Air Force Research Laboratory

Transcription

1 Air Force Research Laboratory Design of SMES Devices for Air and Space Applications 12 Oct 2011 Integrity Service Excellence Timothy J. Haugan, Ph.D. Research Physicist Propulsion Directorate Air Force Research Laboratory 19 October

2 Authors, Acknowlegements D. Latypov, J. V. Holle, BerrieHill Research Corp. Acknowledgments: AFRL/RZP Power Division and Air Force Office of Scientific Research 2

3 Outline: Introduction Air and Space Applications MJ for INVENT energy management MJ for Directed Energy to 2 GJ for Electric Aircraft power SMES Design Criteria and Optimization - Weight - Volume - Energy and Power Densities (mass specific) - Machine and Lifecycle Cost - Efficiency (charge/discharge cycle) - Operability and Logistics 3

4 Ragone Chart E. Shaffer (Army RDECOM), Power and Energy Tutorial, DEPS Nov

5 Ragone Chart E. Shaffer (Army RDECOM), Power and Energy Tutorial, DEPS Nov

6 Ragone Chart ~ NbTi or BSCCO wire BNL YBCO wire SMES - 30 MJ SAFT Li Battery 30 MJ (Discharge) (Charge) Chevy Volt Li-Battery 38 MJ (Discharge) Fuel Cells (Charge) Base chart from ASC 10 6

7 Energy Storage Power Ratings lower? IEEE Power and Energy Magazine, pp , jul/august

8 0.2 MJ Systems: Integrated Vehicle and Energy Management (INVENT) 0.3 m 0.15 m 8

9 More Electric Aircraft 9

10 Boeing 787 Electrical Systems 10

11 INVENT Energy Management Electrical Accumulator Unit: stores and controls power coming back onto the bus off of the load Loads: electromechanical actuators (EMA), electrohydrostatic actuators (EHA), directed energy weapons (DEW), advanced radar J. Wells, et al, Electrical Accumulator Unit for the Energy Optimized Aircraft, SAE International Journal of Aerospace, v. 1(1): pp ,

12 Peak Power (pu) Power Fluctuations on Modern Electric Aircraft (MEA) Power Draw Avg Load pu = power/avg power Representative Transient Power Profile Power back onto bus - Power: Pulsed transients of 150 kw can occur in about 10 ms - Regenerative Power: up to 150 kw waste heat - Duty Cycles: % - Switching frequencies: 0-20 khz J. Wells, et al, Electrical Accumulator Unit for the Energy Optimized Aircraft, SAE International Journal of Aerospace, v. 1(1): pp ,

13 5-50 MJ Systems: Directed Energy 0.75 m 0.25 m 13

14 Hybrid Power for Laser Weapons DEPS 2010 Conference Proceedings, General Atomics Aeronautical Distribution A : Approved for public release; Distribution unlimited 14

15 58 MJ Electrical Energy DEPS 2010 Conference Proceedings, General Atomics Aeronautical Distribution A : Approved for public release; Distribution unlimited 15

16 500 kw Li Batteries for DE Power Energy: 58 useable, ~ 200 MJ actual (?) Discharge time: sec Recharge Time: min Weight: - Total ~ 500 kg Cost: ~ $0.5-1 M (?) DEPS 2010 Conference Proceedings, General Atomics Aeronautical Distribution A : Approved for public release; Distribution unlimited 16

17 37 MJ System* Li Batteries Chevy Volt Charge time: hrs Weight: ~ 170 kg Cost: ~ $13K * Actual = 58 MJ, however useable = 38 MJ 17

18 Brookhaven National Lab SMES YBCO-wire ~ 30 MJ 0.75 m 0.25 m Charge/Discharge Time : 1 sec Mass: ~ kg dominated by wire; wire mass could drop ~ 5-10 x with new wire architecture (?) Cost: YBCO ~ $2.1M (will reduce < $2M in future) 18

19 Energy Storage Comparison MJ Class 38 MJ Li-Battery Chevy-Volt 58 MJ Li-Battery SAFT 30 MJ AFRL YBCO-wire SMES Energy 38 MJ* 58 MJ* 30 MJ Power 136 kw 500 kw > 30 MW Charge Time hrs min ~ 1 sec Discharge Time 280 sec** sec ~ 1 sec Mass 170 kg ~ 500 kg*** ~ 320 kg # Cycles Lifetime ~ ~ 30,000 > 200,000 (?) Efficiency ~ 96 % ~ 98 % Price (rough) $ 13K ~ $ M ~ $ 1-2 M Issues Very long charge time Fire hazard Withstand g- forces and vibration (?) * For Li batteries, only useful capacity = ~ 60% of total capacity is shown; e.g. for Chevy Volt actual capacity = 58 MJ but only 30-90% of the cycle can be used ** Not sure if fire hazard for this discharge rate ** Includes fire suppressant system 19

20 Ragone Chart ~ NbTi or BSCCO wire BNL YBCO wire SMES - 30 MJ SAFT Li Battery 30 MJ (Discharge) (Charge) Chevy Volt Li-Battery 38 MJ (Discharge) Fuel Cells (Charge) Base chart from ASC 10 20

21 0.2-2 GJ Systems: Aircraft Power 1.2 m 0.4 m 21

22 Electric-Aircraft: YUNTEC Int. e430 4 Passenger 100 kw 2 passenger aircraft html Impacts: - Flight Efficiency: 25% or more - Fuel Cost : 10x - Maintenance: only a few parts - Ownership Cost : extremely low - Noise: ultra-quiet - CO 2 emission: potentially zero - Other: vertical lift, distributed, etc.. Specifications Fuel 100 kw Motor Efficiency ~ % 100 kw Combustion All-Electric Engine (glider-style) (typical) ~ $50/hr ~ $3/hr (?) 95 % 9 gal/hr 90 MJ/hr Fuel Weight 70 lbs lbs (Li-Polymer) 22

23 Electric Aircraft: Pipestrel G4 Taurus NASA $1.35M Winner Green Flight Challenge Largest prize in aviation history other Capacity: 4 passenger Battery Size: 270 MJ / 2 hr Battery Weight: ~ 450 lbs per 270 MJ (one source 1100 lbs) Battery Type: Li-polymer; non-insurable fire hazard Fuel Efficiency: ~100 miles/gallon (!) Fuel Cost: $3/hr (!) Other Specifications Motor: 150 kw Motor Efficiency: 95% (includes controller) Drivetrain+Propeller Efficiency: ~ 60-70%? (gearbox needed) Total Empty Weight = 1250 lbs (without battery) Max. Possible Weight: 3300 lbs 23

24 Electric-Aircraft: EADS VoltAir EADS VoltAir all-electric aircraft concept unveiled in Paris European Aeronautic Defense and Space Company N.V. (EADS) parent company of Airbus Battery Size: GJ VoltAir's two next-generation lithium-air batteries would power two highly efficient superconducting electric motors as batteries approach and exceed energy densities of 1000 Wh/kg within the next two decades. http:

25 Hybrid-Electric Aircraft: NASA Subsonic Airliner (~2030) 30 MW Superconductor Power Transmission Superconductor Applications Needed Generators Motors Power Transmission Cables Power Inverters Class MW 4-6 MW 5-70 MW, DC 270V 1-30 MW H. D. KIM 30 MW Superconductor Electrical Generator ~ 6 MW Superconductor Electrical Motor TurboFans Power Electronics MW - Fuel Efficiency: +70% - Potential World-Market Pull: $400B/yr savings Recent NASA contract awards of C.A. Luongo, et al, IEEE Trans. Appl. Supercond. 19(3), 1005 (2009) 25

26 Design Criteria Summary 0.2 MJ INVENT 5-50 MJ Directed Energy GJ Electric Drive Aircraft High Duty Cycle AC Loss High Efficiency Low Weight/Volume Operability/Logistics Cost Rating Scale: 10 is highest and 1 is low for importance (approximate) 26

27 J E (A/mm²) J E vs Applied Field km-length 4-5K YBCO B Tape Plane YBCO B Tape Plane 1000 Nb-Ti RRP Nb 3 Sn Complied from ASC'02 and ICMC'03 papers (J. Parrell OI-ST) filament strand with Ag alloy outer sheath tested at NHMFL SuperPower tape used in record breaking NHMFL insert coil MgB MgB 2 /Nb/Cu/Monel Courtesy M. Tomsic, 2007 Maximal J E for entire LHC Nb Ti strand production ( ) CERN- T. Boutboul '07, and (- -) <5 T data from Boutboul et al. MT-19, IEEE- TASC 06) Bronze Nb 3 Sn 4543 filament High Sn Bronze-16wt.%Sn- 0.3wt%Ti (Miyazaki- MT18-IEEE 04) Applied Field (T) YBCO Insert Tape (B Tape Plane) YBCO Insert Tape (B Tape Plane) MgB 2 19Fil 24% Fill (HyperTech) 2212 OI-ST 28% Ceramic Filaments NbTi LHC Production 38%SC (4.2 K) Nb 3 Sn RRP Internal Sn (OI-ST) Nb 3 Sn High Sn Bronze Cu:Non-Cu

28 SMES Power Density Power Density B 2 /(2*μ o ), so YBCO wire can achieve much higher power densities by making small magnet coils = 25-30T (?) YBCO wire is 5-7x stronger than BSCCO or LTS, which is needed for high-field magnets. 28