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Investigation of ignition characteristics of AN-F-32 and two AN-F-58a fuels in single can-type turbojet combustor

Description: Ignition characteristics of AN-F-32 and two AN-F-58a fuels were studied in a single can-type turbojet combustor under air-flow conditions representing engine speeds of 1600, 2500, and 4000 rpm, altitudes from sea level to 30,000 feet, ambient temperatures at sea level from 90 degrees to minus 36 degrees F, and flight Mach numbers of 0 and 0.6. Critical fuel-flow rates for ignition increased with increase in preignition engine speed, with increase in altitude, or with decrease in sea-level ambient temperature. This flow rate appears to increase in a direct relation to decrease in fuel volatility as indicated by the 10-percent-evaporated temperature.
Date: October 13, 1950
Creator: Rayle, Warren D. & Douglass, Howard W.
Partner: UNT Libraries Government Documents Department

Performance of five short multielement turbojet combustors for hydrogen fuel in quarter-annulus duct

Description: Report presenting an investigation of five short multielement turbojet combustors designed for use with hydrogen fuel tested in a quarter-annulus duct. One combustor had an array of U-gutter flame-holders, while the other four were manifold arrays of swirl-can combustor elements. Results regarding combustion efficiency, temperature profiles, pressure loss, durability, comparison with previous short combustors, and operation with propane fuel are provided.
Date: July 22, 1958
Creator: Jones, Robert E. & Rayle, Warren D.
Partner: UNT Libraries Government Documents Department

Performance of experimental turbojet-engine combustor I: performance of a one-eighth segment of an experimental turbojet-engine combustor

Description: Report presenting an investigation of a one-eighth segment of an annular combustor suitable for use as a component of an experimental turbojet engine. Due to the small space available for the combustor, a special design involving a minimum of obstructions in the combustion chamber was created. Results regarding the temperature-rise efficiency, total-pressure loss, and exhaust-gas temperature variation for several simulated engine operating conditions are provided.
Date: April 21, 1948
Creator: Hill, Francis U. & Mark, Herman
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

Preliminary results from free-jet tests of a 48-inch-diameter ram-jet combustor with an annular can-type flame holder

Description: Report presenting an investigation in an NACA free-jet facility of a ramjet engine with an experimental 48-inch-diameter combustor. Three combustor lengths and three fuel-distribution systems were investigated over a range of fuel-air ratios and at two air flows. Results regarding the combustor performance and ignition data, velocity profile, and starting characteristics are provided.
Date: May 11, 1955
Creator: Wentworth, Carl B.; Dobson, Wilbur F. & Rayle, Warren D.
Partner: UNT Libraries Government Documents Department

Preliminary results from free jet tests of a 48-inch-diameter ram-jet combustor with an annular-piloted baffle-type flameholder

Description: Report presenting an investigation in a free-jet facility of a ramjet engine with an experimental 48-inch-diameter combustor. Three combustor lengths, three lengths of the shroud which separated the bypass air from the burning stream, and four fuel-distribution systems were investigated over a range of fuel-air ratios and a range of engine air flows. Results regarding the engine performance and ignition data, effect of fuel profile on combustion efficiency, total-pressure ratio, and distribution of static pressure in the main air stream are provided.
Date: May 11, 1955
Creator: Rayle, Warren D.; Smith, Ivan D. & Wentworth, Carl B.
Partner: UNT Libraries Government Documents Department

Combustion of gaseous hydrogen at low pressures in a 35 degree sector of a 28-inch-diameter ramjet combustor

Description: Report presenting testing of gaseous hydrogen fuel burned in a connected-pipe combustor with a cross section equal to 35 degrees sector of a 28-inch diameter. Eleven shrouded fuel-injector configurations were used to obtain combustion data at specified high-altitude ramjet combustor conditions. Results regarding shroud air blockage, mixing tabs, higher equivalence-ratio burning, injector size, flameholder durability, burner length, combustion efficiency, and temperature profile are provided.
Date: April 22, 1958
Creator: Kerslake, William R.
Partner: UNT Libraries Government Documents Department

Combustion efficiency performance of a MIL-F-5624 type fuel and monomethylnapthalene in a single vaporizing combustor

Description: Report presenting an investigation conducted with a conventional turbojet fuel, MIL-F-5624 (JP-3), and a low-volatility, high-density hydrocarbon, monomethylnaphthalene, in a vaporizing-type combustor to determine the combustion efficiency for variations in inlet-air conditions and fuel flow and to what extent fuel vaporization would minimize differences in combustion efficiency between the two fuels. Results regarding the performance of the combustor, correlation parameter, pressure-drop characteristics, and other miscellaneous observations are provided.
Date: February 14, 1952
Creator: Jones, Anthony W. & Cook, William P.
Partner: UNT Libraries Government Documents Department

Blow-out velocities of various petroleum, slurry, and hydride fuels in a 1 7/8-inch diameter combustor

Description: Report presenting testing using a 1 7/8-inch inside-diameter combustor that can measure and compare the blow-out velocities of single-component fuels, slurries, and fuel mixtures with a wide range of reactivity and physical properties. The blow-out velocities of isooctane, n-heptane, isopentane, allyl chloride, and propylene oxide varied int he same way as flame speeds of the fuels. Results regarding the effects of different additives are also provided.
Date: April 19, 1954
Creator: Cook, Preston N., Jr.; Lord, Albert M. & Kaye, Samuel
Partner: UNT Libraries Government Documents Department

Effect of fuel nozzle protrusion on transient and steady-state turbojet combustor performance

Description: Report presenting the effect of small variations in the axial position of the liner with respect to the nozzle on limiting rates of change of fuel flow and steady-state combustion efficiencies in a single tubular combustor. Data were obtained with two liner configurations at three combustor-inlet conditions. Results regarding transient combustion performance and steady-state combustion performance are provided.
Date: February 23, 1955
Creator: McCafferty, Richard J. & Donlon, Richard H.
Partner: UNT Libraries Government Documents Department

Effect of mechanically induced sinusoidal air-foil oscillations on operation of a ram-jet engine

Description: Report presenting an experimental investigation in a 16-inch ram-jet engine to examine the degree to which inlet flow pulsations influence the combustion efficiency and lean blow-out limit of a ram-jet combustor.
Date: June 16, 1954
Creator: Dangle, E. E.; Cervenka, A. J. & Perchonok, Eugene
Partner: UNT Libraries Government Documents Department

Effect of liner air-entry holes, fuel state, and combustor size on performance of an annular turbojet combustor at low pressures and high air-flow rates

Description: Report presenting the development of an annular combustor by utilizing the design principles evolved in previous investigations and by making 12 design changes to optimize the altitude performance of the combustor. Three types of fuels were used and the combustion efficiency, pressure losses, and outlet temperature profiles were evaluated.
Date: January 13, 1953
Creator: Norgren, Carl T. & Childs, J. Howard
Partner: UNT Libraries Government Documents Department

Effect of fuel injectors and liner design on performance of an annular turbojet combustor with vapor fuel

Description: Report presenting a direct-connect duct investigation conducted with a one-quarter segment of a 25.5-inch-diameter annular combustor that had been developed for liquid fuel injection. The combustor was modified by changing the fuel injectors and liner design for vapor fuel injection. Results regarding accuracy and reproducibility, combustion efficiency, combustor-outlet temperature profiles, and pressure losses are provided.
Date: April 6, 1953
Creator: Norgren, Carl T. & Childs, J. Howard
Partner: UNT Libraries Government Documents Department

Performance at simulated high altitudes of a prevaporizing annular turbojet combustor having low pressure loss

Description: An annular prevaporizing turbojet combustor having pressure losses lower than those obtained in current turbojet combustors was developed, Pressure losses of 2 to 4 percent, satisfactory temperature profiles, and combustion efficiencies of 98, 88, and 81 percent were obtained at 56,000, 70,000, and 80,000 feet respectively, for a simulated 5.2- pressure-ratio engine at rated speed and 0.6 flight Mach number with JP-4 fuel. Use of JP-5 fuel resulted in a small penalty in efficiency due, at least in part, to insufficient prevaporizer capacity.
Date: December 6, 1956
Creator: Norgren, Carl T.
Partner: UNT Libraries Government Documents Department

Performance of an annular turbojet combustor having reduced pressure losses and using propane fuel

Description: Report presenting an investigation to develop a high-combustion-efficiency turbojet combustor with pressure losses typical of those encountered in current turbojet engines. A total of 13 air-entry hole modifications was investigated to obtain a combustor design with high combustion efficiencies and a satisfactory outlet radial temperature profile. Results regarding combustor development and the performance of Model 28I are provided.
Date: September 24, 1953
Creator: Norgren, Carl T. & Childs, J. Howard
Partner: UNT Libraries Government Documents Department

Free-jet altitude investigation of a 20-inch ram-jet combustor with a rich inner zone of combustion for improved low-temperature-ratio operation

Description: From Summary: "An investigation of the altitude performance of a 20-inch-diameter high-temperature-ratio ram-jet combustor which had been redesigned to provide good combustor efficiency over a wide range of temperature ratios was conducted at zero angle of attack in a free-jet facility at a Mach number of 3.0. Configurations investigated incorporated a cylindrical control sleeve which confined the injected fuel at low over-all fuel-air ratios to about 40 percent of the engine air flow. This provided an optimum fuel-air mixture over a portion of the flame holder when the over-all fuel-air ratio was about 0.02."
Date: May 25, 1953
Creator: Trout, Arthur M. & Wentworth, Carl B.
Partner: UNT Libraries Government Documents Department

Propellant vaporization as a criterion for rocket engine design; Calculations of chamber length to vaporize a single n-heptane drop

Description: Report presenting an analysis based on droplet-evaporation theory, which shows that for a given combustor length, the percent of fuel mass vaporized can be increased by decreasing the fuel-drop size and initial drop velocity, or by increasing chamber pressure, final gas velocity, and initial fuel temperature. The results were correlated to give a single curve of percent of fuel evaporated as a function of the chamber length and the factors involving the parameters.
Date: July 1957
Creator: Priem, Richard J.
Partner: UNT Libraries Government Documents Department

Effect of axially staged fuel introduction on performance of one-quarter sector of annular turbojet combustor

Description: The design principle of injecting liquid fuel at more than one axial station in an annual turbojet combustor was investigated. Fuel was injected into the combustor as much as 5 inches downstream of the primary fuel injectors. Many fuel-injection configurations were examined and the performance results are presented for 11 configurations that best demonstrate the trends in performance obtained. The performance investigations were made at a constant combustor-inlet pressure of 15 inches of mercury absolute and at air flows up to 70 percent higher than values typical of current design practice. At these higher air flows, staging the fuel introduction improved the combustion efficiency considerably over that obtained in the combustor when no fuel staging was employed. At air flows currently encountered in turbojet engines, fuel staging was of minor value. Radial temperature distribution seemed relatively unaffected by the location of fuel-injection stations.
Date: March 30, 1953
Creator: Zettle, Eugene V. & Mark, Herman
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

Spark ignition of flowing gases III : effect of turbulence promoter on energy required to ignite a propane-air mixture

Description: Report presenting an investigation to determine the effect of turbulence generated by different sizes of wire grid on the minimum spark-ignition energy of a flowing propane-air mixture. Gas-stream velocity, size of turbulence promoter, and distance from the promoter plate to the electrodes on minimum ignition energy were evaluated and the effects are shown in figures.
Date: January 14, 1953
Creator: Swett, Clyde C., Jr. & Donlon, Richard H.
Partner: UNT Libraries Government Documents Department

Effect of air distribution on radial temperature distribution in one-sixth sector of annular turbojet combustor

Description: Report presenting an experimental investigation in a one-sixth sector of an annular turbojet combustor to determine a method of controlling radial exhaust-gas-temperature distribution in a gas-turbine combustion chamber. The adjustment in controlling air was made by ducting the dilution air into the combustion zone in a predetermined manner through hollow radial struts or by modifying the basket-wall open-hole area. Results regarding the temperature distribution, temperature-rise efficiency, total-pressure loss, and altitude operating limits are provided.
Date: April 5, 1950
Creator: Mark, Herman & Zettle, Eugene V.
Partner: UNT Libraries Government Documents Department

Altitude performance investigation of two single-annular type combustors and the prototype J40-WE-8 turbojet engine combustor with various combustor-inlet air pressure profiles

Description: Report presenting data obtained three single annular-type combustors with different combustor inlet-air pressure profiles over a range of engine speeds. Results regarding effect of changing combustor inlet-air pressure profile and hole geometry on combustor performance, performance of the prototype J40-WE-8 turbojet engine combustor, correlation of combustion efficiency with engine fuel-air ratio and combustion parameter, and comparison of several combustors from different turbojet engines are provided.
Date: May 29, 1953
Creator: Sobolewski, Adam E.; Miller, Robert R. & McAulay, John E.
Partner: UNT Libraries Government Documents Department

Performance investigation of can-type combustor 2: water injection at various stations in combustor

Description: Report presenting an investigation to determine the maximum quantity of water that could be injected either into or ahead of a single can-type combustor without reducing the attainable combustor-outlet temperature below the value required for engine operation and without the appearance of liquid water at the combustor outlet. Water was injected from spray nozzles at four different stations along the combustor.
Date: September 30, 1948
Creator: Cook, William P. & Zettle, Eugene V.
Partner: UNT Libraries Government Documents Department