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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

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

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

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

Performance of a Ram-Jet-Type Combustor With Flame Holders Immersed in the Combustion Zone

Description: Memorandum presenting the beneficial effects on stability limits and combustion efficiency produced by the application of surfaces immersed in the combustion zone to a ram-jet-type burner. Investigations were made with one, two, three, and four rows of wedges at simulated sea-level and altitude subsonic ram-jet flight conditions. The addition of rows of wedges immersed in the combustion zone regularly extended the stability limits of combustion.
Date: November 1948
Creator: Breitwieser, Roland
Partner: UNT Libraries Government Documents Department

High-Altitude Performance of an Experimental Turbular Prevaporizing Combustor

Description: Memorandum presenting an investigation of an experimental tubular combustor that provides for prevaporizing and premixing of the fuel with a part of the air before its introduction into the combustion zone. Combustion efficiency and total-pressure loss data are presented for three configurations selected from a total of 43 different modifications investigated. Results regarding the combustor development, comparison of liquid and gaseous fuel, combustor total-pressure losses, combustor-outlet temperature distribution, and evaluation of experimental prevaporizing combustors are provided.
Date: December 9, 1954
Creator: Butze, Helmut F.
Partner: UNT Libraries Government Documents Department

Investigation of Three Low-Temperature-Ratio Combustor Configurations in a 48-Inch-Diameter Ram-Jet Engine

Description: Memorandum presenting a preliminary evaluation of three types of combustor configuration in a 48-inch-diameter ramjet engine in order to select the one with the greatest promise of efficient and stable combustion at low fuel-air ratios and low combustor-inlet pressures. Results regarding the inlet conditions, performance, and a comparison of the configurations are provided.
Date: March 10, 1954
Creator: Meyer, Carl L. & Weina, Harry J.
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

Combustion-efficiency investigation of special fuels in single tubular-type combustor at simulated altitude conditions

Description: Report presenting a combustion-efficiency investigation of 10 special straight-run distillate fuels in an individual tubular-type combustor unit of a 14-unit assembly at two simulated engine operating conditions. These distillates were obtained from various crude oils and consisted of hydrocarbon mixtures with distillations temperature varying from 93 to 690 degrees Fahrenheit. Comparison of temperature measurements obtained from two locations in the exhaust duct showed that under certain operating conditions the flame extended beyond the turbine position.
Date: August 15, 1947
Creator: Dittrich, Ralph T.
Partner: UNT Libraries Government Documents Department

Discharge coefficients for combustor-liner air-entry holes 2: flush rectangular holes, step louvers, and scoops

Description: Experimental discharge coefficients for various types of combustor-liner air-entry holes are presented as a function of a dimensionless flow parameter. In general, scoops and step louvers have higher discharge coefficients and wider flow ranges than flush holes. The effects of size or shape of a given type of hole are small. The proximity of multiple flush holes or the wall inclination of a convergent duct has a negligible effect on discharge coefficient.
Date: April 1958
Creator: Dittrich, Ralph T.
Partner: UNT Libraries Government Documents Department

Effects of fuel-nozzle carbon deposition on combustion efficiency of single tubular-type, reverse-flow turbojet combustor at simulated altitude conditions

Description: Report presenting an investigation to study the effects of changes in fuel-nozzle carbon deposition on the combustion efficiency of a single tubular-type, reverse-flow, turbojet combustor. The investigation was conducted because of the need to improve the reproducibility of combustion data for fuel-research purposes.
Date: June 1948
Creator: Dittrich, Ralph T.
Partner: UNT Libraries Government Documents Department

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

Performance of a 28-inch ramjet utilizing gaseous hydrogen at a Mach number of 3.6, angles of attack up to 12 degree, and pressure altitudes up to 110,000 feet

Description: Report presenting an investigation in the 10- by 10-foot supersonic wind tunnel to evaluate the performance of a shrouded injector burner with perforated domes employed in a 28-inch ramjet using gaseous hydrogen as fuel. Steady-state data were obtained at a pressure altitude of 77,000 feet and zero angle of attack. Results indicated that burning could be initiated under severe distortion conditions and that satisfactory combustor operation was accomplished up to a pressure altitude of 110,000 feet with no adverse effect on combustion efficiency.
Date: May 19, 1958
Creator: Musial, Norman T.; Ward, James J. & Wasserbauer, Joseph F.
Partner: UNT Libraries Government Documents Department

Relation of Turbojet and Ramjet Combustion Efficiency to Second-Order Reaction Kinetics and Fundamental Flame Speed

Description: Theoretical studies of the turbojet and ramjet combustion process are summarized and the resulting equations are applied to experimental data obtained from various combustor tests. The theoretical treatment assumes that one step in the over-all chain of processes which constitute jet-engine combustion is sufficiently slow to be the rate-controlling step that determines combustion efficiency.
Date: August 5, 1957
Creator: Childs, J. Howard; Reynolds, Thaine W. & Graves, Charles C.
Partner: UNT Libraries Government Documents Department

Effect of combustor-inlet conditions on performance of an annular turbojet combustor

Description: From Summary: "The combustion performance, and particularly the phenomenon of altitude operational limits, was studied by operating the annular combustor of a turbojet engine over a range of conditions of air flow, inlet pressure, inlet temperature, and fuel flow. Information was obtained on the combustion efficiencies, the effect on combustion of inlet variables, the altitude operational limits with two different fuels, the pressure losses in the combustor, the temperature and velocity profiles at the combustor outlet, the extent of afterburning, the fuel-injection characteristics, and the condition of the combustor basket."
Date: March 21, 1947
Creator: Childs, J. Howard; McCafferty, Richard J. & Surine, Oakley W.
Partner: UNT Libraries Government Documents Department

Investigation of altitude ignition, acceleration, and steady-state operation with a single combustor of a J47 turbojet engine

Description: From Summary :"An investigation was conducted with a single combustor from a J47 turbojet engine using weathered aviation gasoline and several spark-plug modifications to determine altitude ignition, acceleration, and steady state operating characteristics. Satisfactory ignition was obtained with two modifications of the original opposite-polarity spark plug up to and including an altitude of 40,003 feet at conditions simulating equilibrium windmilling of the engine at a flight speed of 400 miles per hour. At a simulated altitude of 30,000 feet, satisfactory ignition was obtained over a range of simulated engine speeds."
Date: September 22, 1950
Creator: Cook, William P. & Butze, Helmut F.
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

Liquid-fuel-distribution and fuel-state effects on combustion performance of a single tubular combustor

Description: Report presenting an investigation to study the effects of liquid-fuel distribution on combustion performance of a single turbojet-engine combustor operating with liquid MIL-F 5624 fuel. Results regarding altitude limits and combustion efficiencies, liquid-fuel distribution, fuel state, and miscellaneous observations are provided.
Date: May 1, 1951
Creator: McCafferty, Richard J.
Partner: UNT Libraries Government Documents Department

Investigation of three low-temperature-ratio combustor configurations in a 48-inch-diameter ram-jet engine

Description: "A preliminary evaluation was made of three types of combustor configurations in a 48-inch-diameter ram-jet engine to determine the one with the greatest promise of ultimately achieving efficient and stable combustion at low fuel-air rations and low combustor-inlet pressure. The combustor configurations evaluated include (1) a can-piloted configuration using a gutter-type flame holder with can-type pilot burners for stability, (2) an annular-piloted configuration using a gutter-type flame holder with an annular pilot burner to provide stability and to serve as a flow divider for confined fuel-air mixing, and (3) a can-type configuration using a flow divider for confined fuel-air mixing. No modifications were made to optimize the performance of any configuration" (p. 1).
Date: March 10, 1954
Creator: Meyer, Carl L. & Welna, Henry J.
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