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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

The calculated performance of airplanes equipped with supercharging engines

Description: In part one of this report are presented the theoretical performance curves of an airplane engine equipped with a supercharging compressor. In predicting the gross power of a supercharging engine, the writer uses temperature and pressure correction factors based on experiments made at the Bureau of Standards (NACA report nos. 45 and 46). Means for estimating the temperature rise in the compressor are outlined. Part two of this report presents an estimation of the performance curves of an airplane fitted with a supercharging engine. A supercharging installation suitable for commercial use is described, and it is shown that with the use of the compressor a great saving in fuel and a considerable increase in carrying capacity can be effected simultaneously. In an appendix the writer derives a theoretical formula for the correction of the thrust coefficient of an airscrew to offset the added resistance of the airplane due to the slip-stream effect.
Date: 1921
Creator: Kemble, E. C.
Partner: UNT Libraries Government Documents Department

Performance of B. M. W. 185-Horsepower Airplane Engine

Description: "This report deals with the results of a test made upon a B. M. W. Engine in the altitude chamber of the Bureau of Standards, where controlled conditions of temperature and pressure can be made to simulate those of the desired altitude. A remarkably low value of fuel consumption - 041 per B. H. P. hour - is obtained at 1,200 revolutions per minute at an air density of 0.064 pound per cubic foot and a brake thermal efficiency of 33 per cent and an indicated efficiency of 37 per cent at the above speed and density. In spite of the fact that the carburetor adjustment does not permit the air-fuel ratio of maximum economy to be obtained at air densities lower than 0.064, the economy is superior to most engines tested thus far, even at a density lower than 0.064, the economies superior to most engines tested thus far, even at a density (0.03) corresponding to an altitude of 25,000 feet" (p. 1).
Date: 1922
Creator: Sparrow, S. W.
Partner: UNT Libraries Government Documents Department

The relative performance obtained with several methods of control of an overcompressed engine using gasoline

Description: "This report presents some results obtained during an investigation to determine the relative characteristics for several methods of control of an overcompressed engine using gasoline and operating under sea-level conditions. For this work, a special single cylinder test engine, 5-inch bore by 7-inch stroke, and designed for ready adjustment of compression ratio, valve timing and valve lift while running, was used. This engine has been fully described in NACA-TR-250. Tests were made at an engine speed of 1,400 R. P. M. for compression ratios ranging from 4.0 to 7.6" (p. 329).
Date: February 25, 1927
Creator: Gardiner, Arthur W. & Whedon, William E.
Partner: UNT Libraries Government Documents Department

Noise from intermittent jet engines and steady-flow jet engines with rough burning

Description: Report presenting sound measurements on a pulsejet and subsonic ramjet of the types used for helicopter rotor drive and on a turbojet with afterburner. The pulsejet was found to produce a discrete-frequency spectrum having a single predominant component corresponding to the engine firing frequency. The small subsonic ramjet and the turbojet with afterburner were both found to produce discrete-frequency noise spectrums.
Date: August 1952
Creator: Lassiter, Leslie W.
Partner: UNT Libraries Government Documents Department

Turbine Engines for High-Speed Flight

Description: This analysis investigates the application of gas turbine engines at a cruise Mach number of 4. Some of the problems of turbine engines, including cooling and off-design performance of certain components, are explored and feasible solutions to the problems are demonstrated.
Date: 1958
Creator: Henneberry, Hugh M. & Zimmerman, Arthur V.
Partner: UNT Libraries Government Documents Department

Hesselman Heavy-Oil High-Compression Engine

Description: Memorandum presenting a description of the Hesselman heavy-oil high-compression engine, which is meant to solve many of the problems associated with standard diesel engines. Specific details of the fuel pump, fuel valve, spraying, and process by which the engine functions are provided.
Date: April 1925
Creator: Hesselman, K. J. E.
Partner: UNT Libraries Government Documents Department

Crank Case Scavenging of a Two-Stroke-Cycle Engine

Description: "Experiments with a two-stroke-cycle, crank case scavenging engine. Effect of systematic variation of the height of the scavenge and exhaust ports on the scavenging, as determined by gas analysis. The best results were obtained under conditions differing from the usual ones" (p. 1).
Date: January 1928
Creator: Holm, Otto
Partner: UNT Libraries Government Documents Department

Researches on Direct Injection in Internal-Combustion Engines

Description: Report presenting a solution for reducing the fatigue of the Diesel engine by permitting the preservation of its components and, at the same time, raising its specific horsepower to a par with that of carburetor engines, while maintaining for the Diesel engine its perogative of burning heavy fuel under optimum economical conditions. The feeding of Diesel engines by injection pumps actuated by engine compression achieves the required high speeds of injection readily and permits rigorous control of the combustible charge introduced into each cylinder and of the peak pressure in the resultant cycle.
Date: November 1941
Creator: Tuscher, Jean E.
Partner: UNT Libraries Government Documents Department

Some Notes on Gasoline-Engine Development

Description: Experiments were carried out using a special engine with small glass windows and a stroboscope to record various aspects of engine performance. Valve position, supercharging, and torque recoil were all investigated with this experimental apparatus.
Date: July 1927
Creator: Ricardo, H. H.
Partner: UNT Libraries Government Documents Department

Compilation and analysis of U.S. turbojet and ram-jet engine characteristics

Description: Report presenting a compilation of sea-level static and flight-performance data for existing and designed U.S. axial-flow turbojet and ram-jet engines. Factors considered include engine size, performance, and weight, and actual and theoretical performances are compared.
Date: November 27, 1956
Creator: Cesaro, Richard S. & Walker, Curtis L.
Partner: UNT Libraries Government Documents Department

Bagnulo Heavy Fuel Internal Combustion Engine and Its Employment in Aviation

Description: We see with great satisfaction that Bagnulo's studies and experiments on his high-speed, heavy-fuel engines, promise to solve not only the general problem of economical power and hence of thermal efficiency, but also all other special problems, of weight and space, and, what is still more important, range of error.
Date: March 1922
Creator: Fiore, Amedeo
Partner: UNT Libraries Government Documents Department

Instrumentation for recording transient performance of gas-turbine engines and control systems

Description: Report presenting design features for the instrumentation used in a study of the transient performance of gas-turbine engines and control systems. The dynamic characteristics of the instrumentation are discussed and examples of typical acceleration data for a controlled and an uncontrolled engine are provided.
Date: June 27, 1951
Creator: Delio, Gene J. & Schwent, Glennon V.
Partner: UNT Libraries Government Documents Department

The effect of compressor-inlet water injection on engine and afterburner performance

Description: From Summary: "A turbojet engine incorporating a conventional-type afterburner was operated over a range of afterburner pressure levels from 1000 to 2000 pounds per square foot absolute and a range of engine-inlet water-air ratios from 0 to 0.08. At each pressure level and water-air ratio, the afterburner fuel flow was varied from lean blowout to maximum burner-outlet temperature."
Date: July 22, 1958
Creator: Sivo, Joseph N.; Wanhainen, John P. & Jones, William L.
Partner: UNT Libraries Government Documents Department

The significance of the time concept in engine detonation

Description: Report presenting an experimental technique developed by means of which the variables affecting the time element in the detonation process in a spark-ignition engine can be controlled and approximately measured. Results indicated that higher maximum permissible pressures can be used if the rate of compression of the end gas is increased. Suggestions for future study are provided.
Date: January 1943
Creator: Leary, W. A. & Taylor, E. S.
Partner: UNT Libraries Government Documents Department

F-35 Alternate Engine Program: Background and Issues for Congress

Description: This report discusses the past four years of administration proposals to terminate the program to develop the General Electric/Rolls-Royce F136 engine as an alternative to the Pratt & Whitney F135 engine that currently powers the F-35 Joint Strike Fighter (JSF). These proposals have been continually rejected by Congress. The Obama Administration's FY2011 budget submission against proposes to terminate the program. This report explores both sides of the termination argument.
Date: November 10, 2010
Creator: Gertler, Jeremiah
Partner: UNT Libraries Government Documents Department

F-35 Alternate Engine Program: Background and Issues for Congress

Description: This report discusses the past four years of administration proposals to terminate the program to develop the General Electric/Rolls-Royce F136 engine as an alternative to the Pratt & Whitney F135 engine that currently powers the F-35 Joint Strike Fighter (JSF). This report explores both sides of the termination argument.
Date: March 22, 2010
Creator: Gertler, Jeremiah
Partner: UNT Libraries Government Documents Department

F-35 Alternate Engine Program: Background and Issues for Congress

Description: This report discusses the past four years of administration proposals to terminate the program to develop the General Electric/Rolls-Royce F136 engine as an alternative to the Pratt & Whitney F135 engine that currently powers the F-35 Joint Strike Fighter (JSF). These proposals have been continually rejected by Congress. The Obama Administration's FY2011 budget submission against proposes to terminate the program. This report explores both sides of the termination argument.
Date: May 24, 2010
Creator: Gertler, Jeremiah
Partner: UNT Libraries Government Documents Department

F-35 Alternate Engine Program: Background and Issues for Congress

Description: This report discusses the past four years of administration proposals to terminate the program to develop the General Electric/Rolls-Royce F136 engine as an alternative to the Pratt & Whitney F135 engine that currently powers the F-35 Joint Strike Fighter (JSF). These proposals have been continually rejected by Congress. The Obama Administration's FY2011 budget submission against proposes to terminate the program. This report explores both sides of the termination argument.
Date: September 17, 2010
Creator: Gertler, Jeremiah
Partner: UNT Libraries Government Documents Department

F-35 Alternate Engine Program: Background and Issues for Congress

Description: This report discusses the past four years of administration proposals to terminate the program to develop the General Electric/Rolls-Royce F136 engine as an alternative to the Pratt & Whitney F135 engine that currently powers the F-35 Joint Strike Fighter (JSF). These proposals have been continually rejected by Congress. The Obama Administration's FY2011 budget submission against proposes to terminate the program. This report explores both sides of the termination argument.
Date: April 20, 2011
Creator: Gertler, Jeremiah
Partner: UNT Libraries Government Documents Department

F-35 Alternate Engine Program: Background and Issues for Congress

Description: This report discusses the past four years of administration proposals to terminate the program to develop the General Electric/Rolls-Royce F136 engine as an alternative to the Pratt & Whitney F135 engine that currently powers the F-35 Joint Strike Fighter (JSF). These proposals have been continually rejected by Congress. The Obama Administration's FY2011 budget submission against proposes to terminate the program. This report explores both sides of the termination argument.
Date: January 10, 2012
Creator: Gertler, Jeremiah
Partner: UNT Libraries Government Documents Department