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Evaluation of hydrogen fuel in a full-scale afterburner

Description: Report presenting a performance investigation using hydrogen fuel in a full-scale afterburner with particular study of fuel-injector configurations and afterburner length. A total of seven fuel-injector configurations, some concentric ring and some radial bar, were investigated at a specified burner inlet velocity over a range of burner-inlet total pressures.
Date: September 24, 1957
Creator: Groesbeck, Donald E.; Prince, William R. & Ciepluch, Carl C.
Partner: UNT Libraries Government Documents Department

A low-pressure-loss short afterburner for sea-level thrust augmentation

Description: Report presenting an investigation of the problems associated with the design of a low-pressure-loss, short afterburner for sea-level thrust augmentation in a static, sea-level test stand using the power section of a 5970-pound-thrust, axial-flow turbojet engine. The various portions of the afterburner and procedures used to test it are described. Results regarding diffuser pressure losses, afterburner pressure losses, and afterburner performance are provided.
Date: June 7, 1955
Creator: Ciepluch, Carl C.; Velie, Wallace W. & Burley, Richard R.
Partner: UNT Libraries Government Documents Department

Effect of pressure level on afterburner-wall temperatures

Description: Report presenting an investigation conducted on a full-scale afterburner and turbojet engine to determine the effect of pressure level on afterburner-wall temperature. The purpose behind the investigation was to investigate the idea that luminous radiation from nongaseous substances in the afterburner gas stream might be present and vary significantly with pressure.
Date: June 11, 1958
Creator: Shillito, Thomas B. & Smolak, George R.
Partner: UNT Libraries Government Documents Department

Experimental Investigation of Effects of Combustion-chamber Length and Inlet Total Temperature, Total Pressure, and Velocity on Afterburner Performance

Description: Report presenting an investigation of the effects of afterburner-inlet total temperature, total pressure, velocity, fuel-air ratio, and afterburner combustion-chamber length on afterburner performance and stability limits using a cylindrical afterburner installed in a duct test rig. The afterburner was investigated over a range of total temperature, total pressure, velocity, and afterburner fuel-air ratios.
Date: June 3, 1957
Creator: King, Charles R.
Partner: UNT Libraries Government Documents Department

Effect of pressure level on afterburner-wall temperatures

Description: Report presenting an investigation conducted on a full-scale afterburner and turbojet engine to determine the effect of pressure level on afterburner-wall temperature. For a given ratio of cooling airflow to afterburner gas flow, the afterburner-wall temperature increased as afterburner-outlet pressure was increased. The results indicated that heat transfer by luminous radiation was not significant any pressure level investigated.
Date: June 11, 1958
Creator: Shillito, Thomas B. & Smolak, George R.
Partner: UNT Libraries Government Documents Department

Effect of diffuser design, diffuser-exit velocity profile and fuel distribution on altitude performance of several afterburner configurations

Description: "An investigation was conducted in the NACA Lewis altitude wind tunnel to improve the altitude performance and operational characteristics of an afterburner primarily by modifying the diffuser-exit velocity profile by changes in diffuser design and by changing the fuel distribution and the flame holder. Twenty configurations, consisting of combinations of six diffuser geometries, six flame-holder types, and twelve fuel systems, were investigated. Data were obtained over a range of afterburner fuel-air ratios at diffuser-inlet total pressures from 2750 to 620 pounds per square foot" (p. 1).
Date: July 9, 1953
Creator: Conrad, E. William; Schultz, Frederick W. & Usow, Karl H.
Partner: UNT Libraries Government Documents Department

Experimental investigation of screeching combustion in full-scale afterburner

Description: Report presenting an investigation using a number of systematic configuration modifications to an afterburner to determine their effect on screech characteristics. The modifications included changes in the afterburner diffuser, the fuel system, and the flame holder. Results regarding some of the characteristics of screeching combustion, effect of diffuser flow conditions, and effect of fuel system and flame holder are provided.
Date: December 4, 1953
Creator: Usow, Karl H.; Meyer, Carl L. & Schulze, Frederick W.
Partner: UNT Libraries Government Documents Department

A study of flame-holder elements for use in high-velocity afterburners

Description: Report presenting an investigation of a total of 31 flame-holder elements that can be classified into 7 distinct types under simulated afterburner operating conditions to determine their merit and feasibility for use in a high-velocity gas stream. The results indicated that a screen-type flame holder could far exceed the velocity limits of the same size conventional V-gutter at fuel-air ratios below about 0.045.
Date: February 23, 1955
Creator: Conrad, Earl William; Velie, Wallace W. & Schulze, Frederick W.
Partner: UNT Libraries Government Documents Department

Cooling characteristics of a transpiration-cooled afterburner with a porous wall of brazed and rolled wire cloth

Description: Report presenting cooling data for a transpiration-cooled afterburner with a porous combustion-chamber wall of brazed and and rolled wire cloth for a range of exhaust-gas temperatures, total flow ratios of cooling air to combustion gas, and pressure altitudes. Results regarding typical data, cooling correlation, transpiration-cooling performance, comparison of transpiration and forced-convection cooling, and pressure environment of the wire cloth are provided.
Date: August 19, 1954
Creator: Koffel, William K.
Partner: UNT Libraries Government Documents Department

Performance Characteristics of a 24 Degree Straight-Outer-Wall Annular-Diffuser-Tailpipe Combination Utilizing Rectangular Vortex Generators for Flow Control

Description: An investigation of the performance characteristics of annular-diffuser designs applicable to turbojet afterburners. The best vortex-generator installations improved the diffuser static-pressure rise and downstream radial distributions without significantly altering the loss coefficients. Results regarding the axial inlet flow and whirling inlet flow are provided.
Date: October 6, 1953
Creator: Wood, Charles C. & Higginbotham, James T.
Partner: UNT Libraries Government Documents Department

Investigation of noise field and velocity profiles of an afterburning engine

Description: Report presenting sound pressure levels, frequency spectrum, and jet velocity profiles for an engine-afterburner combination at various values of afterburner fuel-air ratio. Lower sound pressure levels were obtained from a current fighter aircraft with a different afterburner configuration. Results regarding the jet temperature, jet Mach number and velocity, and sound measurements are provided.
Date: September 24, 1954
Creator: North, Warren J.; Callaghan, Edmund E. & Lanzo, Chester D.
Partner: UNT Libraries Government Documents Department

Altitude-wind-tunnel investigation of several afterburner configurations having moderately high burner-inlet velocities

Description: From Introduction: "The screech investigation, reported in reference 1, included a large number of afterburner configurations. Several of these configurations are presented herein to show the effects of afterburner-inlet gas whirl pattern, flame-holder design, and fuel distribution on performance as determined by combustion efficiency, augmented thrust ratio, and special fuel consumption."
Date: November 17, 1954
Creator: Schulze, F. W.; Bloomer, H. E. & Miller, R. R.
Partner: UNT Libraries Government Documents Department

Influence of combustion-chamber length on afterburner performance

Description: Report presenting an investigation of the influence of combustion-chamber length on afterburner performance under conditions simulating altitude flight. The component design and arrangement were selected from the results of previous investigations to produce maximum thrust augmentation near the stoichiomtric condition. Results regarding afterburner-inlet conditions, operational limits, and structural cooling requirements are provided.
Date: August 27, 1954
Creator: Useller, James W.; Braithwaite, Willis M. & Rudey, Carl J.
Partner: UNT Libraries Government Documents Department

Afterburner performance with combustion-chamber lengths from 10 to 62 inches at several afterburner-inlet temperatures

Description: Report presenting an investigation to determine the effect of variation of afterburner combustion-chamber length and inlet temperature on a low-pressure-loss sea-level afterburner.
Date: February 1956
Creator: Ciepluch, Carl C.; Velie, Wallace W. & Burley, Richard R.
Partner: UNT Libraries Government Documents Department

An investigation of effects of flame-holder gutter shape on afterburner performance

Description: Report presenting an investigation of the effect of flame-holder gutter cross-sectional shape on afterburner performance in an afterburner test rig. Fuel-air distribution and burner inlet temperature were held as constant as possible for all of the shapes. Results regarding the burner flow conditions, typical performance characteristics, and effect of flame-holder gutter shape on combustion efficiency, pressure loss, and stability limits are provided.
Date: February 10, 1954
Creator: Nakanishi, S.; Velie, W. W. & Bryant, L.
Partner: UNT Libraries Government Documents Department

Tests with hydrogen fuel in a simulated afterburner

Description: Report presenting an investigation in a 16-inch-diameter simulated afterburner using gaseous hydrogen fuel. Results regarding combustion efficiency, afterburner pressure losses, spontaneous ignition, and a heat-balance check are provided.
Date: July 2, 1956
Creator: Kerslake, W. R. & Dangle, E. E.
Partner: UNT Libraries Government Documents Department

Tests with hydrogen fuel in a simulated afterburner

Description: From Summary: "An investigation was conducted in a 16-inch-diameter simulated afterburner using gaseous hydrogen fuel. No flameholder was used with a multipoint fuel injector. The burner length was varied from 9.5 to 38 inches. The afterburner-inlet conditions were: temperature of 1200 degrees or 1500 degrees F, pressure of 14 to 44 inches mercury absolute, and velocity of 300 to The measured combination efficiency ranged from 85 to 98 percent over an equivalence-ratio range of 0.2 to 1.0. The cold-flow pressure-drop coefficient was 1.0 for the system. Spontaneous ignition was always possible at temperatures above 1200 degrees F but was not possible at temperatures above 1200 degrees F but was not possible below 1100 degrees F for all pressures and velocities tested."
Date: July 2, 1956
Creator: Kerslake, W. R. & Dangle, E. E.
Partner: UNT Libraries Government Documents Department

Investigation of ram-jet afterburning as a means of varying effective exhaust nozzle area

Description: Report presenting a discussion of the flow mechanism in an afterburner extension to a ramjet engine. An experimental evaluation of the operation of 16-inch ramjet equipped with an afterburner at Mach number 1.8 and 2.0 in the supersonic wind tunnel. The experimental data confirmed the proposed method of afterburner operation.
Date: November 17, 1952
Creator: Perchonok, Eugene & Wilcox, Fred A.
Partner: UNT Libraries Government Documents Department

Experimental investigation of ejector-nozzle metal temperatures

Description: Metal temperatures were obtained on a full-scale ejector nozzle installed on an afterburner operating at exhaust-gas temperatures up to 3450 degrees R. A favorable afterburner-outlet temperature profile helped keep the primary-jet nozzle components cool. The ejector shroud temperatures were much more sensitive to secondary airflow than were temperatures on the primary-jet nozzle.
Date: February 27, 1957
Creator: Shillito, Thomas B. & Koffel, William K.
Partner: UNT Libraries Government Documents Department

Experimental sea-level static investigation of a short afterburner

Description: Report presenting a sea-level static investigation to determine the performance and some design principles for a short afterburner. The power section of a 12-stage axial-flow turbojet engine was used and the afterburner was designed to fit within the length required for the tail pipe used on the standard nonafterburning model.
Date: May 11, 1954
Creator: Harp, James L.; Shillito, Thomas B. & Mallett, William E.
Partner: UNT Libraries Government Documents Department

Altitude Performance of the Afterburner on the Iroquois Turbojet Engine. Coord. No. AF-P-6

Description: "The performance and operational characteristics of two afterburner configurations for the Iroquois turbojet engine were evaluated in an altitude test chamber over a range of afterburner equivalence ratios at afterburner-inlet pressures from 733 to 3186 pounds per square foot absolute. These conditions correspond to an altitude range from 38,700 to 66,800 feet at a flight Mach number of 1.5. The only difference between the two afterburner configurations was in the pattern of afterburner fuel injection. At an afterburner-inlet pressure of approximately 3100 pounds per square foot absolute, corresponding to an altitude of 38,700 feet and a flight Mach number of 1.5, the combustion efficiency of both configurations reached peak values of 0.80 to 0.85 at equivalence ratios of 0.35 to 0.40" (p. 1).
Date: July 28, 1958
Creator: Groesbeck, Donald E. & Peters, Daniel J.
Partner: UNT Libraries Government Documents Department

Preliminary Internal Performance Data for a Variable-Ejector Assembly on the XJ79-GE-1 Turbojet Engine, 2, Afterburning Configurations

Description: Internal performance of an XJ79-GE-1 variable ejector was experimentally determined with the primary nozzle in two representative after-burning positions. Jet-thrust and air-handling data were obtained in quiescent air for 4 selected ejector configurations over a wide range of secondary to primary airflow ratios and primary-nozzle pressure ratios. The experimental ejector data are presented in both graphical and tabulated form.
Date: July 30, 1957
Creator: Bloomer, Harry E. & Groesbeck, Donald E.
Partner: UNT Libraries Government Documents Department

Preliminary experimental investigation of transpiration cooling for an afterburner with a sintered, porous stainless-steel combustion-chamber wall

Description: Report presenting an experimental investigation of the application of transpiration air-cooling to the combustion-chamber wall of an afterburner. Results regarding the typical temperature and pressure profiles, correlation of wall temperatures, distribution of cooling-air flux density, longitudinal distribution of cooling air, longitudinal distribution of wall temperature, effect of permeability on cooling-air requirements, and fabricating and operating problems are provided.
Date: June 8, 1953
Creator: Koffel, William K.
Partner: UNT Libraries Government Documents Department

Empirical cooling correlation for an experimental afterburner with an annular cooling passage

Description: Report presenting an empirical cooling correlation for an experimental high-performance afterburner. The correlation equation is useful for shortening the experimental investigation of afterburner cooling characteristics inasmuch as it provides a method for interpolating the critical wall temperatures for other combinations of operating variables.
Date: June 26, 1952
Creator: Koffel, William K. & Kaufman, Harold R.
Partner: UNT Libraries Government Documents Department