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LibertyWorks® Copyright © 2013 Rolls-Royce
Page 1
©2013 Rolls-Royce North American Technologies Inc. The information in this document is the property of Rolls-Royce North American Technologies Inc and may not be copied
or communicated to a third party, or used for any purpose other than that for which it is supplied without the express written consent of Rolls-Royce North American Technologies
Inc. This information is given in good faith based upon the latest information available to Rolls-Royce North American Technologies Inc, no warranty or representation is given
concerning such information, which must not be taken as establishing any contractual or other commitment binding upon Rolls-Royce North American Technologies Inc or any of its
subsidiary or associated companies
John Shade Program Director, Rolls-Royce North American Technologies, Inc.
AIAA Aerospace Today and Tomorrow
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Broad Portfolio of Commercial Aircraft Engines
Copyright © 2013 Rolls-Royce
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Commercial Business is Fueling US Jobs
Copyright © 2013 Rolls-Royce
Crosspointe, VA
Indianapolis, IN
Stennis, MS
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Key Challenges for Future Commercial Aircraft
Copyright © 2013 Rolls-Royce
Balancing Benefits…
Fuel Burn, NOx, and Noise
Weight, Drag
Affordability, Reliability
Significant Opportunities Exist
Components
Sub-Systems
Integrated Systems
Operational Benefits
Disruptive Technologies
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Continued SFC Improvements Attainable
Copyright © 2013 Rolls-Royce
0.30
0.35
0.40
0.45
0.50
0.55
0.60
0.65
0.70
0.700
0.725
0.975
1.000
0.950
0.925
0.900
0.875
0.825
0.850
0.800
0.775
0.750
0.4
0.425
0.450
0.475
0.500
0.525
0.550
0.575
0.600
0.625
Current High
Bypass ratio
Engines
Approaching
Theoretical
Limit, of
Propulsive
Efficiency
Approaching
Theoretical
Limit, of
Propulsive
Efficiency
Approaching
Theoretical Limit of
thermal efficiency
Approaching
Theoretical Limit of
thermal efficiency
Spe
cific
Fue
l C
on
su
mp
tio
n lb
/hr
/ lb
f@
0.8
Mn
Propulsive
Efficiency
Thermal
“Cycle”
Efficiency
Higher Pressures
Temperatures, Efficiencies
Novel Core Systems
Higher Pressures
Temperatures, Efficiencies
Novel Core Systems
Higher bypass ratios
Novel LP Systems
Higher bypass ratios
Novel LP Systems
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OPR 40 65+
Mechanical difficulty
Cycle temperatures
Fu
el
bu
rn I
mp
rovem
en
ts
Red
ucin
g L
ife R
eq
uir
em
en
ts
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Driving Thermal Efficiency
Copyright © 2013 Rolls-Royce
Materials
Aerodynamics
Architecture
Adv.
Cooling
Adv.
Sealing
Low NOx
Combustion
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Driving Propulsive Efficiency
Copyright © 2013 Rolls-Royce
BPR 10+ 50+
Technical risk
Installation issues
Open Rotor
UltraFanTM
Advanced HBR direct
drive turbofan
SF
C
Fu
el b
urn
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Driving Integrated Solutions
Copyright © 2013 Rolls-Royce
SFC
Optimum
Weight
Drag
Fan diameter
Integrated
energy
management
Core
configuration
Bypass ratio
optimization
Integrated
propulsion
system
Pneumatic
Hydraulic
Electric
Integrated
fuel burn
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Potential Game Changers
Copyright © 2013 Rolls-Royce
Pressure Gain
Combustion
Engine – Airframe Optimization
Advanced Cycles
Hybrid Electric Propulsion Nano materials
N-phase
Rectifier
N-phase
Generator
Turboshaft
Engine
Tra
nsm
issio
n
Lin
e(s
) (DC)
Inverter MotorN-phase
Rectifier
N-phase
Generator
Turboshaft
Engine
Inverter Motor
Inverter Motor
Inverter Motor
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Concluding Thoughts
Copyright © 2013 Rolls-Royce
Dynamic and vibrant industry
Significant benefits still achievable
Goals and objectives are aligned
FAA, NASA, ACARE, Defense…
Driving significant innovation
Balance performance, affordability, reliability, …
Future regulations
