Some alkali metal corrosion effects in a Rankine cycle test loop
Metal corrosion effects in Rankine cycle lithium-boiling potassium test loop simulating working fluids of spacecraft nuclear turboplant propulsion system
Phillips, W. M.↗
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A progress report on the JPL liquid-metal MHD cycle
Liquid metal MHD power conversion system with Cs and Li as working fluids, describing hydraulic, electrical and high temperature tests results
Cerini, D. J.↗
Theoretical analyses of cryogenic heat pipes
Working fluids liquid property variations effects on cryogenic heat pipe performance
Chi, S. W.↗
Steady-state and transient performance of hot reservoir gas-controlled heat pipes
Liquid or vapor phase working fluids penetration effects on steady state and transient performance of hot reservoir gas controlled heat pipes
Fleischman, G. L.↗
Performance map of an ammonia /NH3/ heat pipe
Heat pipe performance map with ammonia as working fluid, comparing thermal transport efficiency with water pipe
Schwartz, J.↗
System accurately controls pressure in cryogenic tanks
High-resolution differential pressure transducer senses very small positive or negative pressure variations in the cryogenic tank relative to absolute reference pressure. System is useful in calibrating instruments where working fluid must be maintained at closely controlled temperature, or in processes requiring very fine pressure control.
Kirchmeier, W. E., Jr.↗
Design and development of a gas management subsystem for a Brayton space power system
Gas management subsystem using xenon-helium working fluid designed for Brayton space power system
Haack, A. F.↗
Design and development of a prototype static cryogenic heat transfer system
Design and development of prototype static cryogenic heat transfer system utilizing heat pipe with wetting arterial wick and nitrogen as working fluid
Source record↗
Status of advanced Rankine power conversion technology
Rankine cycle turboelectric nuclear space power conversion system with liquid K as working fluid, discussing current technology status
Gutstein, M. U.↗
Design point characteristics of a 15-to-80 kWe nuclear-reactor Brayton-cycle power system
Nuclear reactor Brayton cycle space power system design point characteristics, discussing cycle parameters, working fluid, turbine inlet temperature, operating pressure level, etc
Kerwin, P. T.↗
Component and overall performance of an advanced Rankine cycle test rig
Component performance of three loop Rankine cycle test rig using lithium, potassium and NaK-78 as working fluids
Bond, J. A.↗
An electrohydrodynamic heat pipe
Dielectric liquid for transfer of heat provides liquid flow from the condenser section to the evaporator section in conventional heat pipes. Working fluid is guided or pumped by an array of wire electrodes connected to a high-voltage source.
Jones, T. B.↗
Status of power generation experiments in the NASA Lewis closed cycle MHD facility
The design and operation of the closed cycle MHD facility is discussed and results obtained in recent experiments are presented. The main components of the facility are a compressor, recuperative heat exchanger, heater, nozzle, MHD channel with 28 pairs of thoriated tungsten electrodes, cesium condenser, and an argon cooler. The facility has been operated at temperatures up to 2100 K with a cesium-seeded argon working fluid. At low magnetic field strengths, the open circuit voltage, Hall voltage and short circuit current obtained are 90, 69, and 47 percent of the theoretical equilibrium values, respectively. Comparison of this data with a wall and boundary layer leakage theory indicates that the generator has shorting paths in the Hall direction.
Sovie, R. J.↗
Design and preliminary testing of a Brayton space radiator concept
A low-temperature radiator has been designed to reject 17.62 kW of thermal power from an isotope Brayton power system. This power system has an electrical output of 7.1 kW. The total radiator consists of two radiators connected in series. Both radiators have a redundant coolant loop, shared fins, and are close to flight configuration. A silicone oil is used as the working fluid. Low flow rates and moderate pressure drop in the radiator required a small hydraulic diameter with large heat transfer area and large flow area. To obtain these characteristics and meet schedule limitations, an expanded tube configuration (with an approximately trapezoidal cross section) was selected. Because of the low flow rates and unconventional tube shape, small scale tests were performed to evaluate the validity of existing heat transfer and pressure drop correlations to this case. The results of these tests were in good agreement with predictions.
Miller, T. J.↗
Preliminary performance of a 4.97-inch radial turbine operating in a Brayton power system with a helium-xenon gas mixture
The performance characteristics of the Brayton-rotating-unit's 4.97-inch radial turbine were investigated with the turbine part of a power conversion system. The following system parameters were varied: turbine inlet temperature from 1200 to 1600 F, compressor inlet temperature from 60 to 120 F, compressor outlet pressure from 20 to 45 psia, and shaft speed from 90-110 percent of rated speed (36000 rpm). The working fluid of the system was a gas mixture of helium-xenon with a nominal molecular weight of 83.8. Test results indicate that changes in system conditions have little effect on the turbine efficiency. At the design turbine inlet temperature of 1600 F and compressor inlet temperature of 80 F, an average turbine efficiency of 91 percent was obtained.
Leroy, M. J., Jr.↗
Steady-state temperature distribution within a Brayton rotating unit operating in a power conversion system using helium-xenon gas
The Brayton rotating unit (BRU), consisting of a turbine, an alternator, and a compressor, was tested as part of a Brayton cycle power conversion system over a side range of steady state operating conditions. The working fluid in the system was a mixture of helium-xenon gases. Turbine inlet temperature was varied from 1200 to 1600 F, compressor inlet temperature from 60 to 120 F, compressor discharge pressure from 20 to 45 psia, rotative speed from 32 400 to 39 600 rpm, and alternator liquid-coolant flow rate from 0.01 to 0.27 pound per second. Test results indicated that the BRU internal temperatures were highly sensitive to alternator coolant flow below the design value of 0.12 pound per second but much less so at higher values. The armature winding temperature was not influenced significantly by turbine inlet temperature, but was sensitive, up to 20 F per kVA alternator output, to varying alternator output. When only the rotational speed was changed (+ or - 10% of rated value), the BRU internal temperatures varied directly with the speed.
Johnsen, R. L.↗
Brayton heat exchange unit development program
A Brayton Heat Exchanger Unit (BHXU), consisting of a recuperator, a heat sink heat exchanger and a gas ducting system, was designed, fabricated, and tested. The design was formulated to provide a high performance unit suitable for use in a long-life Brayton-cycle powerplant. A parametric analysis and design study was performed to establish the optimum component configurations to achieve low weight and size and high reliability, while meeting the requirements of high effectiveness and low pressure drop. Layout studies and detailed mechanical and structural design were performed to obtain a flight-type packaging arrangement. Evaluation testing was conducted from which it is estimated that near-design performance can be expected with the use of He-Xe as the working fluid.
Morse, C. J.↗
Design and fabrication of the Brayton rotating unit
The Brayton rotating unit (BRU), operating on a gas bearing system, has been designed, fabricated, and demonstrated for use in a closed Brayton cycle space power conversion system. The BRU uses a binary mixture of xenon and helium (molecular weight, 83.8) as the cycle working fluid and bearing lubricating medium and was designed to produce from 2.25 to 10.5 kw sub e of 1200 Hz three-phase electrical power. The single-shaft rotating assembly operates at a design speed of 36,000 rpm and comprises a radial single-stage compressor, a four-pole Rice alternator rotor, and a radial inflow turbine. Four units, a dynamic simulator and three component research packages, were supplied to the NASA Lewis Research Center for performance testing and further development.
Davis, J. E.↗