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Calculated Performance of Nuclear Turbojet Powered Airplane at Flight Mach Number of 0.9

Description: "An analysis was made at flight Mach number of 0.9 to estimate performance of nuclear-energy-powered turbojet engine and optimum engine operating conditions and to determine gross weight and load-carrying capacity of airplane powered by such an engine. The size of airplane required to carry disposable load of 20,000 pounds was found to vary from approximately 300,000 to 900,000 pounds depending on assumptions. For a reactor tube-wall mean temperature of 2500 degrees R, turbine-inlet temperature of 2000 degrees R, reactor-free-flow-area ratio of 0.33, reactor-shielding-material specific gravity of 6.0, shielding thickness of 3.0 feet, and altitude of 30,000 feet, the airplane gross weight required to carry a 20,000 payload is 545,000 pounds" (p. 1).
Date: May 11, 1950
Creator: Doyle, Ronald B.
Partner: UNT Libraries Government Documents Department

Altitude Investigation of Gas Temperature Distribution at Turbine of Three Similar Axial-Flow Turbojet Engines

Description: An investigation of the effect of inlet pressure, corrected engine speed, and turbine temperature level on turbine-inlet gas temperature distributions was conducted on a J40-WE-6, interim J40-WE-6, and prototype J40-WE-8 turbojet engine in the altitude wind tunnel at the NACA Lewis laboratory. The engines were investigated over a range of simulated pressure altitudes from 15,000 to 55,000 feet, flight Mach numbers from 0.12 to 0.64, and corrected engine speeds from 7198 to 8026 rpm.
Date: August 6, 1952
Creator: Prince, W. R. & Schulze, F. W.
Partner: UNT Libraries Government Documents Department

Investigation of several techniques for improving altitude starting limits of turbojet engines

Description: Report presenting a study of the altitude-starting limits of a production turbojet engine with an axial-flow compressor and a multiple through-flow combustor. The ignition limits, flame-propagation limits, and acceleration limits of the engine were improved to increase the starting limits to relatively high altitude.
Date: October 29, 1952
Creator: Armstrong, John C. & Wilsted, H. D.
Partner: UNT Libraries Government Documents Department

Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine, 7, Pressure and Temperature Distributions

Description: Temperature and pressure distributions for an original and modified 3000 pound thrust axial flow turbojet engine were investigated. Data are included for a range of simulated altitudes from 5000 to 45000 feet, Mach numbers from 0.24 to 1.08, and corrected engine speeds from 10,550 to 13,359 rpm.
Date: December 10, 1948
Creator: Saari, Martin J. & Prince, William R.
Partner: UNT Libraries Government Documents Department

Performance of two air-cooled turbojet engines determined analytically from engine component performance for a range of cooling-air weight flows

Description: Report presenting an analysis of two turbojet engines, including the component performance of the compressors and turbines, in order to determine the effect on engine performance and operation of bleeding the compressor to furnish cooling air for the turbine rotor blades. Results regarding the compressor and turbine performance characteristics and engine performance characteristics are provided.
Date: February 18, 1954
Creator: Ziemer, Robert R.; Schafer, Louis J., Jr. & Heaton, Thomas R.
Partner: UNT Libraries Government Documents Department

Altitude-Wind-Tunnel Investigation of a 4000-Pound-Thrust Axial-Flow Turbojet Engine, Part 1, Performance and Windmilling Drag Characteristics

Description: From Summary: "The results of altitude-wind-tunnel tests conducted to determine the performance of an axial-flow-type 4000-pound-thrust turbojet engine for a range of pressure altitudes from 5000 to 40,000 feet and ram pressure ratios from 1.02 to 1.86 are presented and the experimental and analytical methods employed are discussed. By means of suitable generalizing factors applied to the measured performance data, curves were obtained from which the engine performance at any altitude for a given ram pressure ratio can be estimated. The data presented include the windmilling drag characteristics of the turbojet engine for the ranges of altitudes and ram pressure ratios covered by the performance data."
Date: August 3, 1948
Creator: Fleming, William A.
Partner: UNT Libraries Government Documents Department

Altitude-Wind-Tunnel Investigation of a 4000-Pound-Thrust Axial-Flow Turbojet Engine. 2 - Operational Characteristics

Description: From Summary: "An investigation was conducted in the Cleveland altitude wind tunnel to determine the operational characteristics of an axial flow-type turbojet engine with a 4000-pound-thrust rating over a range of pressure altitudes from 5,000 to 50,000 feet, ram pressure ratios from 1.00 to 1.86, and temperatures from 60 deg to -50 deg F. The low-flow (standard) compressor with which the engine was originally equipped was replaced by a high-flow compressor for part of the investigation. The effects of altitude and airspeed on such operating characteristics as operating range, stability of combustion, acceleration, starting, operation of fuel-control systems, and bearing cooling were investigated."
Date: August 6, 1948
Creator: Fleming, William A.
Partner: UNT Libraries Government Documents Department

Graphic Analysis of American and British Axial-Flow Turbojet Engine Performance Trends (Current and Future)

Description: From Summary: "This report presents a compilation of static sea-level data on existing or designed American and British axial-flow turbojet engines in terms of basic engine parameters such as thrust and air flow. In the data presented, changes in the over-U engine performance with time are examined as well as the relation of the various engine parameters to each other."
Date: December 10, 1951
Creator: Cesaro, Richard S. & Lazar, James
Partner: UNT Libraries Government Documents Department

Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine 2 - Analysis of Compressor Performance

Description: Compressor performance properties for two 11-stage compressors of 3000-pound-thrust axial-flow turbojet engines were determined. Data are presented for a range of simulated altitudes and a range of Mach numbers for various modifications of the engine.
Date: August 23, 1948
Creator: Dietz, Robert O., Jr.; Berdysz, Joseph J. & Howard, Ephraim M.
Partner: UNT Libraries Government Documents Department

Altitude-Wind-Tunnel Investigation of the 19B-2, 19B-8, and 19XB-1 Jet Propulsion Engines, 4 - Performance and Windmilling Drag Characteristics

Description: The performance characteristics of the 19B-8 and 19XB-1 turbojet engines and the windmilling-drag characteristics of the 19B-6 engine were determined in the Cleveland altitude wind tunnel. The investigations were conducted on the 19B-8 engine at simulated altitudes from 5000 to 25,000 feet with various free-stream ram-pressure ratios and on the 19XB--1 engine at simulated altitudes from 5000 to 30,000 feet with approximately static free-stream conditions.
Date: April 9, 1947
Creator: Fleming, William A. & Dietz, Robert O., Jr.
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

Analytical investigation of the effect of water injection on supersonic turbojet-engine - inlet matching and thrust augmentation

Description: From Introduction: "In order to provide engine-inlet matching to prevent such mass flow spillage and the attendant drags, much mechanical complication has been introduced. References 1 and 2 propose employing this principle at subsonic and supersonic speeds to achieve thrust augmentation. The merits of the system for supersonic engine-inlet airflow matching, as well as thrust augmentation, appear considerable; and a comparative study with existing fixed- and variable-geometry inlets was therefore undertaken."
Date: January 1957
Creator: Beke, Andrew
Partner: UNT Libraries Government Documents Department

Analytical investigation of distribution of centrifugal stresses and their relation to limiting operating temperatures in gas-turbine blades

Description: From Introduction: "Analyses that provide a basis for comparing the centrifugal-stress distributions inherent in jet-engine turbine blades of several designs currently in use were therefore made and are presented."
Date: April 12, 1948
Creator: Kemp, Richard H. & Morgan, William C.
Partner: UNT Libraries Government Documents Department

Analytical method for determining performance of turbojet-engine tail-pipe heat exchangers

Description: From Introduction: "The NACA Lewis laboratory has undertaken a program of analytical study to evaluate the effect on turbojet-engine performance of extracting energy from several points in the cycle. The program included an investigation of the effects of air bleed from the compressor outlet, hot gas bleed from the turbine inlet, hot gas bleed from the turbine outlet, and shaft power extraction (references 1 to 4). "
Date: September 1951
Creator: Behun, Michael & Chandler, Harrison C., Jr.
Partner: UNT Libraries Government Documents Department

Analysis of parameters for thrust control of a turbojet engine equipped with air-inlet throttle and variable-area exhaust nozzle

Description: From Introduction: "In this report, altitude, airplane velocity, exhaust-nozzle area, and turbine-inlet temperature were chosen and corresponding engine speed, fuel flow, and throttle pressure ratio were found. A detailed discussion of the engine analysis and the calculations used are presented in Appendix A. The derivations of the principal equations used are presented in appendix B."
Date: August 10, 1948
Creator: Boksenbom, Aaron S. & Feder, Melvin S.
Partner: UNT Libraries Government Documents Department

Analysis of several methods of pumping cooling air for turbojet engine afterburners

Description: From Introduction: "Afterburning is well established as an effective means of increasing the thrust of a turbojet engine. In order to obtain the maximum thrust from an afterburner, it is necessary to burn to the highest temperatures possible (reference 1). At these high temperatures, material limitations (reference 2) necessitate the installation of cooling systems to permit safe and reliable operation."
Date: February 2, 1953
Creator: Samuels, John C. & Yanowitz, Herbert
Partner: UNT Libraries Government Documents Department

Component and over-all performance evaluation of a J47-GE-25 turbojet engine over a range of engine-inlet Reynolds number indices

Description: Report presenting an investigation in the altitude test chamber to evaluate the performance of an axial-flow turbojet engine over a range of engine-inlet Reynolds number indices. Secondary effects of exhaust-nozzle flow coefficient, air-flow leakage, and inlet temperature should be considered before analyzing the effect of variations in engine-inlet Reynolds number index. Several minor design modifications proposed by the manufacturer did not produce any measurable improvement in engine performance.
Date: September 29, 1953
Creator: Walker, Curtis L.; Braithwaite, Willis M. & Fenn, David B.
Partner: UNT Libraries Government Documents Department

Component performance of J71-A-2(600-D1) turbojet engine at several Reynolds number indices

Description: Report presenting an investigation in the altitude test chamber to determine the altitude performance of the J71-A-2(600-D1) turbojet engine. The engine was equipped with two-position inlet guide vanes and compressor acceleration bleeds. Results regarding the compressor performance, combustor performance, turbine performance, and effect of altitude on engine performance are provided.
Date: December 28, 1956
Creator: Seashore, Ferris L. & Corrington, Lester C.
Partner: UNT Libraries Government Documents Department

Determination of surge and stall limits of an axial-flow turbojet engine for control applications

Description: Report presenting an investigation of an axial-flow turbojet engine in the altitude wind tunnel, including limitations on transient operation of the engine in relation to two altitudes and exhaust-nozzle-areas. Results regarding hysteresis, frequency of surge and stall, altitude effect, exhaust-nozzle-area effect, and a comparison of steady-state and transient surge lines are provided.
Date: September 1957
Creator: Schmidt, Ross D.; Vasu, George & McGraw, Edward W.
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

Calibration of Air-Flow Meters for J33 Compressor Investigation

Description: Flow-metering devices used by the NACA and by the manufacturer of the J33 turbojet engine were calibrated together to determine whether an observed discrepancy in weight flow of approximately 4 percent for the two separate investigations might be due to the different devices used to meter air flow. A commercial adjustable orifice and a square-edge flat-plate orifice used by the NACA and a flow nozzle used by the manufacturer were calibrated against surveys across the throat of the nozzle. It was determined that over a range of weight flows from 18 to 45 pounds per second the average weight flows measured by the metering device used for the compressor test would be 0.70 percent lower than those measured by the metering device used in the engine tests and the probable variation about this mean would be +/- 0.39 percent. The very close agreement of the metering devices shows that the greater part of the discrepancy in weight flow is attributable to the effect of inlet pressure.
Date: August 16, 1948
Creator: Kovach, Karl & Withee, Joseph R., Jr.
Partner: UNT Libraries Government Documents Department

Relation of turbojet propulsion system development to the strategic bomber mission

Description: From Summary: "A generalized analysis presents the effects of turbojet propulsion system development and fuel selection on ability of a strategic bomber to perform desired and minimum missions. The variation of bomber performance using a hydrocarbon, boron, or nuclear fuel is discussed. With chemical fuel, the effects of refueling are discussed. With nuclear fuel, the nuclear cruise-chemical dash bomber and the nuclear subsonic tug towing a chemically powered supersonic bomber are compared."
Date: August 15, 1956
Creator: Rothrock, Addison M.; Cesaro, Richard S. & Walker, Curtis L.
Partner: UNT Libraries Government Documents Department

Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine, Part 5, Performance and Windmilling Drag Characteristics

Description: "An investigation has been conducted in the NACA Cleveland altitude wind tunnel to evaluate the performance and windmilling drag characteristics of an original and a modified turbojet engine of the same type. Data have been obtained at simulated altitudes from 5000 to 45,000 feet, simulated flight Mach numbers from 0.09 to 1.08, and engine speeds from 4000 to 12,500 rpm. Engine performance data are presented for both engines to show the effects of altitude at a flight Mach number of 0.25 and of flight Mach number at an altitude of 25,000 feet" (p. 1).
Date: August 23, 1948
Creator: Meyer, Carl L. & Bloomer, Harry E.
Partner: UNT Libraries Government Documents Department