Rotorcraft Noise and Emissions Reduction Reduction

ANERS 2011 October 2525-27 Marseille, France

Rotorcraft Noise and Emissions Reduction - Process for ‘Clean Sky The Measurement of Success Work done by by:: Chrissy Smith, AgustaWestland Ltd Ltd.., UK

Laurent Thevenot, Eurocopter SAS, FR Roberto D’Ippolito, LMS International, BE Jos Stevens, National Aerospace Laboratory NLR, NL Alf Junior,

DLR, DE

Ioannis Goulos, Cranfield University University,, UK

Contents Clean Sky Green Rotorcraft - Introduction Green Rotorcraft Process Generic Rotorcraft Derivation Y2000 Baseline Y2020+ Reference Y2020+ Conceptual

Green Rotorcraft Subprojects - Clean Sky Technologies The Technology Evaluator – Results Conclusion

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ANERS 2011, October 25-27, Marseille, France

Introduction GRC - Drivers for Clean Sky participation Growing presence of helicopters in air traffic

Specific & multiple mission profiles Sustainable growth requires reduction of impact on environment & population

Specific architecture & flight physics

Generic technologies (fixed-wing A/C) need to be adapted for R/C Dedicated solutions needed to address R/C specific issues

Clean Sky provides structured framework

Programme duration & size : less fragmentation Cross-fertilization between platforms, powerplants & equipment sectors

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Introduction - GRC Environmental Objectives

Halving noise

REACH compliance

Green Life Cycle Emission reduction ANERS 2011, October 25-27, Marseille, France

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Introduction - Clean Sky Structure Vehicle ITD1

Eco-design

Transverse ITD1 for all vehicles

For Airframe and Systems

Smart Fixed-Wing Aircraft

Green Regional Aircraft

Green Rotorcraft

Sustainable and Green Engines

Clean Sky Technology Evaluator Systems for Green Operations 5 1

ITD: Integrated Technology Demonstrator


Green Rotorcraft Process

EUROPA

GSP

Y2000

HELENA

GRC7

Year 2000 Year 2000 ‘Baseline’ Light Single2000 Year Baseline Year Light Twin 2000 Baseline Medium Twin Baseline

Year 2000 Fleet Feedback

Heavy Twin

Y2010

Year 2020+ ‘Reference’’ Year 2020+ Light Single

PhoeniX Model

‘Reference’’ Year 2000 Light Twin 2000 Year Baseline Year 2000 Medium Twin Baseline Heavy Twin Baseline

GRC 1,2,3,4,5 & 6 Parameters (variables)

Tilt Rotor

T.E.

Year 2020+ Fleet

Y2020+


Year 2020+ Year 2020+ ‘Conceptual’ Year 20 ‘Conceptual’ Light Single Year 2000 Light‘Conc Twin Year Light Single2000 Baseline Year 2000 Baseline Heavy Twin Baseline Tilt Rotor Diesel Engine

Periodic GRC (i) Technology 6 Insertion

Generic Rotorcraft Derivation – Y2000 Baseline

TEL Weight Average MAUM Ext Load kg

4000,000 A109

3500,000

AS355 BELL 206LT

3000,000

BELL 222

2500,000

BELL 230

2000,000

BELL 427

1500,000

BK-117B-1 EC135T1

1000,000

EC145 500,000

MBB105

0,000 0,00000 0,02000 0,04000 0,06000 0,08000

MD900

MD902

TEL Weighted Main Rotor Solidity

Y2000 Baseline Worldwide Database Consists of 16660 Civil with Military VIP and SAR rotorcraft – 353 different types Each allocated into a specific weight class Key design parameters collected including average annual flight hour Flight hour weighted average factor = No of r/c x av annual flight hour total no of hours flown by class

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Generic Rotorcraft Derivation – Y2000 Baseline Parameter

TEL

TEM

MAUM

2855 kg

4945 kg

Op Empty Mass

1570kg

2903 kg

10.98m

13.76 m

Parameter

TEL

TEM

Main rotor disc loading

30.16 kg/m²

33.23kg/m²

Main rotor solidity

0.0713

0.0713

Main rotor tip speed

218.87 m/s

226.92 m/s

Main rotor diameter

0.385 m

917.66 kg/m²

993.75 kg/m²

Main rotor blade mean chord

0.31m

Tail rotor disc loading Tail rotor solidity

0.12559

0.1472

Main rotor blade RPM

380

315

Tail rotor tip speed

212.67 m/s

217.70 m/s

Tail rotor diameter

1.99m

2.52 m

Tail rotor blade mean chord

0.196m

0.281 m

Tail rotor blade RPM

2341.77

2595.71

Tail rotor moment arm

6.82m

8.47m

No of main rotor blades

4

4

No of tail rotor blades

2

2

Y2000 Baseline Parameters derived from fleet database

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Generic Rotorcraft Derivation – Y2000 Baseline

SEL

TEL

TEM

TEH

AB206

MBB105

AB212

S61

AS350

AS355

AB412

AS332

H369

BK117

Bell 204*

Mi 8

A109

S76 AS365

Generic BO105 Helicopter VERSION: 00.1.4.5, DATED: 20/01/2010 105 4 : Aircraft type and mark code numbers 2 : Number of engines 2500.0 : Maximum Take-Off Mass 1500.0 : Operational Empty Mass 942.0 : Inertia of rotating components (kg.m2) 257500.0 : Datum power (W) 86.0 : Datum torque (%) 424.0 : Datum rotor speed (RPM) 100.0 : Datum Nr (%) 11000.0 : Accessory power (W) 15000.0 : Hub power at the datum rotor speed (W) 1.03 : Transmission loss factor Trimming process gains data 0.7 0.6 0.6 0.7 : Gains for coll., lat., long., yaw 0.5 0.5 0.7 : Gains for roll, pitch, lat. vel. Trimming process tolerances data 1.5 1.0 5.0 : Tolerances for FX, FY, FZ (N) 10.0 15.0 5.0 : Tolerances for MX, MY, MZ (Nm) Configuration data 1 1 Number of main and tail rotor files 1 Number of fuselage files 1 1 Number of fin and tailplane files 1 Number of engine files 4 Number of landing gear files 0 Number of AFCS files bo105.mro bo105.tro bo105.fus bo105.fin bo105.tpl Allison_250_20B.mxl bo105.mgp bo105.mgs bo105.ngp bo105.ngs

Example EUROPA input file * SEL R/C>4000kg

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Generic Rotorcraft Derivation – Y2000 Baseline Example output file for GSP (‘gsp.dat’) // EUROPA generated input file for GSP // time[s] press.[Pa] temper.[K] 0.0000 101244.4609 288.1064 0.5000 101243.3906 288.1058 1.0000 101243.3828 288.1058 1.5000 101243.3516 288.1058 2.0000 101243.2969 288.1058 2.5000 101243.2422 288.1057 3.0000 101243.2344 288.1057 3.5000 101243.2812 288.1058 4.0000 101243.4062 288.1058 4.5000 101243.5859 288.1059 5.0000 101243.7891 288.1060

power[W] 175621.5781 175615.8281 175593.0000 175299.3438 175122.2031 175200.6406 175255.7188 175405.2344 175613.8750 175949.8438 176358.6250

Platform Hosting Operational & ENvironmental Investigations for Rotorcraft

Example output file for HELENA (‘helena.dat’) OUTPUT FOR USE WITH PhoeniX PLATFORM time s 0.0000 0.0200 0.0400 0.0600 0.0800 0.1000 0.1200 0.1400 0.1600 0.1800 0.2000

xpos m 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000

ypos m 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000

zpos m 8.7397 8.7397 8.7397 8.7397 8.7397 8.7397 8.7397 8.7397 8.7397 8.7397 8.7397

vair m/s 0.0000 0.0000 0.0000 0.0001 0.0001 0.0001 0.0001 0.0001 0.0001 0.0001 0.0001

theta deg 3.0245 3.0245 3.0245 3.0245 3.0245 3.0245 3.0246 3.0247 3.0249 3.0251 3.0254

phi deg -3.1863 -3.1863 -3.1864 -3.1865 -3.1867 -3.1868 -3.1869 -3.1870 -3.1870 -3.1870 -3.1869

psi deg 360.0000 360.0000 359.9999 359.9999 359.9999 359.9999 359.9999 359.9999 359.9999 359.9999 359.9999

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Y2000 Baseline outputs compared to real rotorcraft for validation

Generic Rotorcraft Derivation – Y2020+ Reference

What would a replacement of the Clean Sky Year 2000 Twin Engine Light (TEL)

baseline (shown below) a rotorcraft representing 60’s, 70’s 80’s and 90’s technologies configuration and parameters be, if it were designed using today’s available technologies (ie. without Clean Sky)?

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Assumes the capability, role, payload and range maintained Taking into account historical trends, GRC(i) advice & today’s current r/c

design

Empty weight fraction is recalculated

Tip speed reduced

Main & tail rotors re-assessed

Rotorcraft drag improved in line with today’s current designs

Engine Technology - SAGE input

Assumes less fuel is required to carry Y2000 payload the same distance Process would take several iterations from GRC7 12


Parameter

Y2000 TEL

Y2020+ Ref TEL

Delta

Empty Weight Fraction

55%

53%

-2%

MTOM

2855kg

2680kg

-6.13%

Empty Mass

1570kg

1420kg

-10%

Standard fuel tank capacity

500kg

475kg

-

Maximum payload

700kg

700kg

-

Crew (included in useful payload)

85kg

85kg

-

Useful Load (payload, crew fuel)

1285kg

1260kg

-25kg

Tip Speed MR

218 m/s

214 m/s

-1.84%

Tip Speed TR

213 m/s

207 m/s

-2.82%

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The improvements of today’s technologies are used to reduce the size of the

Y2020+ Reference rotorcraft but payload range capability is maintained. With assistance from the GRC experts the EUROPA, GSP and HELENA

inputs are revised to reflect the impact of Y2010 technologies. The outputs of the Generic Y2020+ Reference are compared to real r/c

for validation

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Generic Rotorcraft Derivation – Y2020+ Conceptual Each GRC(i) developing technology is assessed for it’s predicted impact to Mass R/C drag co-efficient Power required Accessory power Engine bleed Noise reduction

Performance benefits

The Y2020+ Reference set of PhoeniX inputs are updated to replicate the

GRC(i) predicted results. Accuracy will improve over the Programme duration The Outputs of Y2020+ Conceptual generic r/c will be compared to real

rotorcraft for validation

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GRC1GRC1- Innovative Rotor Blades Passive Rotor Optimisation :

Objective : the development of active and passive technologies to provide the greatest possible reduction in rotor noise and fuel consumption

Technologies :

Active control surface e.g. Active Twist :

Passive Rotor Optimisation

Active Twist Active Gurney Flap Supporting enabling technologies

Active control surface e.g. Gurney flap :

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GRC2 - Drag Reduction of Airframe & Non Lifting Rotating Systems Objective : Reduction of emissions and noise through rotorcraft drag reduction and airframe optimisation

Technologies : Rotor hub drag reduction Fuselage drag reduction

Improved engine installation Optimised airframe design

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GRC3 – Integration of Innovative Electrical Systems

Objective : removal of hydraulic fluid, deletion of engine bleed air circuit. Weight reduction Technologies : Efficient electrical generation,

conversion and distribution (generic for small aircraft). Electromagnetic Actuators for helicopter flight control (ground testing). Efficient power generation and control for piezoelectric actuation, esp. active blades. Electrically driven Tail Rotor (concept studies). 18


GRC4 - Diesel Engine on a Light Helicopter Objectives : Significant reduction of CO2 emissions due to low fuel consumption of modern diesel engine technology Typically -30% to -40% over full flight envelope Using regular kerosene fuel (or biodiesel) To integrate the engine minimising the potential

adverse effects : • weight penalty ; • vibration ; • cooling system

Technology : Austroengine - Diesel engine 19


GRC5GRC5- Environmentally Environmentally--Friendly Flight Path Objectives :

Flight Guidance Systems

For the helicopter and tilt rotor Noise footprint and noise impact reduction Minimise fuel consumption and gas emission

Technologies : IFR & VFR approach and departure procedures Low level VFR & IFR en route navigation Rotorcraft specific shorter routes to minimise fuel consumption and gas Operational emission Requirements

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GRC6 – EcoDesign Demonstration for Rotorcraft Airframe Objective : To demonstrate eco-friendly life cycle processes for specific helicopter components Technologies : Structural Assessment • Recyclable composite parts • Surface preparation for composite-metallic bonding • Bonding and painting • Repair and testing

Review of Gearbox Housing • Cr6 free Magnesium protection & touch up and painting Transmission Components • Testing

Doors & Structural Gear Box Housing

Transmission Components • Cd free protection • Repair and painting • Testing ANERS 2011, October 25-27, Marseille, France

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GRC7 – Support to Technology Evaluator for Rotorcraft Objective : Provide the Technology Evaluator (TE) with a framework enabling measurement of CO2 and noise emissions of the Rotorcraft sector of the ATS Technology :PhoeniX: Platform Hosting Operational & ENvironmental Investigations for Rotorcraft

Helicopter Mission

Simulation Framework

GHG emission Noise Footprints

Image courtesy of Eurocopter

Image courtesy of AgustaWestland

TE Sample simulation results: ONERA (PhoeniX (PhoeniX / IESTA) Example of Dummy Data Noise Level Comparison Y2020 Non CS Y2000 Y2000

Y2020 With CS

With comparative values for fuel

Images courtesy of ONERA

burn CO2 & NOx Emissions 23


Conclusion:

GRC have provided a simulation framework that allows rotorcraft model trade-off studies (GRC7) environmental impact assessments (TE)

The framework can be used to assess the environmental

impact of any GRC(i) technology developed Future studies can be developed to assess major r/c

configuration changes The development of an invaluable impact assessment tool that

can be exploited way beyond the duration of CleanSky 24
