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Aluminum borohydride as an ignition source for turbojet combustors

Description: From Introduction: "Problems associated with the use of aluminum borohydride for ignition in aircraft are discussed. A detailed description of its properties and results of static chamber tests to determine the effect of diluting aluminum borohydride with n-pentane on flammability in dry air are included in this investigation."
Date: September 3, 1953
Creator: Straight, David M.; Fletcher, Edward A. & Foster, Hampton H.
Partner: UNT Libraries Government Documents Department

High-altitude performance of 9.5-inch-diameter tubular experimental combustor with fuel staging

Description: Report presenting an investigation of 57 experimental tubular designs embodying adjacent fuel-rich and air-rich regions and axial staging of the fuel introduction at simulated high-altitude conditions. Results regarding the development of pilot, development of secondary-air admission sleeve, development of final configuration, and performance of best configuration are provided.
Date: March 22, 1954
Creator: Scull, Wilfred E.
Partner: UNT Libraries Government Documents Department

Effect of Distribution of Basket-Hole Area on Simulated Altitude Performance of 25 1/2-Inch-Diameter Annular-Type Turbojet Combustor

Description: A simulated altitude performance of a 25 1/2-inch-diameter annular-type turbojet combustor was performed to determine the effect of the distribution of basket-hole area on the altitude operational limits of the engine as imposed by the combustor.Total pressure drop was recorded, as well as the effect of fuel-nozzle flow capacity,and fuel-nozzle spray angle for one basket configuration. General observations were made for all configurations regarding flames, extent of afterburning, and durability of the baskets.
Date: August 24, 1948
Creator: Olson, Walter T. & Schroeter, Thomas T.
Partner: UNT Libraries Government Documents Department

Turbojet combustor efficiency with ceramic-coated liners and with mechanical control of fuel wash on walls

Description: Report presenting an investigation to evaluate two methods of decreasing losses of unevaporated fuel from the combustion zone of turbojet-engine combustors. One method had fuel dams on the inner surface of the combustor liner and one had a ceramic coating on the combustor-liner walls. Results regarding the effect of the fuel dams, effect of ceramic coatings, effect of combination of fuel dams and ceramic coatings, and effect of ceramic coating on carbon deposition are provided.
Date: November 24, 1952
Creator: Butze, Helmut F. & Jonash, Edmund R.
Partner: UNT Libraries Government Documents Department

Carbon deposition of 19 fuels in an annular turbojet combustor

Description: Report presenting the effects of fuel properties and change in simulated engine operating conditions on carbon deposition in an annular turbojet combustor. The fuel properties examined included specific gravity, volumetric average boiling temperature, hydrocarbon type, and hydrogen-carbon weight ratio. The fuels included hydrocarbons of the paraffinic, olefinic, and aromatic types as well as fuel mixtures.
Date: February 3, 1949
Creator: Wear, Jerrold D. & Jonash, Edmund R.
Partner: UNT Libraries Government Documents Department