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Priem, R. J.

Publications and source records attributed to Priem, R. J..

At least 19 records
All sourcesNASA NTRSDOE OSTI
NASA NTRS1980

Chemical propulsion technology

An overview of NASA's low thrust liquid chemical propulsion program is presented with particular emphasis on thrust system technology in the ten to one thousand pound thrust range. Key technology issues include high performance of cooled low thrust engines; small cryogenic pumps; multiple starts-shutdowns (10) with slow ramps (approximately 10 seconds); thrust variation - 4/1 in flight and 20/1 between flights; long life (100 hours); improved system weight and size; and propellant selection.

Priem, R. J.↗
NASA NTRS1977

Effluent characterization from a conical pressurized fluid bed

To obtain useable corrosion and erosion results it was necessary to have data with several levels of particulate matter in the hot gases. One level of particulate loading was as low as possible so that ideally no erosion and only corrosion occurred. A conical fluidized bed was used to obtain some degree of filtration through the top of the bed which would not be highly fluidized. This would minimize the filtration required for the hot gases or conversely the amount of particulate matter in the hot gases after a given level of filtration by cyclones and/or filters. The data obtained during testing characterized the effluent from the bed at different test conditions. A range of bed heights, coal flows, air flows, limestone flows, and pressure are represented. These tests were made to determine the best operating conditions prior to using the bed to determine erosion and corrosion rates of typical turbine blade materials.

Priem, R. J.↗
NASA NTRS1977

Effluent characterization from a conical pressurized fluid bed

An important factor regarding the use of a pressurized coal burning fluidized bed (PFB) providing gases for driving a gas turbine is the turbine blade lifetime. However, very little data are currently available to predict erosion and corrosion rates produced by the effluent from a PFB. To assess the potential of alloys developed for aeronautical applications to resist this environment it was decided to build a coal burning fluidized bed that could be employed to measure erosion and corrosion rates. Tests were conducted with a conical fluidized bed to obtain some degree of filtration through the top of the bed. A description is presented of the data obtained in the first 138 hours of testing to characterize the effluent from the bed under different test conditions. The considered tests had been made to determine the best operating conditions prior to using the bed for a determination of the erosion and corrosion rates of typical turbine blade materials.

Priem, R. J.↗
NASA NTRS1977

Emissions control for ground power gas turbines

The similarities and differences of emissions reduction technology for aircraft and ground power gas turbines is described. The capability of this technology to reduce ground power emissions to meet existing and proposed emissions standards is presented and discussed. Those areas where the developing aircraft gas turbine technology may have direct application to ground power and those areas where the needed technology may be unique to the ground power mission are pointed out. Emissions reduction technology varying from simple combustor modifications to the use of advanced combustor concepts, such as catalysis, is described and discussed.

Rudney, R. A.↗
NASA NTRS1973

Technique for predicting high-frequency stability characteristics of gaseous-propellant combustors

A technique for predicting the stability characteristics of a gaseous-propellant rocket combustion system is developed based on a model that assumes coupling between the flow through the injector and the oscillating chamber pressure. The theoretical model uses a lumped parameter approach for the flow elements in the injection system plus wave dynamics in the combustion chamber. The injector flow oscillations are coupled to the chamber pressure oscillations with a delay time. Frequency and decay (or growth) rates are calculated for various combustor design and operating parameters to demonstrate the influence of various parameters on stability. Changes in oxidizer design parameters had a much larger influence on stability than a similar change in fuel parameters. A complete description of the computer program used to make these calculations is given in an appendix.

Priem, R. J.↗
NASA NTRS1970

Liquid rocket technology for the ch. e.

Liquid rocket technology for chemical engineers, discussing propellant tanks, lines and valves, tank pressurization, turbopumps and combustion chamber problems

Priem, R. J.↗