CODIFICATION OF FIBER REINFORCED COMPOSITE PIPING

The goal of the overall project is to successfully adapt spoolable FRP currently used in the oil industry for use in hydrogen pipelines. The use of FRP materials for hydrogen service will rely on the demonstrated compatibility of these materials for pipeline service environments and operating conditions. The ability of the polymer piping to withstand degradation while in service, and development of the tools and data required for life management are imperative for successful implementation of these materials for hydrogen pipeline. The information and data provided in this report provides the technical basis for the codification for fiber reinforced piping (FRP) for hydrogen service. The DOE has invested in the evaluation of FRP for the delivery for gaseous hydrogen to support the development of a hydrogen infrastructure. The codification plan calls for detailed investigation of the following areas: System design and applicable codes and standards; Service degradation of FRP; Flaw tolerance and flaw detection; Integrity management plan; Leak detection and operational controls evaluation; Repair evaluation. The FRP codification process started with commercially available products that had extensive use in the oil and gas industry. These products have been evaluated to assure that sufficient structural integrity is available for a gaseous hydrogen environment

Extended performance solar electric propulsion thrust system study. Volume 1: Executive summary

Several thrust system design concepts were evaluated and compared using the specifications of the most advanced 30 cm engineering model thruster as the technology base. The extensions in thruster performance required for the Halley's comet mission were defined and alternative thrust system concepts were designed. Confirmation testing and analysis of thruster and power-processing components were performed, and the feasibility of satisfying extended performance requirements was verified. A baseline design was selected from the alternatives considered, and the design analysis and documentation were refined. A program development plan was formulated that outlines the work structure considered necessary for developing, qualifying, and fabricating the flight hardware for the baseline thrust system within the time frame of a project to rendezvous with Halley's comet. An assessment was made of the costs and risks associated with a baseline thrust system as provided to the mission project under this plan. Critical procurements and interfaces were identified and defined. Results are presented

Liner characterisation and leak detection using electrical resistivity techniques

The resistivity of soil ranges from 7-15 Ωm for Leachate #1 to 20-50 Ωm for Leachate #2. The resistivity decreases with an increase in the proximity to the leak point. Furthermore, the resistivity values obtained with water were nearly 10 times the values observed with landfill leachate as the leaching liquid. Based on the resistivity profiles of soil as observed at different time intervals, the method is found to be effective in determining leakages in the liner. The test results have also been presented for the leakage of Bayer liquor obtained from aluminium manufacturing company in Western Australia. The resistivity values were found to range from 1 to 3 Ωm. A similar trend in the resistivity values was found with distance/depth for Bayer liquor contamination as observed with other leachates. Therefore, the installation of this innovative detection system below the liners in the aluminium industry can enable the effective monitoring of the lining systems and in case of failures, to take timely action for hazard mitigation. Finally, based on the leak detection test results, empirical correlations and analytical modelling have been developed and presented for the relationship between resistivity, leakage duration and distance/depth. These can be used to predict the velocity of flow of leachate at any point within a liner base soil specimen. A numerical model for the seepage analysis of the leak detection test has been developed using the SEEP/W software. The flow velocity obtained from this model has then been used in conjunction with the new correlations to generate resistivity profiles for any specific soil type and leachate, in the leak detection test. Any other suitable seepage analysis software (e.g. GGU-SEEP, GGU-SS-FLOW2D, GGU-SSFLOW3D, etc.) can be used by practicing engineers to predict resistivity, and therefore, to design a suitable lining system for waste containment facilities. This research work is particularly useful in generating awareness about the state of landfilling and will help various environmental protection agencies in making informed decisions for the development of rules and regulations to govern landfills. It is demonstrated that this system can be used to effectively detect and locate the liner leaks by simulating the field condition. The newly developed innovative diagnostic technique can be useful in designing the monitoring systems for waste storage and handling facilities, subbase contamination detection, liner leak detection, development and placement of sensors, soil and corrosion studies and so on, in Australia as well as worldwide

Spherical Cryogenic Hydrogen Tank Preliminary Design Trade Studies

A structural analysis, sizing optimization, and weight prediction study was performed by Collier Research Corporation and NASA Glenn on a spherical cryogenic hydrogen tank. The tank consisted of an inner and outer wall separated by a vacuum for thermal insulation purposes. HyperSizer (Collier Research and Development Corporation), a commercial automated structural analysis and sizing software package was used to design the lightest feasible tank for a given overall size and thermomechanical loading environment. Weight trade studies were completed for different panel concepts and metallic and composite material systems. Extensive failure analyses were performed for each combination of dimensional variables, materials, and layups to establish the structural integrity of tank designs. Detailed stress and strain fields were computed from operational temperature changes and pressure loads. The inner tank wall is sized by the resulting biaxial tensile stresses which cause it to be strength driven, and leads to an optimum panel concept that need not be stiffened. Conversely, the outer tank wall is sized by a biaxial compressive stress field, induced by the pressure differential between atmospheric pressure and the vacuum between the tanks, thereby causing the design to be stability driven and thus stiffened to prevent buckling. Induced thermal stresses become a major sizing driver when a composite or hybrid composite/metallic material systems are used for the inner tank wall for purposes such as liners to contain the fuel and reduce hydrogen permeation

Feasibility study for development of a hypervelocity gun final report

Hypervelocity gun with nonconductive projectile and arc plasma armature and metal rails between insulated slab

Automotive Stirling Engine Development Program

Activities performed on Mod I engine testing and test results; the manufacture, assembly, and test of a Mod I engine in the United States; design initiation of the Mod I-A engine system; transient performance testing; Stirling reference engine manufacturing and reduced size studies; components and subsystems; and the study and test of low cost alloys are summarized

Energy Efficient Engine (E3) combustion system component technology performance report

The Energy Efficient Engine (E3) combustor effort was conducted as part of the overall NASA/GE E3 Program. This effort included the selection of an advanced double-annular combustion system design. The primary intent of this effort was to evolve a design that meets the stringent emissions and life goals of the E3, as well as all of the usual performance requirements of combustion systems for modern turbofan engines. Numerous detailed design studies were conducted to define the features of the combustion system design. Development test hardware was fabricated, and an extensive testing effort was undertaken to evaluate the combustion system subcomponents in order to verify and refine the design. Technology derived from this effort was incorporated into the engine combustion hardware design. The advanced engine combustion system was then evaluated in component testing to verify the design intent. What evolved from this effort was an advanced combustion system capable of satisfying all of the combustion system design objectives and requirements of the E3

Structural Integrity and Durability of Reusable Space Propulsion Systems

A two-day conference on the structural integrity and durability of reusable space propulsion systems was held on 14 to 15 May 1991 at the NASA Lewis Research Center. Presentations were made by industry, university, and government researchers organized into four sessions: (1) aerothermodynamic loads; (2) instrumentation; (3) fatigue, fracture, and constitutive modeling; and (4) structural dynamics. The principle objectives were to disseminate research results and future plans in each of four areas. This publication contains extended abstracts and the visual material presented during the conference. Particular emphasis is placed on the Space Shuttle Main Engine (SSME) and the SSME turbopump