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  • 1
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    Round Trip Energy Efficiency of NASA Glenn Regenerative Fuel Cell System (2006)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: NASA Glenn Research Center (GRC) has recently demonstrated a Polymer Electrolyte Membrane (PEM) based hydrogen/oxygen regenerative fuel cell system (RFCS) that operated for a charge/discharge cycle with round trip efficiency (RTE) greater than 50 percent. The regenerative fuel cell system (RFCS) demonstrated closed loop energy storage over a pressure range of 90 to 190 psig. In charge mode, a constant electrical power profile of 7.1 kWe was absorbed by the RFCS and stored as pressurized hydrogen and oxygen gas. In discharge mode, the system delivered 3 to 4 kWe of electrical power along with product water. Fuel cell and electrolyzer power profiles and polarization performance are documented in this paper. Individual cell performance and the variation of cell voltages within the electrochemical stacks are also reported. Fuel cell efficiency, electrolyzer efficiency, and the system RTE were calculated from the test data and are included below.
    Keywords: Energy Production and Conversion
    Type: NASA/TM-2006-214054 , E-15411 , NHA Annual Hydrogen Conference 2006; Mar 12, 2006 - Mar 16, 2006; Long Beach, CA; United States
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  • 2
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    Test of Hydrogen-Oxygen PEM Fuel Cell Stack at NASA Glenn Research Center (2003)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper describes performance characterization tests of a 64 cell hydrogen oxygen PEM fuel cell stack at NASA Glenn Research Center in February 2003. The tests were part of NASA's ongoing effort to develop a regenerative fuel cell for aerospace energy storage applications. The purpose of the tests was to verify capability of this stack to operate within a regenerative fuel cell, and to compare performance with earlier test results recorded by the stack developer. Test results obtained include polarization performance of the stack at 50 and 100 psig system pressure, and a steady state endurance run at 100 psig. A maximum power output of 4.8 kWe was observed during polarization runs, and the stack sustained a steady power output of 4.0 kWe during the endurance run. The performance data obtained from these tests compare reasonably close to the stack developer's results although some additional spread between best to worst performing cell voltages was observed. Throughout the tests, the stack demonstrated the consistent performance and repeatable behavior required for regenerative fuel cell operation.
    Keywords: Energy Production and Conversion
    Type: NASA/TM-2003-212374 , E-13950 , NAS 1.15:212374 , AIAA Paper 2003-6123 , First International Energy Conversion Engineering Conference; Aug 17, 2003 - Aug 21, 2003; Portsmouth, VA; United States
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  • 3
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    Regenerative Fuel Cell Test Rig at Glenn Research Center (2003)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The regenerative fuel cell development effort at Glenn Research Center (GRC) involves the integration of a dedicated fuel cell and electrolyzer into an energy storage system test rig. The test rig consists of a fuel cell stack, an electrolysis stack, cooling pumps, a water transfer pump, gas recirculation pumps, phase separators, storage tanks for oxygen (O2) and hydrogen (H2), heat exchangers, isolation valves, pressure regulators, interconnecting tubing, nitrogen purge provisions, and instrumentation for control and monitoring purposes. The regenerative fuel cell (RFC) thus formed is a completely closed system which is capable of autonomous cyclic operation. The test rig provides direct current (DC) load and DC power supply to simulate power consumption and solar power input. In addition, chillers are used as the heat sink to dissipate the waste heat from the electrochemical stack operation. Various vents and nitrogen (N2) sources are included in case inert purging is necessary to safe the RFC test rig.
    Keywords: Energy Production and Conversion
    Type: NASA/TM-2003-212375 , E-13951 , NAS 1.15:212375 , AIAA Paper 2003-5942 , First International Energy Conversion Engineering Conference; Aug 17, 2003 - Aug 21, 2003; Portsmouth, VA; United States
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  • 4
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    Investigations of Physical Processes in Microgravity Relevant to Space Electrochemical Power Systems (2015)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: NASA has performed physical science microgravity flight experiments in the areas of combustion science, fluid physics, material science and fundamental physics research on the International Space Station (ISS) since 2001. The orbital conditions on the ISS provide an environment where gravity driven phenomena, such as buoyant convection, are nearly negligible. Gravity strongly affects fluid behavior by creating forces that drive motion, shape phase boundaries and compress gases. The need for a better understanding of fluid physics has created a vigorous, multidisciplinary research community whose ongoing vitality is marked by the continuous emergence of new fields in both basic and applied science. In particular, the low-gravity environment offers a unique opportunity for the study of fluid physics and transport phenomena that are very relevant to management of fluid - gas separations in fuel cell and electrolysis systems. Experiments conducted in space have yielded rich results. These results provided valuable insights into fundamental fluid and gas phase behavior that apply to space environments and could not be observed in Earth-based labs. As an example, recent capillary flow results have discovered both an unexpected sensitivity to symmetric geometries associated with fluid container shape, and identified key regime maps for design of corner or wedge-shaped passive gas-liquid phase separators. In this presentation we will also briefly review some of physical science related to flight experiments, such as boiling, that have applicability to electrochemical systems, along with ground-based (drop tower, low gravity aircraft) microgravity electrochemical research. These same buoyancy and interfacial phenomena effects will apply to electrochemical power and energy storage systems that perform two-phase separation, such as water-oxygen separation in life support electrolysis, and primary space power generation devices such as passive primary fuel cell.
    Keywords: Spacecraft Propulsion and Power
    Type: GRC-E-DAA-TN26570 , International Symposium on Physical Sciences (ISPS-6); Sep 14, 2015 - Sep 18, 2015; Kyoto,; Japan
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  • 5
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    High Performance Fuel Cell and Electrolyzer Membrane Electrode Assemblies (MEAs) for Space Energy Storage Systems (2012)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Regenerative fuel cells provide a pathway to energy storage system development that are game changers for NASA missions. The fuel cell/ electrolysis MEA performance requirements 0.92 V/ 1.44 V at 200 mA/cm2 can be met. Fuel Cell MEAs have been incorporated into advanced NFT stacks. Electrolyzer stack development in progress. Fuel Cell MEA performance is a strong function of membrane selection, membrane selection will be driven by durability requirements. Electrolyzer MEA performance is catalysts driven, catalyst selection will be driven by durability requirements. Round Trip Efficiency, based on a cell performance, is approximately 65%.
    Keywords: Spacecraft Propulsion and Power
    Type: 2012 Space Power Workshop; Apr 17, 2012 - Apr 19, 2012; Manhattan Beach, CA; United States
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  • 6
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    The Advantages of Non-Flow-Through Fuel Cell Power Systems for Aerospace Applications (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: NASA has been developing proton-exchange-membrane (PEM) fuel cell power systems for the past decade, as an upgraded technology to the alkaline fuel cells which presently provide power for the Shuttle Orbiter. All fuel cell power systems consist of one or more fuel cell stacks in combination with appropriate balance-of-plant hardware. Traditional PEM fuel cells are characterized as flow-through, in which recirculating reactant streams remove product water from the fuel cell stack. NASA recently embarked on the development of non-flow-through fuel cell systems, in which reactants are dead-ended into the fuel cell stack and product water is removed by internal wicks. This simplifies the fuel cell power system by eliminating the need for pumps to provide reactant circulation, and mechanical water separators to remove the product water from the recirculating reactant streams. By eliminating these mechanical components, the resulting fuel cell power system has lower mass, volume, and parasitic power requirements, along with higher reliability and longer life. These improved non-flow-through fuel cell power systems therefore offer significant advantages for many aerospace applications.
    Keywords: Spacecraft Propulsion and Power
    Type: E-17776 , 2011 Next-Generation Suborbital Researchers Conference; Feb 28, 2011 - Mar 02, 2011; Orlando, FL; United States
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  • 7
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    Photovoltaic Power System and Power Distribution Demonstration for the Desert RATS Program (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: A stand alone, mobile photovoltaic power system along with a cable deployment system was designed and constructed to take part in the Desert Research And Technology Studies (RATS) lunar surface human interaction evaluation program at Cinder Lake, Arizona. The power system consisted of a photovoltaic array/battery system. It is capable of providing 1 kW of electrical power. The system outputs were 48 V DC, 110 V AC, and 220 V AC. A cable reel with 200 m of power cable was used to provide power from the trailer to a remote location. The cable reel was installed on a small trailer. The reel was powered to provide low to no tension deployment of the cable. The cable was connected to the 220 V AC output of the power system trailer. The power was then converted back to 110 V AC on the cable deployment trailer for use at the remote site. The Scout lunar rover demonstration vehicle was used to tow the cable trailer and deploy the power cable. This deployment was performed under a number of operational scenarios, manned operation, remote operation and tele-robotically. Once deployed, the cable was used to provide power, from the power system trailer, to run various operational tasks at the remote location.
    Keywords: Electronics and Electrical Engineering
    Type: NASA/TM-2012-217284 , E-18039
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  • 8
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    Thermal System Sizing Comparison of a PEM and Solid Oxide Fuel Cell Systems on Mars (2019)
    In:  CASI
    Details
    Publication Date: 2019-07-20
    Description: Power production is a key aspect to any Mars mission. One method for providing power throughout the day/night cycle, or to satisfy short-duration high-output power needs, is to utilize a regenerative fuel cell system for providing energy storage and nighttime or supplemental power. This study compares the total system mass for two types of fuel cell systems, proton exchange membrane (PEM) and solid oxide (SO), sized to provide 10 kW of electrical output power in the Mars environment. Two operating locations were examined; one near the equator at 4 S latitude and one the higher northern latitude of 48N. The systems were sized to operate throughout the year at these locations, where the radiator was sized for the worst-case warm condition and the insulation was sized for the worst-case cold condition. Using the selected system parameters, the results for both latitudes showed that the lightest system was the SO fuel cell with a PEM electrolyzer. This was mainly due to the higher operational temperature of the SO system enabled a significantly smaller radiator mass compared to that of the PEM fuel cell system. However, there was a significant difference in mass for the PEM system when operated near the equator as compared to the higher northern latitude. For the 10-kW output system this difference in mass was just under 100 kg.
    Keywords: Spacecraft Propulsion and Power
    Type: GRC-E-DAA-TN62192 , NASA/TM-2019-220019
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  • 9
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    Fuel Cell Research and Development for Earth and Space Applications (2018)
    In:  CASI
    Details
    Publication Date: 2019-07-20
    Description: This presentation provides a high-level summary of recent fuel cell and electrolysis development activities at NASA for both aeronautic and aerospace applications. It highlights advances in PEM and solid oxide technologies implemented as primary fuel cells. It also includes the results of recent Lunar energy storage trade studies evaluating the feasibility of regenerative fuel cell energy storage.
    Keywords: Spacecraft Propulsion and Power; Energy Production and Conversion
    Type: GRC-E-DAA-TN59040
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  • 10
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    Energy Storage for Lunar Surface Exploration (2018)
    In:  CASI
    Details
    Publication Date: 2019-07-20
    Description: This paper presents the updated results of a previous NASA study funded under the Advanced Exploration Systems (AES) Modular Power Systems (AMPS) project. This work focuses on generating high-level system sizing relationships for two lunar surface locations that serve as bounding conditions for most other locations. Four critical parameters are considered to provide sizing data: specific energy, energy density, specific power, and power density. Given the energy storage requirements or customer power demand for a lunar mission location, the data presented in this paper provides a method to determine the critical parameter values of a Regenerative Fuel Cell (RFC) system in order to perform high-level mission architecture trades.
    Keywords: Lunar and Planetary Science and Exploration
    Type: GRC-E-DAA-TN60376 , AIAA Space and Astronautics Forum (SPACE Forum 2018); Sep 17, 2018 - Sep 19, 2018; Orlando, FL; United States
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