Combustion chamber Patent
Regenerative cooling system for rocket combustion chamber using coolant tubes in convergent-divergent nozzle
Gregory, J. W.↗
SEARCH · Engineering Papers
Results for “cooling system”
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Use of high conductivity cladding material on D-shaped coolant passages in nozzles to reduce tube-wall crest temperatures
Analysis of wall temperatures in rocket engine cooling system using D-shaped copper and stainless steel tubes for reduction of tube-wall crest temperatures
Huff, R. G.↗
Space storable regenerative cooling investigation
Performance tests and specifications for space storable regenerative cooling system with liquid oxygen and methane propellants
Source record↗
Heat pipe technology for advanced rocket thrust chambers
Regenerative cooling system design for rocket engines
Rousar, D. C.↗
Investigations of a turbulent jet in a crossflow
Analyses of flow field downstream of jet directed at right angles into crossflow for heated and unheated single jets are presented. Application of flow data to cooling system for gas turbine combustion chambers is discussed. Temperature distribution, velocity trajectory, and vortex motion are described.
Kamotani, Y.↗
Solar powered absorption cycle heat pump using phase change materials for energy storage
Solar powered heating and cooling system with possible application to residential homes is described. Operating principles of system are defined and illustration of typical energy storage and exchange system is provided.
Middleton, R. L.↗
Tolerence for work-induced heat stress in men wearing liquidcooled garments
An investigation of the heat tolerance in men unable to dispose of metabolic heat as fast as it is produced within the body is discussed. Examinations were made of (a) the effect of work rate (metabolic rate) on tolerance time when body heat storage rate is a fixed quantity, and (b) tolerance time as a function of metabolic rate when heat loss is terminated after a thermal quasi-equilibrium was attained under comfortable conditions of heat transfer. The nature of the physiological mechanisms involved in such heat stress situations, and the possibility of using prediction techniques to establish standard procedures in emergencies involving cooling system failures are also discussed.
Blockley, W. V.↗
A multispectral image sensor array.
A silicon monolithic multispectral photosensor device is described. Fabrication techniques and preliminary spectral response data are presented. The device is designed to meet small size and weight requirements and to impose a reduced load upon cooling systems in use on satellites.
Gerhard, G. C.↗
A variable conductance heat pipe/radiator for the lunar surface magnetometer.
The device was developed to supplement the existing cooling system of the Apollo 16 Lunar Surface Magnetometer (LSM). Analysis and tests showed that two such devices, inserted by an astronaut into receptacles on opposite sides of the electronics package, would reduce the diurnal temperature variation by about 40% and thereby would considerably increase the reliability of 50,000 welded connections. The LSM design constraints, selection of a variable conductance technique, heat pipe/radiator design features, and thermal performance are discussed.
Kirkpatrick, J. P.↗
A Case of near Fatal Ammonia Gas Poisoning
A report is given of the near fatal effects of anhydrous ammonia poisoning to a repairman working on a compression room cooling system. The repairman was exposed for approximately 5 minutes to an environment of nearly 100% ammonia gas. Descriptions are given of body burns, breathing problems, and eye burns suffered by the worker.
White, E.↗
Key technology for airbreathing hypersonic aircraft.
This paper reviews recent progress in the key hypersonic technologies, which has been good despite a relatively low priority. Successful hypersonic research engine tests have been made. Active cooling system analyses have shown potential for weight savings, alleviation of structural design problems, and long airframe life. Maturing computerized flow field theories permit optimizing engine-airframe performance. Adequate progress in the future requires an expanded technology program emphasizing hydrogen usage. A hydrogen fueled hypersonic research airplane is essential, providing critical flight data and operational experience.
Nagel, A. L.↗
Off-design temperature effects on nuclear fuel pins for an advanced space-power-reactor concept
An exploratory out-of-reactor investigation was made of the effects of short-time temperature excursions above the nominal operating temperature of 990 C on the compatibility of advanced nuclear space-power reactor fuel pin materials. This information is required for formulating a reliable reactor safety analysis and designing an emergency core cooling system. Simulated uranium mononitride (UN) fuel pins, clad with tungsten-lined T-111 (Ta-8W-2Hf) showed no compatibility problems after heating for 8 hours at 2400 C. At 2520 C and above, reactions occurred in 1 hour or less. Under these conditions free uranium formed, redistributed, and attacked the cladding.
Bowles, K. J.↗
NASA and energy
NASA technology contributions to create energy sources include direct solar heating and cooling systems, wind generation of electricity, solar thermal energy turbine drives, solar cells, and techniques for locating, producing, and collecting organic materials for conversion into fuel.
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Physical sciences: Thermodynamics, cryogenics, and vacuum technology: A compilation
Technological developments which have potential application outside the aerospace community are reported. A variety of thermodynamic devices including heat pipes and cooling systems are described along with methods of handling cryogenic fluids. Vacuum devices are also described. Pata et information is included.
Source record↗
Hypersonic research engine project. Phase 2: Preliminary report on the performance of the HRE/AIM at Mach 6
Test results of the Aerothermodynamic Integration Model are presented. A program was initiated to develop a hydrogen-fueled research-oriented scramjet for operation between Mach 3 and 8. The primary objectives were to investigate the internal aerothermodynamic characteristics of the engine, to provide realistic design parameters for future hypersonic engine development as well as to evaluate the ground test facility and testing techniques. The engine was tested at the NASA hypersonic tunnel facility with synthetic air at Mach 5, 6, and 7. The hydrogen fuel was heated up to 1500 R prior to injection to simulate a regeneratively cooled system. The engine and component performance at Mach 6 is reported. Inlet performance compared very well both with theory and with subscale model tests. Combustor efficiencies up to 95 percent were attained at an equivalence ratio of unity. Nozzle performance was lower than expected. The overall engine performance was computed using two different methods. The performance was also compared with test data from other sources.
Sun, Y. H.↗
Summary of NASA Lewis Research Center solar heating and cooling and wind energy programs
Plans for the construction and operation of a solar heating and cooling system in conjunction with a office building being constructed at Langley Research Center, are discussed. Supporting research and technology includes: testing of solar collectors with a solar simulator, outdoor testing of collectors, property measurements of selective and nonselective coatings for solar collectors, and a solar model-systems test loop. The areas of a wind energy program that are being conducted include: design and operation of a 100-kW experimental wind generator, industry-designed and user-operated wind generators in the range of 50 to 3000 kW, and supporting research and technology for large wind energy systems. An overview of these activities is provided.
Vernon, R. W.↗
Solar collector performance evaluated outdoors at NASA-Lewis Research Center
The study of solar reflector performance reported is related to a project in which solar collectors are to be provided for the solar heating and cooling system of an office building at NASA's Langley Research Center. The solar collector makes use of a liquid consisting of 50% ethylene glycol and 50% water. A conventional air-liquid heat exchanger is employed. Collector performance and solar insolation data are recorded along with air temperature, wind speed and direction, and relative humidity.
Vernon, R. W.↗
Summary of NASA-Lewis Research Center solar heating and cooling and wind energy programs
NASA is planning to construct and operate a solar heating and cooling system in conjunction with a new office building being constructed at Langley Research Center. The technology support for this project will be provided by a solar energy program underway at NASA's Lewis Research Center. The solar program at Lewis includes: testing of solar collectors with a solar simulator, outdoor testing of collectors, property measurements of selective and nonselective coatings for solar collectors, and a solar model-systems test loop. NASA-Lewis has been assisting the National Science Foundation and now the Energy Research and Development Administration in planning and executing a national wind energy program. The areas of the wind energy program that are being conducted by Lewis include: design and operation of a 100 kW experimental wind generator, industry-designed and user-operated wind generators in the range of 50 to 3000 kW, and supporting research and technology for large wind energy systems. An overview of these activities is provided.
Vernon, R. W.↗