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National Aeronautics and Space Administration
www.nasa.gov 1
Development Status of the Fission Surface Power Technology Demonstration Unit
Maxwell Briggs, Marc Gibson, and Steven Geng NASA Glenn Research Center
National Aeronautics and Space Administration
www.nasa.gov
Presentation Outline
• Fission Power Systems • The Fission Surface Power Technology
Demonstration Unit – Overview – Component Development
• Reactor Simulator • Annular Linear Induction Pump • Stirling Engine • Heat Rejection
– Sub-System Testing • Heat Rejection System • RXSim Sub-system
– System Level Test Status
2
National Aeronautics and Space Administration
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Fission Power Systems (FPS) Fission Surface Power (FSP) (10 – 100 kW)
3
Small Reactor (Kilopower) (1 – 10 kW) Nuclear Propulsion (100 kW - ~1MW)
National Aeronautics and Space Administration
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FSP Technology Demonstration Unit
• Non-nuclear demonstration of a Fission Surface Power System • Full-scale FSP components • Thermal vacuum environment • Heat provided by a reactor simulator • Originally designed to achieve TRL 6
4
National Aeronautics and Space Administration
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Technology Demonstration Unit (TDU)
5
∆P +28 kPaat 1.75 kg/s
(0.5-2.5 kg/s)
NaK850 K
∆P +190 kPaat 0.375 kg/s(0.2-0.6 kg/s)
440 kPa160 kPa
H2O~375 K
(925 K and275 kPa max)
(450 K and690 kPa max)
Core Sim48 kWe nom
(90 kWe max)
Waste Heat Exchanger
Pwr Conv12 kWe nom
(14.4 kWe max)
PVA RVA
PP RP
∆P
≤14
kPa
∆P
≤7 k
Pa
∆P
≤15
kPa
Vacuum≤1x10-5 torr
PCU Cntl12 kWe nom
6-13.2 kWe reg.
ELS≥10 kWe
400 Vac
η ≥25%η ≥10%
η ≥90%
120+/-6 Vdc
Waste heat rejected to ambient air
Original Design
Reduced budget design
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Core Simulator
• Core Simulator – Thermally and hydraulically similar to
FSP core – Tested with TDU ALIP at MSFC June
2012 – Delivered to GRC January 2013 – Can be operated in constant power,
constant temperature, or reactivity feedback modes.
6
Core simulator
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ALIP
• Annular Linear Induction Pump (ALIP) – Electromagnetic pump / No moving parts – Two Pumps manufactured – Both were tested in the ALIP Test Circuit at MSFC
7
ALIP installed at MSFC
National Aeronautics and Space Administration
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Sub-System Testing at MSFC
• Core simulator demonstrated to 50 kWt
• FSP and TDU ALIP pump curves have been generated • Flow resistance curves have been generated
– Showed that larger of the two ALIPs must be used during TDU testing
• All components tested at nominal and maximum temperatures
8
National Aeronautics and Space Administration
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Stirling Power Conversion Units • Two 6 kW Stirling convertors have been fabricated and tested by Sunpower
– Convertor 1 was fabricated in Fall of 2011 – Convertor 2 was fabricated in Spring of 2012
9
• Tested as individual convertors - Convertor 1 reached full power in Dec 2011 - Convertor 2 reached full power in July 2012
• Combined into a 12 kW PCU April 2013 • Electrically heated test finished in Late 2014. • NaK heat exchanger fabrication delayed
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Radiator Testing
10
Material Innovation 2nd Gen RDU (2009)
GRC Affordable Radiator (2013-2014)
Advanced Cooling Technologies Composite Radiator (2011)
Phase II SBIR with ACT to deliver 6 radiator panels using affordable design approach
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Heat Rejection Sub-System Testing
• Completed in January 2013 – Demonstrated water pump
compatibility in thermal vacuum – Verified start-up, shutdown, and
emergency drain procedures – Pump performance data has
been incorporated into TDU system models
11
National Aeronautics and Space Administration
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RxSim Subsystem Test Hot NaK Preparation / Preliminary Work
• NaK Storage • Fill/Drain • Steam Cleaning • NaK and Caustic Disposal • Safety Permit • Operating Procedures
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RxSim Subsystem Test NaK Testing
13
• Operated through full operating range • Verified component performance • Validated subsystem models
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TDU System Model Validation
14
300
400
500
600
700
800
900
0 1000 2000 3000 4000 5000 6000 7000 8000 9000
Tem
pera
ture
(K)
Time (s)
Model Core NaK Temp
Model ALIP NaK Temp
ALIP NaK Temperature
Core NaK Temperature
0
500
1000
1500
2000
2500
0
500
1000
1500
2000
2500
3000
3500
0 1000 2000 3000 4000 5000 6000 7000 8000 9000
Mas
s flo
w (g
/s)
Pow
er (W
)
Time (s)
ALIP-POW (W)
Model ALIP Power
EM Flow
Model Mass Flow
650670690710730750770790810830
0 1000 2000 3000 4000 5000
Tem
pera
ture
(K)
Time (s)
Cool Down
ALIP Inlet
ALIP OUTLET
ALIP OUTLET
ALIP Inlet
Core Outlet
Core Inlet
Core NaK Temp
Model ALIP NaK Temp
Model Core NaK Temp
• Verify internal Core Sim Temps • Verify Flow and Pump Power • Verify Thermal Losses • Verify Steady-State Operating
Conditions and Transient Response.
National Aeronautics and Space Administration
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System Level TDU Test Status Fabrication/Assembly Delay
• Complicated braze geometry was difficult to fabricate • New NaK Heater Head Design Being Fabricated
– Material changes eliminated difficult brazes – Final engine assembly scheduled for May 2015
15
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Conclusion
16
Component Testing Complete
Sub-System Testing Complete
TDU Testing scheduled for June 2015