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DOE OSTI2024

Integration and Optimization of a Waste Heat Driven Organic Rankine Cycle for Power Generation in Wastewater Treatment Plants

The study focuses on achieving energy self-sufficiency in Wastewater Treatment Plants by proposing a comprehensive model for integrating, sizing, and optimizing an Organic Rankine Cycle system. The Organic Rankine Cycle system is designed to utilize waste heat from the gensets at As Samra Wastewater Treatment Plant in Jordan, where it will contribute to the overall electrical energy supply of the plant. Real data from As Samra Wastewater Treatment Plant is used to model and calculate the available waste heat using TRNSYS® software. The Organic Rankine Cycle model is then developed using ASPEN PLUS® software to explore the impact of operational parameters and determine their optimal values for maximizing the plant's energy profile. An economic analysis is conducted to assess the feasibility of the proposed model, considering system components, installation, operation, and maintenance costs. To optimize the Organic Rankine Cycle system, the study employs the Multi-Output Support Vector Regression technique to capture nonlinear relationships between independent variables (fluid type, turbine inlet pressure, turbine inlet temperature, turbine outlet pressure, and mass flow rate) and dependent variables (pump power input, waste heat input, and turbine specific work). The Osprey optimization algorithm is used to address the multi-objective optimization problem, with the proposed Pareto-based Osprey Optimization Algorithm and the Multi-Objective Particle Swarm Optimization technique being employed to evaluate critical performance and economic parameters such as system thermal efficiency, net power output, and the levelized cost of electricity. The results of the optimization strategies indicate that the M-SVR model's prediction accuracy is significantly improved after parameter optimization, with the model returning high R 2 and low Mean Square Error values of 0.991 and 0.00216, respectively. The Pareto-Based Osprey Optimization Algorithm optimizer identifies the best working fluid as Isobutane/Isopentane in a ratio of 66:34, with optimal turbine inlet pressure and temperature of 15 bars and 218 °C, respectively. In conclusion, the Organic Rankine Cycle model at these optimal conditions achieves a cycle efficiency of 19.93% and an Levelized Cost of Electricity value of 0.0353 USD/kWh.

32 ENERGY CONSERVATION, CONSUMPTION, AND UTILIZATI↗

NASA NTRS2000

NEA Multi-Chamber Sample Return Container with Hermetic Sealing

A sample return container is being developed by Honeybee Robotics to receive samples from a derivative of the Champollion/ST4 Sample Acquisition and Transfer Mechanism or other samplers such as the 'Touch and Go' Surface Sampler (TGSS), and then hermetically seal the samples for a sample return mission. The container is enclosed in a phase change material (PCM) chamber to prevent phase change during return and re-entry to earth. This container is designed to operate passively with no motors and actuators. Using the rotation axis of the TGSS sampler for interfacing, transferring and sealing samples, the container consumes no electrical power and therefore minimizes sample temperature change. The circular container houses multiple isolated canisters, which will be sealed individually for samples acquired from different sites or depths. The TGSS based sampler indexes each canister to the sample transfer position, below the index interface for sample transfer. After sample transfer is completed, the sampler indexes a seal carrier, which lines up seals with the openings of the canisters. The sampler moves to the sealing interface and seals the sample canisters one by one. The sealing interface can be designed to work with C-seals, knife edge seals and cup seals. This sample return container is being developed by Honeybee Robotics in collaboration with the JPL Exploration Technology program. A breadboard system of the sample return container has been recently completed and tested. Additional information is contained in the original extended abstract.

Rafeek, Shaheed↗

DOE OSTI2012

Performance of Spring Chinook Salmon Reared in Acclimation Ponds for Two and Four Months before Release

Abstract Seasonal temperature cues may play an important role in the parr–smolt transformation of Pacific salmon Oncorhynchus spp., but salmon reared in groundwater-supplied hatcheries with seasonally stable water temperatures do not experience these cues. In this study, conducted over six release years, hatchery spring Chinook salmon O. tshawytscha that were initially reared in a groundwater-supplied hatchery were transferred to acclimation ponds supplied with surface water either in November (November transfer [NT]) or January (January transfer [JT]) for rearing at ambient water temperatures prior to release into the Umatilla River, Oregon, in early March. After stream release, we monitored out-migration travel times and survival to John Day Dam (JDD) by using passive integrated transponder tags in a subsample of each release group. Across all release groups, median travel time was slower for NT groups (51 d) than for JT groups (46 d); significant differences were observed in five of six release years. Average survival probabilities were 15% higher for NT groups than for JT groups, although this difference was not significant. We used recoveries of coded wire tags to estimate smolt-to-adult survival (SAS) and straying for NT and JT groups. Average SAS over the study was 27% higher for NT groups (0.76%) than for JT groups (0.60%), but straying was minimal for both types of release group. We found no significant linear relationship between SAS and travel time or survival to JDD. Adult returns of NT groups had a slightly older age distribution than those of JT groups. Our results suggest that for salmon juveniles reared in groundwater-supplied hatcheries, providing an overwinter period of exposure to ambient water temperatures should optimize postrelease survival. We also discuss some risks and benefits to winter rearing in acclimation ponds for managers that are considering this approach.

Clarke, Lance R.↗

DOE OSTI2018

Implementation of a 1-2 keV point-projection x-ray spectrometer on the National Ignition Facility

A point-projection soft X-ray Opacity Spectrometer (OpSpec) has been implemented to measure X-ray spectra from ~1 to 2 keV on the National Ignition Facility (NIF). Measurement of such soft X-rays with open-aperture point-projection detectors is challenging because only very thin filters may be used to shield the detector from the hostile environment. OpSpec diffracts X-rays from 540 to 2100 eV off a potassium (or rubidium) acid phthalate (KAP or RbAP) crystal onto either image plates or, most recently, X-ray films. A “sacrificial front filter” strategy is used to prevent crystal damage, while 2 or 3 rear filters protect the data. Since May 2017, OpSpec has been recording X-ray transmission data for iron-magnesium plasmas on the NIF, at “Anchor 1” plasma conditions (temperature ~150 eV, density ~7 × 10 21 e - /cm 3 ). Upgrades improved OpSpec’s performance on 6 NIF shots in August and December 2017, with reduced backgrounds and 100% data return using filter stacks as thin as 2.9 μm (total). We conclude that photometric noise is beginning to meet requirements, and further work will reduce systematic errors.

47 OTHER INSTRUMENTATION↗

NASA NTRS1990

Containerless experiments in fluid physics in microgravity

The physical phenomena associated with the behavior of liquid samples freely suspended in low gravity must be thoroughly understood prior to undertaking detailed scientific studies of the materials under scrutiny. The characteristics of molten specimens under the action of containerless positioning stresses must be identified and separated from the specific phenomena relating to the absence of an overwhelming gravitational field. The strategy designed to optimize the scientific return of reliable experimental data from infrequent microgravity investigations should include the gradual and logical phasing of more sophisticated studies building on the accumulated results from previous flight experiments. Lower temperature fluid physics experiments using model materials can provide a great deal of information that can be useful in analyzing the behavior of high temperature melts. The phasing of the experimental capabilities should, therefore, also include a gradual build-up of more intricate and specialized diagnostic instrumentation and environmental control and monitoring capabilities. Basic physical investigations should also be distinguished from specific materials technology issues. The latter investigations require very specific high temperature (and high vacuum) devices that must be thoroughly mastered on the ground prior to implementing them in space.

Trinh, E. H.↗

NASA NTRS1993

Experimental Determination of in Situ Utilization of Lunar Regolith for Thermal Energy Storage

A Lunar Thermal Energy from Regolith (LUTHER) experiment has been designed and fabricated at the NASA Lewis Research Center to determine the feasibility of using lunar soil as thermal energy storage media. The experimental apparatus includes an alumina ceramic canister (25.4 cm diameter by 45.7 cm length) which contains simulated lunar regolith, a heater (either radiative or conductive), 9 heat shields, a heat transfer cold jacket, and 19 type B platinum rhodium thermocouples. The simulated lunar regolith is a basalt, mined and processed by the University of Minnesota, that closely resembles the lunar basalt returned to earth by the Apollo missions. The experiment will test the effects of vacuum, particle size, and density on the thermophysical properties of the regolith. The properties include melt temperature (range), specific heat, thermal conductivity, and latent heat of storage. Two separate tests, using two different heaters, will be performed to study the effect of heating the system using radiative and conductive heat transfer. The physical characteristics of the melt pattern, material compatibility of the molten regolith, and the volatile gas emission will be investigated by heating a portion of the lunar regolith to its melting temperature (1435 K) in a 10(exp -4) pascal vacuum chamber, equipped with a gas spectrum analyzer. A finite differencing SINDA model was developed at NASA Lewis Research Center to predict the performance of the LUTHER experiment. The analytical results of the code will be compared with the experimental data generated by the LUTHER experiment. The code will predict the effects of vacuum, particle size, and density has on the heat transfer to the simulated regolith.

Richter, Scott W.↗

NASA NTRS1993

Reentry systems: Material technology needs

The material technology needs are: (1) lightweight and durable rigid insulating and higher temperature flexible materials; and (2) inspection, repair, producibility, and maintainability of refractory composites. The direction of efforts are: (1) funding base is relatively small for future years; (2) to minimize returns, collaborative programs appear to be practical; and (3) SSD's approach is to implement NASA developed technology.

Ehret, Richard Michael↗

NASA NTRS2002

International Space Station Nickel-Hydrogen Battery Startup and Initial Performance

The Battery Orbital Replacement Unit (ORU) was designed to meet the following requirements: a 6.5-year design life, 38,000 charge/discharge Low Earth Orbit cycles, 81-Amp-hr nameplate capacity, 4 kWh nominal storage capacity, contingency orbit capability, an operating temperature of 5 +/- 5 C standard orbit and 5+5/-10 C contingency orbit, a non-operating temperature of -25 to +30 C, a five-year Mean Time between failure, an on-orbit replacement using ISS robotic interface, and one launch to orbit and one return to ground. The ISS electrical power system is successfully maintaining power for all on-board loads. ISS Eclipse power is currently supplied by six Ni-H2 batteries (12 ORUs), which are operating nominally.

Dalton, Penni↗

NASA NTRS2014

The Komplast Experiment: Space Environmental Effects after 12 Years in LEO (and Counting)

The Komplast materials experiment was designed by the Khrunichev Space Center, together with other Russian scientific institutes, and has been carried out by Mission Control Moscow since 1998. The purpose is to study the effect of the low earth orbit (LEO) environment on exposed samples of various spacecraft materials. The Komplast experiment began with the launch of the first International Space Station (ISS) module on November 20, 1998. Two of eight experiment panels were retrieved during Russian extravehicular activity in February 2011 after 12 years of LEO exposure, and were subsequently returned to Earth by Space Shuttle "Discovery" on the STS-133/ULF-5 mission. The retrieved panels contained an experiment to detect micrometeoroid and orbital debris (MMOD) impacts, radiation sensors, a temperature sensor, several pieces of electrical cable, both carbon composite and adhesive-bonded samples, and many samples made from elastomeric and fluoroplastic materials. Our investigation is complete and a summary of the results obtained from this uniquely long-duration exposure experiment will be presented.

Shaevich, S. K.↗

NASA NTRS2014

The Komplast Experiment: Space Environmental Effects after 12 Years in LEO (and Counting)

Shaevich, Sergei K.↗

NASA NTRS2014

The Komplast Experiment: Space Environmental Effects after 12 Years in LEO (and Counting)

Golden, J. L.↗

NASA NTRS2015

Laboratory Studies of Cometary Materials - Continuity Between Asteroid and Comet

Laboratory analysis of cometary samples have been enabled by collection of cometary dust in the stratosphere by high altitude aircraft and by the direct sampling of the comet Wild‐2 coma by the NASA Stardust spacecraft. Cometary materials are composed of a complex assemblage of highly primitive, unprocessed interstellar and primordial solar system materials as well as a variety of high temperature phases that must have condensed in the inner regions of the protoplanetary disk. These findings support and contradict conclusions of comet properties based solely on astronomical observations. These sample return missions have instead shown that there is a continuity of properties between comets and asteroids, where both types of materials show evidence for primitive and processed materials. Furthermore, these findings underscore the importance and value of direct sample return. There will be great value in comparing the findings of the Stardust cometary coma sample return mission with those of future asteroid surface sample returns OSIRIS‐REx and Hayabusa II as well as future comet nucleus sample returns.

Messenger, Scott↗

NASA NTRS2020

Breakthrough Materials for Space Applications Workshop

In the course of its 60 year history, the National Aeronautics and Space Administration (NASA) has blazed trails in the development and advancement of aerospace materials and the transition of these advancements to industry. The Agency has overseen the infusion of new high-performance materials into a diverse array of mission applications, including aeronautics, planetary science, and human spaceflight. The next generation of demanding exploration missions, including a return to the lunar surface with humans in the 2020s, will present new and unprecedented material challenges. Selecting or developing materials to survive the environments of launch and the high temperatures present in propulsion systems, operate in a microgravity and/or a vacuum environment (which includes exposure to radiation), and/or survive years on a planetary surface is an immense challenge. In addition to functioning in their intended use environment, materials for space must also possess extremely high-performance characteristics. The anecdotal Von Braun quote “space is weightlifting” reminds us of the need to minimize the mass of a space system while still meeting safety margins. The cost of launching a kg to orbit is estimated currently at $10,000; barring a drastic reduction in launch costs, lightweight and high-strength materials will remain the most sought-after spaceflight materials for the foreseeable future. Other primary considerations for materials in spaceflight applications include affordability, compatibility with other systems and materials, and manufacturability. The emergence of new advanced manufacturing processes such as friction stir welding and additive manufacturing have revolutionized the aerospace industry in recent years. Additive manufacturing in particular allows for rapid fabrication of components and greater design freedom. With the advent of these new processes, however, comes the need to develop new specifications, process control approaches (including material modeling), testing, and nondestructive evaluation techniques to ensure that parts meet the stringent functional requirements for spaceflight.

Prater, T.↗

DOE OSTI2016

Effect of pH on hydrogen pick-up and corrosion in zircaloy-4

Thermal Desorption Spectroscopy (TDS) has been used to investigate the hydrogen pick-up behaviour in different samples of Zircaloy-4. This includes as-received, cold rolled, hydrogen charged, and autoclave-oxidised in pure water and at an elevated pH (with 50% deuterated water) compared to commercial reactors. A characteristic desorption peak for hydrogen has been found at about 650 Celsius degrees, which is theorised to come from hydrides. Cold rolled samples show the same general shape spectrum as the as-received samples, with more hydrogen detected per unit volume of sample. This suggests more hydrogen is in trapping sites or outward diffusion paths are facilitated by dislocations, since no more hydrogen has been added. The peak broadens towards higher temperature, which indicates that additional dislocations could provide trapping sites with a slightly higher energy than the average in the as-received samples. The hydrogen charged samples form a hydride rim, which contains much more hydrogen than the as-received samples. The peak broadens but on average does not shift. The surface oxide, when present, acts as a barrier to the desorption of hydrogen, until the temperature rises enough for the oxygen to migrate into the bulk. The oxide itself only contains a small amount of hydrogen, as is evidenced when the oxide layer is removed, whereupon the desorption peak returns to the characteristic shape seen in as-received samples. Samples oxidised in pure water exhibit a slightly higher oxidation rate, and pass through kinetic transition much earlier than samples exposed to an elevated pH. Before transition pH has little effect on the hydrogen pick-up. After transition the hydrogen pick-up is much higher in pure water, which implies that the H{sup +} concentration in the environment affects hydrogen pickup at this stage. The elevated pH samples showed peaks for D-H and D{sub 2}, which follow the H{sub 2} peaks. The hydrogen content in these samples increases at around 70% of the time to the first transition. This may correlate with development of through-thickness percolation paths, which could lead to the pH inside cracks being modified to a lower value, increasing the availability of H{sup +} ions. (authors)

36 MATERIALS SCIENCE↗

NASA NTRS2011

Status of NASA In-Space Propulsion Technologies and Their Infusion Potential

Since 2001, the In-Space Propulsion Technology (ISPT) program has been developing in-space propulsion technologies that will enable or enhance NASA robotic science missions. These in-space propulsion technologies have broad applicability to future competed Discovery and New Frontiers mission solicitations, and are potentially enabling for future NASA flagship and sample return missions currently being considered. This paper provides status of the technology development of several in-space propulsion technologies that are ready for infusion into future missions. The technologies that are ready for flight infusion are: 1) the high-temperature Advanced Material Bipropellant Rocket (AMBR) engine providing higher performance; 2) NASA s Evolutionary Xenon Thruster (NEXT) ion propulsion system, a 0.6-7 kW throttle-able gridded ion system; and 3) Aerocapture technology development with investments in a family of thermal protection system (TPS) materials and structures; guidance, navigation, and control (GN&C) models of blunt-body rigid aeroshells; and aerothermal effect models. Two component technologies that will be ready for flight infusion in FY12/13 are 1) Advanced Xenon Flow Control System, and 2) ultra-lightweight propellant tank technology advancements and their infusion potential will be also discussed. The paper will also describe the ISPT project s future focus on propulsion for sample return missions: 1) Mars Ascent Vehicles (MAV); 2) multi-mission technologies for Earth Entry Vehicles (MMEEV) needed for sample return missions from many different destinations; and 3) electric propulsion for sample return and low cost missions. These technologies are more vehicle-focused, and present a different set of technology infusion challenges. Systems/Mission Analysis focused on developing tools and assessing the application of propulsion technologies to a wide variety of mission concepts.

Anderson, David↗

DOE OSTI2015

Interacting supernovae and supernova impostors: Evidence of incoming supernova explosions?

Violent eruptions, and consequently major mass loss, are a common feature of the so–called Luminous Blue Variable (LBV) stars. During major eruptive episodes LBVs mimic the behavior of real type IIn supernovae (SNe), showing comparable radiated energy and similar spectroscopic properties. For this reason these events are frequently labelled as SN impostors. Type IIn SN spectra are characterized by the presence of prominent narrow Balmer lines in emission. In most cases, SNe IIn arise from massive stars (M>8{sub ⊙}) exploding in a dense H–rich circumstellar medium (CSM), produced by progenitor’s mass loss prior to the SN explosion. Although the mechanisms triggering these eruptions are still unknown, recently we had direct proofs of the connection between very massive stars, their eruptions and ejecta-CSM interacting SNe. SNe 2006jc, 2010mc, 2011ht and the controversial SN 2009ip are famous cases in which we observed the explosion of the star months to years after major outbursts. In this context, the case of a recent transient event, LSQ13zm, is extremely interesting since we observed an outburst just ∼3 weeks before the terminal SN explosion. All of this may suggest that SN impostors occasionally herald true SN explosions. Nonetheless, there are several cases where major eruptions are followed by a quiescent phase in the LBV life. The impostor SN 2007sv is one of these cases, since it showed a single outburst event. Its photometric (a relatively faint absolute magnitude at the maximum) and spectroscopic properties (low velocity and temperature of the ejecta, and the absence of the typical elements produced in the explosive nucleosynthesis) strongly suggest that SN 2007sv was the giant eruption of an LBV, which has then returned in a quiescent stage.

79 ASTRONOMY AND ASTROPHYSICS↗

NASA NTRS1971

The Viking mission to Mars.

In 1975 the National Aeronautics and Space Administration will launch two unmanned scientific payloads to make soft landings on Mars in 1976. They will be placed in orbit around the planet to perform a reconnaissance before landing. The spacecraft will be separated into an orbiter, which is sent to the surface. During the entry into the Martian atmosphere, Viking will make measurements of the composition and atmospheric structure. After landing, two cameras will be used to visually characterize the site. A device will be deployed to obtain a sample of the Mars surface, which will be returned to the lander for biological tests and for chemical analysis. The atmosphere at the surface will be chemically analyzed as well as the wind velocity, the humidity, and changes in temperature and pressure.

Soffen, G. A.↗

NASA NTRS1974

Exoelectronic emission of particles of lunar surface material

A secondary electron multiplier was used to study the thermostimulated exoelectronic emission of particles of lunar surface material returned by the Soviet Luna 16 automatic station. The natural exoemission from fragments of slag, glass, anorthosite, and a metallic particle was recorded in the isochronic and isothermal thermostimulation regimes. The temperature of emission onset depended on the type of regolith fragment. For the first three particles the isothermal drop in emission is described by first-order kinetic equations. For the anorthosite fragment, exoemission at constant temperature is characterized by a symmetric curve with a maximum. These data indicate the presence of active surface defects, whose nature can be due to the prehistory of the particles.

Mints, R. I.↗