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Preliminary investigation of propane combustion in a 3-inch-diameter duct of inlet-air temperatures of 1400 to 1600 F

Description: Report presenting a determination of ignition delays and combustion efficiencies for propane injected into a heated airstream. Two types of flames were observed for multipoint fuel injectors: a diffusion flame that stabilized at the injector orifices and an ignition-stabilized flame that formed a flame front downstream of the fuel injector. Results regarding combustion of injector-stabilized flames and combustion of ignition-stabilized flames are provided.
Date: July 1957
Creator: Lezberg, Erwin A.
Partner: UNT Libraries Government Documents Department

Preliminary evaluation of pentaborane in a 1/4-sector of an experimental annular combustor

Description: Report presenting an evaluation of a 1/4-sector of an annular combustor designed for use with pentaborane fuel at a simulated altitude condition. Results regarding the pentaborane performance, combustor development, and the JP-5 fuel performance are provided.
Date: May 22, 1957
Creator: Kaufman, Warner B.; Lezberg, Erwin A. & Breitwieser, Roland
Partner: UNT Libraries Government Documents Department

Experimental investigation of physical and combustion properties of several residual fuel oils and magnesium - fuel-oil slurries in a ram-jet-type combustor

Description: Report presenting an experimental investigation using a 1 7/8-inch diameter burner to determine the suitability of residual fuel oils as carriers in magnesium slurries. Four residual fuel oils with varying viscosities were investigated by themselves and in slurries of 50 percent magnesium. Results regarding the settling characteristics, blow-out velocity, and combustion efficiency are provided.
Date: June 23, 1953
Creator: Cook, Preston N., Jr.; Evans, Vernida E. & Lezberg, Erwin A.
Partner: UNT Libraries Government Documents Department

Weight-flow and thrust limitations due to use of rotating combustors in a turbojet engine

Description: Report presenting the suggestion of an engine configuration that is intended to minimize difficulties caused by exhaust products that are expected to adhere to stationary parts but not rotating parts and exploit the high reactivity of fuel. Component efficiencies of the engine are assigned and its performance is compared with that of a single-stage turbine engine. Results regarding the effect of reaction-nozzle-jet angle, effect of turbine-exit axial Mach number, comparison of rotojet and turbojet performance, and performance of fixed-geometry rotojet engine are provided.
Date: August 17, 1956
Creator: Lezberg, Erwin A.; Blackshear, Perry L., Jr. & Rayle, Warren D.
Partner: UNT Libraries Government Documents Department