Document
National Aeronautics and Space Administration
NASA Electric Propulsion System Studies
James L. Felder, Systems Analysis & Integration Advanced Air Transport Technology Project NASA Glenn Research Center Cleveland, OH www.nasa.gov
Outline
• Why Electric Propulsion
• Overview of Electric Propulsion architectures.
• Example Implementations.
– Boeing SUGAR Volt
– ECO - 150
– STARC - ABL
– N3 - X
Why Electric Propulsion
• Allows the use of non - CO2 emitting terrestrial power
sources in aviation
• High flexibility in moving power around the vehicle is a key
enabler for several different ways to integrate propulsion
into the aircraft in ways to further reduce the energy
intensity of the vehicle
– Boundary Layer Ingestion
– Wingtip Propulsors
– Highly distributed embedded propulsor arrays
Four Cardinal Electric Propulsion Architectures
Motor
Parallel Hybrid Turboelectric
Turbofan Electric Bus Turboshaft Electric Bus Distributed Fans Generator Motor Fuel Battery Motor Fan Fuel
All Electric Series Hybrid
Motor Battery Turboshaft Motor(s) Electric Bus Electric Bus Distributed Fans Generator Fuel 1 to Many Fans Motor Battery
But Wait, There's More!
Series/Parallel Partial Hybrid
Motor Turbofan Electric Bus 1 to Many Fans Generator Motor Fuel Battery Fan
Boeing SUGAR Volt (Parallel Hybrid)
NASA Goal • 150 passenger • 3500 nm range • 750 Wh/kg battery energy density • 1.3 MW motor meets NASA N+3 fuel reduction goal at the same energy consumption as SUGAR High • 5.3 MW motor reduces fuel consumption further at the price of increased energy consumption compared to SUGAR High Boeing Research & Technology, Boeing N+3 Subsonic Ultra Green Aircraft Research (SUGAR) Final Report
Boeing SUGAR Volt CO2 Reduction
Dependent on Terrestrial Charging Grid
Flow around an aircraft tailcone
• Diffusion into the base region of the Total Pressure Vs Height aircraft means the velocity profiles represent more than just the viscous in boundary layer of the fuselage - • Velocity profile nearly uniform Height circumferentially, so distortion is nearly all radial 0 1 2 3 4 Pt - psia Velocity in - Height 0 200 400 600 800 Velocity - ft/sec
STARC - ABL*
( Partial Turboelectric/Fuselage BLI Fan)
Passengers 150 Range 3500 nm Cruise Speed Mach 0.7 Tailcone Thruster Motor 2.6 MW (3500 hp) Turbofan Generator 1.44 MW (1940 hp ) Turbofan Fan 1.95 MW (2615 hp) Fuel Burn Reduction ~10% (vs same tech turbofan) Gen Motor *STARC - ABL: Single - aisle Turboelectric AirCRaft – Aft Boundary Layer
ESAero ECO - 150
(Fully Turboelectric/Distributed)
Propulsor non - cryo motor cryo motor Turbogenerator with non - cryo generator
• 150 Passenger/35k lbs Payload
• 3500 nm range
• Mach 0.8 Cruise
• 2 8 - MW turbine driven generators
• 16 1 - MW motor driven fans
• Fuel reduction from 737 - 700
Empirical Systems Aerospace: SBIR NNX13CC24P
• 44% Non - cryo
Phase I 2013 / NNA10DA88Z Task 6 2012 / SBIR NNX10CC81P Phase I 2009 / SBIR NNX09CC86P
• 59% Cryo (with LH2 cooling)
Phase I 2008
NASA N3 - X
(Fully Turboelectric/Distributed/BLI )
Baseline: B777 - 200LR/GE90 - 115B
Passengers: 300
Range: 7500 nm
Payload: 118,000 lbs
Cruise Speed: Mach 0.84
Fuel: 279,800 lbs
N3 - X Superconducting
Passengers: 300
Range: 7500 nm
Payload: 118,000 lbs
Cruise Speed: Mach 0.84
Fuel: 76,000 lbs
( - 72%)
Generators: 30 MW
Motors: 4.3 MW
Turboelectric distributed propulsion benefits on the N3 - X vehicle, Kim H.D. et al, Aircraft Engineering and Aerospace Technology Journal, Vol 86 Iss 6 pp. 558 - 561 2014 (http :// dx.doi.org/10.1108/AEAT - 04 - 2014 - 0037)
NASA N3 - X Propulsion System Weight
N3 - X
B777 - 200LR
N3A/UHB
SCFCL & AC/DC SCFCL Electric Machin Converter Energy Storage Energy AC/DC Converter Storage Device DC/AC Motor Drive Circuit Breakers Superconducting Fault SCFCL Current Limiter
GE90 - 115B
GE90 - like UHB TeDP/Cryo TeDP/LH2 Thrust – RTO 180,400 139,000 94,200 85,800 Non - electrical System - lbs 58,600 30,500 28,100 Electrical System/Gearbox - lbs 1800 21,300 16,300 Total Weight - lbs 47,300 60,400 51,800 44,400 For the power range bar for each aircraft class • The left side is the smallest electrical machine in a partially electrified system • The right side is the size of the generator in a twin engine fully electrified system Your Title Here