprietary Information Unauthorized Disclosure, Use, or Export are Prohibited. DERIVED AIRCRAFT FLIGHT NPD (EPNL) Rome Univ. 28/05/2004 - 26

Noise Family Plan Application 1 st Version : Certification using an acoustic flight test Change on propulsion system Acoustic impact study YES Individual Impact < 0. 3 EPNd. B NO YES Analysis Dossier Outdoor Acoustic Engine Static Test CFMI Proprietary Information Unauthorized Disclosure, Use, or Export are Prohibited. Cumulative Impact < 5. 0 EPNd. B NO Flight Test Rome Univ. 28/05/2004 - 27

B 737 NG / CFM 56 -7 B Example 2 CERTIFICATION STATIC TEST + 1 CERTIFICATION FLIGHT TEST = SEVERAL AIRCRAFT / ENGINE NOISE CERTIFICATION CFMI Proprietary Information Unauthorized Disclosure, Use, or Export are Prohibited. Rome Univ. 28/05/2004 - 28

Current CFMI Engines Typical Noise Signature Engine Noise Sources Forward Fan Noise Approach Aft Fan Noise Combustor Noise Turbine Noise Cutback CFMI Proprietary Information Unauthorized Disclosure, Use, or Export are Prohibited. Jet Noise Sideline Rome Univ. 28/05/2004 - 30

Current Noise Reduction Technologies CYCLE OPTIMISATION Rotating Speed Reduction BLADES NUMBER OPTIMISATION BLADES / VANES SPACING OPTIMISATION CYCLE OPTIMISATION Fan Pressure Ratio Reduction CYCLE OPTIMISATION Speed Reduction MIXER ACOUSTIC LINING CFMI Proprietary Information Unauthorized Disclosure, Use, or Export are Prohibited. Rome Univ. 28/05/2004 - 31

Improvement of Current CFM 56 Engines Fan Noise Reduction through 3 D OGV Aeracoustic Design Jet Noise Reduction through Chevron Nozzle Design CFMI Proprietary Information Unauthorized Disclosure, Use, or Export are Prohibited. Rome Univ. 28/05/2004 - 32

Nacelle Noise Reduction Systems Extension of Attenuation Bandwidth towards Low Frequency Range Improvement of Liner Efficiency through 3 D Impedance Optimisation 20 3 DOF-SDOF 15 D L [d. B] 10 5 0 -5 315 630 1250 2500 5000 10000 Frequency [Hz] 3 Degree-of-Freedom Inlet Liner Hollow Sphere Exhaust Liner CFMI Proprietary Information Unauthorized Disclosure, Use, or Export are Prohibited. Rome Univ. 28/05/2004 - 33

Nacelle Noise Reduction Systems Finite Element Duct Progation Model to support Negatively Scarfed Inlet Design 3 -Diameter Sphere 85 d. B INLET 80 d. B 75 d. B 70 d. B 65 d. B Observer Plane CFMI Proprietary Information Unauthorized Disclosure, Use, or Export are Prohibited. Rome Univ. 28/05/2004 - 34

Future Engine Applications Full Implementation of CAA capabilities to achieve Low Broadband Noise Fan Design Active Technologies applied to Low Frequency Fan Tones Reduction OGV Static Pressure t = O t = 1/4 T t = 2/4 T t = 3/4 T CFMI Proprietary Information Unauthorized Disclosure, Use, or Export are Prohibited. Rome Univ. 28/05/2004 - 35

Low Noise Aircraft Design - Engine installation • Optimisation of future aircraft designs should consider powerplant installation factors as an opportunity for further noise reduction • Significant development of aerocoustics modelling and appropriate testing facilities will support such activities CFMI Proprietary Information Unauthorized Disclosure, Use, or Export are Prohibited. Rome Univ. 28/05/2004 - 36

Technologies Panel to support Optimum Aircraft System Definition Advanced CFD Models Basic Tools & Source Understanding Source Models Propagation Models Turbomachinery Noise Reduction Technology Exhaust Noise Reduction Technology Airframe noise Reduction Techniques Noise Reduction at Source Noise Reduction Systems Nozzle Design & Liner Technology High Lift Devices & Landing Gear

Upcoming Challenges • Goal to introduce in service by 2010 products allowing traffic growth at no environmental cost (Ex : 10 d. B cumulative margin re Chapter 4 for a typical 90 Tons MTOW Twin Engine Aircraft) : Þ Development of appropriate panel of noise reduction technologies to support individual optimisation of aircraft system components: - Engine - Nacelle - Landing Gear - High Lift Devices Þ Combined optimisation of powerplant and aircraft taking into consideration installation factors and flight performance CFMI Proprietary Information Unauthorized Disclosure, Use, or Export are Prohibited. Rome Univ. 28/05/2004 - 39

European Aircraft Noise Research Initiative Years 93 94 95 96 97 98 99 00 01 02 03 04 05 JEAN Advanced CFD Models Basic Tools & Source Understanding Source Models Turbo. Noise CFD FANPAC National / Industry Research Exhaust Noise Reduction Technology Airframe noise Reduction Techniques Noise Reduction at Source Noise Reduction systems Nozzle Design & Liner Technology High Lift Devices & Landing Gear RAIN DUCAT Propagation Models Turbomachinery Noise Reduction Technology RESOUND FANPAC RANNTAC National / Industry Research SILENCE(R) Technology Platform RAIN CFMI Proprietary Information Unauthorized Disclosure, Use, or Export are Prohibited. Rome Univ. 28/05/2004 - 40

SILENCE(R) Technology Platform Project Coordinator : Snecma Moteurs Main Innovations : Noise Evaluation of Advanced Engine Concepts Validation 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 Engine Validations 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.

CFMI Proprietary Information Unauthorized Disclosure, Use, or Export are Prohibited. Rome Univ. 28/05/2004 - 42