2,484 Matching Results

Search Results

Advanced search parameters have been applied.

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

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

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

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

Scavenging a piston-ported two-stroke cylinder

Description: An investigation was made with a specially designed engine to determine the scavenging characteristics of a large number of inlet-port shapes and arrangements and the optimum port arrangement and timing for this particular type of engine. A special cylinder construction permitted wide variations in timing for this particular type of engine. A special cylinder construction permitted wide variations in timing as well as in shape and arrangement of both the inlet and exhaust ports. The study of the effect of port shape combinations and timings on engine performance was made using illuminating gas as a fuel. Through variations in inlet-port arrangement and port timings, the value of the scavenging efficiency was increased from an original 44 percent to approximately 67 percent with a corresponding increase in power. With the optimum port arrangement and timing determined, a large number of performance runs were made under both spark-ignition and compression-ignition operation.
Date: November 1938
Creator: Rogowski, A. R. & Bouchard, C. L.
Partner: UNT Libraries Government Documents Department

Compression-ignition engine performance at altitudes and at various air pressures and temperatures

Description: From Summary: "Engine test results are presented for simulated altitude conditions. A displaced-piston combustion chamber on a 5- by 7-inch single cylinder compression-ignition engine operating at 2,000 r.p.m. was used. Inlet air temperature equivalent to standard altitudes up to 14,000 feet were obtained. Comparison between performance at altitude of the unsupercharged compression-ignition engine compared favorably with the carburetor engine."
Date: November 1937
Creator: Moore, Charles S. & Collins, John H., Jr.
Partner: UNT Libraries Government Documents Department

Analytical comparison of a standard turbojet engine, a turbojet engine with a tail-pipe burner, and a ram-jet engine

Description: From Introduction: "Experimental investigations (reference 1) have shown that in some cases the thrust can be more than doubled by means of tail-pipe burning. A comparison is made of a standard turbojet engine, whose thrust is augmented by tail-pipe burning, and a ram-jet engine. The performance characteristics for the ram-jet engine were computed entirely from theoretical considerations and on the assumption that the burner-inlet velocity was constant."
Date: February 10, 1947
Creator: Krebs, Richard P & Palasics, John
Partner: UNT Libraries Government Documents Department

Preliminary Transient Performance Data on the J73 Turbojet Engine 2 - Altitude, 35,000 Feet

Description: A program was undertaken to determine the J73 turbojet engine compressor stall and surge characteristics and combustor blow-out limits encountered during transient engine operation. Data were obtained in the form of oscillograph traces showing the time history of several engine performance parameters with changes in engine fuel flow. The data presented in this report are for step changes in fuel flow at an altitude of 35,000 feet, at flight Mach numbers of 0.3, 0.8, and 1.2, and at several engine-inlet temperatures,.
Date: July 16, 1953
Creator: Lubick, Robert J. & Sobolewski, Adam E.
Partner: UNT Libraries Government Documents Department

Method of matching components and predicting performance of turbine-propeller engine

Description: Report presenting equations derived for the equilibrium operation of a turbine-propeller engine in terms of parameters used in turbine- and compressor-performance maps. By use of the analytical relations, geometric, thermodynamic, and aerodynamic relations among compressor, turbine, and exhaust nozzle may be calculated.
Date: September 1951
Creator: Sutor, Alois T. & Zipkin, Morris A.
Partner: UNT Libraries Government Documents Department

Free-jet tests of a 6.5-inch-diameter ram-jet engine at Mach numbers 1.81 and 2.00

Description: Report presenting testing of a 6.5-inch-diameter ramjet engine with a design Mach number of 2.13 and a short-flame-length combustor. Performance characteristics are provided for a range of Mach numbers and fuel-air ratios. Results regarding thrust, drag tests, static pressure, and combustion efficiencies are provided.
Date: March 7, 1951
Creator: Faget, Maxime A.; Watson, Raymond S. & Bartlett, Walter A., Jr.
Partner: UNT Libraries Government Documents Department

Investigation of power extraction characteristics and braking requirements of a windmilling turbojet engine

Description: Report presenting an investigation in an altitude chamber to determine the power extraction and braking characteristics of a windmilling single-spool axial-flow turbojet engine of the 5000-pound thrust class over a range of altitudes and Mach numbers. Results regarding extractable horsepower from a windmilling engine, total pressure gradient through a windmilling engine, contribution of a compressor to extracted horsepower, and braking of the windmilling engine are provided.
Date: July 15, 1952
Creator: Walker, Curtis L. & Fenn, David B.
Partner: UNT Libraries Government Documents Department

Effect of design changes of operating conditions on combustion and operational performance of a 28-inch diameter ram-jet engine

Description: Report presenting an investigation of the altitude performance of a 28-inch diameter ram-jet engine using a direct-connect system in an altitude test chamber. The majority of the investigation occurred at Mach number 2 at altitudes above the tropopause (250 degrees Fahrenheit inlet temperature). Various design configurations were explored and runs were made with different types of fuel.
Date: February 13, 1952
Creator: Shillito, T. B. & Nakanishi, Shigeo
Partner: UNT Libraries Government Documents Department

Design of Combustor for Long-Range Ram-Jet Engine and Performance of Rectangular Analog

Description: The report describes the design of a piloted combustor intended for a ram-jet engine of long flight range. The unit comprises a large annular basket of V-type cross-section, the inner surface of which is slotted and bent into small V-gutters. At the trailing edge of the basket, eight V-gutters are used to propagate the flame into the main stream. A rectangular analog of this combustor was tested at air-flow conditions corresponding to those that might be obtained during cruise. At these conditions, combustion efficiencies of as much as 90 percent were calculated for the combustor at the design equivalence ratio of 0.52. The performance of the unit was relatively insensitive to mounting and flow variables; the greatest effect on efficiency was that of the manner and location of the fuel injection. A full-scale version of this combustor has been designed for a 48-inch-diameter engine.
Date: January 29, 1954
Creator: Rayle, Warren D. & Koch, Richard G.
Partner: UNT Libraries Government Documents Department