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Performance of pure fuels in a single J33 combustor 1: five liquid hydrocarbon fuels

Description: Report presenting an investigation of several pure hydrocarbon fuels in a single tubular-type combustor in order to determine possible relations between combustor performance and fuel properties. The combustor temperature rise, combustion efficiency, and blow-out limits were determined with five liquid hydrocarbon fuels of high purity over a range of heat input and air-flow rates and at two inlet-air-temperature conditions. Performance parameters were selected to compare with the physical and fundamental combustion properties of the fuel.
Date: November 21, 1952
Creator: Wear, Jerrold D. & Dittrich, Ralph T.
Partner: UNT Libraries Government Documents Department

Effect of fuel properties on carbon deposition in atomizing and prevaporizing turbojet combustors

Description: Report presenting investigations of the effects of fuel properties on combustion-chamber carbon deposition in singe tubular fuel-atomizing and fuel-prevaporizing combustors. The NACA K factor and the smoking tendency were approximately equally effective in relating carbon-deposition data from the prevaporizing and atomizing combustors. Results regarding the K factor, smoking tendency, effect of prevaporizing combustor operating conditions, sulfur, gum, and olefin, are provided.
Date: June 6, 1952
Creator: Wear, Jerrold D. & Cook, William P.
Partner: UNT Libraries Government Documents Department

Preliminary investigation of the performance of a single tubular combustor at pressure up to 12 atmospheres

Description: "The effects of combustor operation at conditions representative of those encountered in high pressure-ratio turbojet engines or at high flight speeds on carbon deposition, exhaust smoke, and combustion efficiency were studied in a single tubular combustor. Carbon deposition and smoke formation tests were conducted over a range of combustor-inlet pressures from 33 to 173 pounds per square inch absolute and combustor reference velocities from 78 to 143 feet per second. Combustion efficiency tests were conducted over a range of pressures from 58 to 117 pounds per square inch absolute and velocities from 89 to 172 feet per second" (p. 1).
Date: January 28, 1954
Creator: Wear, Jerrold D. & Butze, Helmut F.
Partner: UNT Libraries Government Documents Department

Performance of a Single Fuel-vaporizing Combustor With Six Injectors Adapted for Gaseous Hydrogen

Description: Report presenting an investigation in a single tubular combustor to determine the effectiveness of hydrogen fuel using an annular fuel-vaporizing combustor in a full-scale turbojet engine. Six different fuel-injector designs were investigated. Results regarding the ignition, combustion efficiency, combustor pressure loss, stability of combustion, and best configuration are provided.
Date: November 30, 1955
Creator: Wear, Jerrold D. & Smith, Arthur L.
Partner: UNT Libraries Government Documents Department

Combustion-efficiency and altitude-limit investigations of five fuels in an annular turbojet combustor

Description: Report presenting five fuels of boiling temperatures and several hydrocarbon types in a jet-propulsion annular combustor to determine the effect of fuel boiling temperature and paraffinic and aromatic hydrocarbon types on combustion efficiency and altitude operational limit. At the severe inlet-air condition, the highest combustion efficiencies were obtained with the paraffinic and aromatic fuels with low boiling temperatures were found to vary from 30 to 58 percent.
Date: June 7, 1954
Creator: Wear, Jerrold D. & 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

Carbon deposition from AN-F-58 fuels in a J33 single combustor

Description: Report presenting an investigation using a single combustor from a 4600-pound-thrust turbojet engine to determine the amount of carbon deposition of AN-F-58 fuels and the effect of carbon formations in the combustor on the altitude operational limits. Three fuel blends conforming to AN-F-58 specification were prepared in order to determine the influence of boiling temperature and of aromatic content on carbon deposition. Results regarding carbon deposition and effect of carbon formations on altitude operational limits are provided.
Date: June 24, 1949
Creator: Wear, Jerrold D. & Douglass, Howard W.
Partner: UNT Libraries Government Documents Department

Lead susceptibility of several fuels as determined in an air-cooled aircraft-engine cylinder

Description: From Report: "In order to determine the lead susceptibility of several fuels, leaded and unleaded fuels from the same stock were blended and tested in a full-scale air-cooled aircraft-engine cylinder. The fuels were S-4 reference fuel, virgin-base stock, aviation alkylate, neohexane, and blends of 25-percent benzene with 75-percent virgin-base stock and 25-percent toluene with 75-percent virgin-base stock."
Date: February 1946
Creator: Stricker, Edward G. & Hensley, Reece V.
Partner: UNT Libraries Government Documents Department

Relative effects of cylinder-head and inlet-mixture temperatures upon knock limits of fuels

Description: Report discusses an investigation into the relation between the effects of cylinder-head temperature and inlet-mixture temperature on the knock limits of fuels. The tests were run at a constant fuel-air ratio and the decrease in cylinder-head temperature required to offset the effect of increasing the inlet-mixture temperature on knock-limited power was determined. The apparatus and testing procedure are described and the effect of changes in cylinder-head temperature on the knock limit of any fuel are plotted.
Date: October 1944
Creator: Sanders, Newell D.; Wear, Jerrold D. & Hensley, Reece V.
Partner: UNT Libraries Government Documents Department

Relations between fuel properties and combustion carbon deposition

Description: Report discussing some methods for predicting the carbon-forming propensity of turbojet-engine fuels from results of simple laboratory tests of the fuels. The prediction of carbon deposition from fuel characteristics including aromatic content, hydrogen-carbon ratio, distillation temperatures, gravity, and aniline point from several empirical laboratory carbon-deposition tests are provided. Results regarding fuel composition and volatility, related fuel properties, empirical laboratory tests, a comparison of methods predicting carbon-deposition characteristics of fuels, and application of fuel quality control methods are provided.
Date: April 14, 1952
Creator: Jonash, Edmund R.; Wear, Jerrold D. & Hibbard, Robert R.
Partner: UNT Libraries Government Documents Department

Performance at high temperatures and pressures of an annular turbojet combustor having articulated liner walls

Description: Report discussing the performance of an experimental quarter-sector annular combustor at conditions simulating supersonic flight of a cooled-turbine engine, as well as 20 different modification to the design. The final configuration was found to show no structural failures and little or no warping of liner parts after 40 hours of operation.
Date: May 10, 1957
Creator: McCafferty, Richard J.; Wear, Jerrold D. & Cook, William P.
Partner: UNT Libraries Government Documents Department

Effect of fuel variables on carbon formation in turbojet-engine combustors

Description: Report presents the results of an investigation of the effects of fuel properties and of a number of fuel additives on combustion-chamber carbon deposition and exhaust-gas smoke formation in a single tubular turbojet-engine combustor. Limited tests were conducted with a number of the fuels in several full-scale turbojet engines to verify single-combustor data.
Date: October 23, 1957
Creator: Jonash, Edmund R.; Wear, Jerrold D. & Cook, William P.
Partner: UNT Libraries Government Documents Department