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Results for “SUPERCHARGERS - NASH”

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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At least 55 records · Page 3
All sourcesNASA NTRSDOE OSTI
NASA NTRS1977

Intense localized photoelectric charging in the lunar sunset terminator region. I - Development of potentials and fields. II - Supercharging at the progression of sunset

Numerical computations show that locally sunlit areas in the dark lunar sunset terminator region can acquire large electric potentials and fields due to the retention of photoelectrons emitted from sunlit areas by surrounding dark areas of the highly resistive lunar surface. It is shown that the potential can increase or decrease depending on the rates of photoelectron emission and areal contraction. It is concluded that in the lunar situation, the likely result is an increase in the potential, or a 'supercharging' of the sunlit area.

Criswell, D. R.↗
NASA NTRS1979

Supercharged topping rocket propellant feed system

A rocket propellant feed system utilizing a bleed turbopump to supercharge a topping turbopump is presented. The bleed turbopump is of a low pressure type to meet the cavitation requirements imposed by the propellant storage tanks. The topping turbopump is of a high pressure type and develops 60 to 70 percent of the pressure rise in the propellant.

Stewart, W. L.↗
NASA NTRS1990

Performance of a supercharged direct-injection stratified-charge rotary combustion engine

A zero-dimensional thermodynamic performance computer model for direct-injection stratified-charge rotary combustion engines was modified and run for a single rotor supercharged engine. Operating conditions for the computer runs were a single boost pressure and a matrix of speeds, loads and engine materials. A representative engine map is presented showing the predicted range of efficient operation. After discussion of the engine map, a number of engine features are analyzed individually. These features are: heat transfer and the influence insulating materials have on engine performance and exhaust energy; intake manifold pressure oscillations and interactions with the combustion chamber; and performance losses and seal friction. Finally, code running times and convergence data are presented.

Bartrand, Timothy A.↗
NASA NTRS1992

Supercharged ejector ramjet

The Supercharged Ejector Ramjet (SERJ) engine is a highly flexible and promising composite propulsion system offering significant payoffs in high performance vehicle systems. Its basic subsystems such as fan, ejector, and ramjet have been experimentally demonstrated. These components have also been integrated into engine demonstrators and tested in Marquardt Cell 2 facilities. It is recommended that Marquardt's past SERJ related test data and studies be reviewed and updated by incorporating state-of-the art technologies.

Rosevear, Jerry↗
NASA NTRS1940

Pressure and temperature measurement in supercharger investigations

With the further development of the supercharger, requirements with regard to measuring accuracy increase while at the same time the conditions under which the measurements must be carried out become more difficult. The present paper is a contribution toward the improvement and refinement of the measuring methods. For pressure measurements some suggestions are made with regard to design and location of the measuring stations. The question of temperature measurement in rapid air flow is discussed, new instruments for the direct measurement of the temperature in the rapid airstream are described and the results obtained with the various instruments presented.

Franz, A↗
NASA NTRS1937

The Design of Airplane-engine Superchargers

With the forms of superchargers and underlying principles of computation, delivery heads per stage of 7,000 to 8,500 meters (air column) at an effective efficiency, based on the adiabatic process, of 0.7 may be attained, the space and weight requirements being kept within reasonable limits.

Von Der Null, Werner↗
NASA NTRS2000

Marquardt's Mach 4.5 Supercharged Ejector Ramjet (SERJ) High-Performance Aircraft Engine Project: Unfulfilled Aspirations Ca.1970

The Supercharged Ejector Ramjet (SERJ) engine developments of the 1960s, as pursued by The Marquardt Corporation and its associated industry team members, are described. In just three years, engineering work on this combined-cycle powerplant type evolved, from its initial NASA-sponsored reusable space transportation system study status, into a U.S. Air Force/Navy-supported exploratory development program as a candidate 4.5 high-performance military aircraft engine. Bridging a productive transition from the spaceflight to the aviation arena, this case history supports the expectation that fully-integrated airbreathing/rocket propulsion systems hold high promise toward meeting the demanding propulsion requirements of tomorrow's aircraft-like Spaceliner class transportation systems. Lessons to be learned from this "SERJ Story" are offered for consideration by today's advanced space transportation and combined-cycle propulsion researchers and forward-planning communities.

Escher, William J. D.↗
NASA NTRS1947

Possibilities of Reducing the Length of Axial Superchargers for Aircraft Motors

Axial blowers are gaining importance as aircraft engine superchargers. However, the pressure head obtainable per stage is small. Due to the necessary great number of stages, the physical length of the blower becomes too great for an airworthy device. This report discusses several types of construction that permit a reduction in the length of the blower.

Eckert, B.↗
NASA NTRS2008

Supercharged two-cycle engines employing novel single element reciprocating shuttle inlet valve mechanisms and with a variable compression ratio

This invention relates to novel reciprocating shuttle inlet valves, effective with every type of two-cycle engine, from small high-speed single cylinder model engines, to large low-speed multiple cylinder engines, employing spark or compression ignition. Also permitting the elimination of out-of-phase piston arrangements to control scavenging and supercharging of opposed-piston engines. The reciprocating shuttle inlet valve (32) and its operating mechanism (34) is constructed as a single and simple uncomplicated member, in combination with the lost-motion abutments, (46) and (48), formed in a piston skirt, obviating the need for any complex mechanisms or auxiliary drives, unaffected by heat, friction, wear or inertial forces. The reciprocating shuttle inlet valve retains the simplicity and advantages of two-cycle engines, while permitting an increase in volumetric efficiency and performance, thereby increasing the range of usefulness of two-cycle engines into many areas that are now dominated by the four-cycle engine.

Wiesen, Bernard↗