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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

Analytical evaluation of effect of inlet-air temperature and combustion pressure on combustion performance of boron slurries and blends of pentaborane in octene-1

Description: From Summary: "The effects of variation in inlet-air temperature, combustion pressure, and boron or pentaborane concentration on combustion performance were discussed. It was shown how the theoretical data herein could be employed in obtaining the combustion efficiency of experimental combustors. Data were presented by which combustion efficiencies obtained with a water-quench heat balance could be adjusted for the heat of dissociation of the combustion products."
Date: June 1, 1955
Creator: Tower, Leonard K.
Partner: UNT Libraries Government Documents Department

Experimental evaluation of 'swirl-can' elements for hydrogen-fuel combustor

Description: Report presenting a study of the performance of "swirl-can" combustor elements for an experimental short-length turbojet combustor utilizing hydrogen fuel at high-altitude operating conditions. Fuel was injected into each element through a tangential , sonic orifice that created a swirling fuel-air mixture within the element. Results regarding combustor blowout, combustion efficiency, outlet temperature distribution, and preliminary performance of the multielement performance of multielement combustor are provided.
Date: May 13, 1957
Creator: Rayle, Warren D.; Jones, Robert E. & Friedman, Robert
Partner: UNT Libraries Government Documents Department

NACA research on combustors for aircraft gas turbines 1: effects of operating variables on steady-state performance

Description: Some of the systematic research conducted by the NACA on aircraft gas-turbine combustors is reviewed. Trends depicting the effect of inlet-air pressure, temperature, and velocity and fuel-air ratio on performance characteristics, such as combustion efficiency, maximum temperature rise attainable, pressure loss, and combustor-outlet temperature distribution are described for a variety of turbojet combustors of the liquid-fuel type. These trends are further discussed as effects significant to the turbojet engine, such as altitude operational limits, specific fuel consumption, thrust, acceleration, and turbine life.
Date: October 18, 1950
Creator: Olson, Walter T. & Childs, J. Howard
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

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

Engineering method of ram-jet thrust determination based on experimentally obtained combustor parameters

Description: From Summary: "A parameter is introduced which simplifies the accounting for pressure losses in ram-jet combustors. This parameter, called the combustor-force coefficient, relates the jet force and the total pressure at the combustion-chamber entrance. Experimental data for several different combustors are presented for evaluation and comparison."
Date: August 13, 1953
Creator: Dettwyler, H. Rudolph & Faget, Maxime A.
Partner: UNT Libraries Government Documents Department

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

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

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