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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

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

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

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

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

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

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

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

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

Radial aircraft-engine bearing loads 1: crankpin-bearing loads for engines having nine cylinders per crankpin

Description: From Summary: "Dimensional analysis and the principle of similitude are applied to the computation of the crankpin-bearing loads of radial engines having nine cylinders per crankpin." All values of engine speed up to 5000 rpm and all values of indicated mean effective pressure to 500 pounds per square inch have been charted and presented. The effects of several engine dimensions, including reciprocating weight, rotating weight, connecting-rod length, stroke, bore, and compression ratio on the crankpin-bearing loads are also included.
Date: October 1945
Creator: Shaw, Milton C. & Macks, E. Fred
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

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

Altitude performance of a 20-inch-diameter ram-jet engine investigated in a free-jet facility at Mach number 3.0

Description: Report discussing the performance of a 20-inch-diameter ram-jet engine at Mach number 3.0 over a range of simulated altitudes from 60,500 to 66,500 feet. Information about the maximum combustor efficiency, range of exhaust-nozzle total pressures, lean blow-out, diffuser total-pressure recovery, and internal thrust coefficient is provided.
Date: June 15, 1953
Creator: Smolak, George R. & Wentworth, Carl B.
Partner: UNT Libraries Government Documents Department

The performance of a composite engine consisting of a reciprocating spark-ignition engine, a blow-down turbine, and a steady-flow turbine

Description: Report presenting an analysis of the performance of a composite engine consisting of a reciprocating spark-ignition engine, two superchargers, a blowdown turbine, and a steady-flow turbine. The performance of the configuration was analyzed in order to determine the suitability and cost of design compromises when the size of turbines and superchargers and all gear ratios are assumed fixed. Results regarding the variable-component system, fixed-component system, and auxiliary-propeller system are provided.
Date: October 1947
Creator: Turner, L. Richard & Noyes, Robert N.
Partner: UNT Libraries Government Documents Department

Analytical investigation of fuel-cooled turbine blades with return-flow type of finned coolant passages

Description: From Introduction: "The purpose of this report was to investigate the possible use of engine fuels (hydrogen and methane) as coolants for turbine rotor blades and to determine the pressure-drop characteristics of these coolants for a turbine blade with a more effective coolant-passage configuration than that considered in reference 5 but for the same engine and flight conditions."
Date: June 26, 1957
Creator: Nachtigall, Alfred J & Slone, Henry O
Partner: UNT Libraries Government Documents Department

Analysis of two-spool turboprop-engine characteristics

Description: From Introduction: "The purpose of this report is to present the results of an analytical investigation of the engine characteristics of two-spool engines with high over-all compressor pressure ratio (12.0 at design). Some of the turbine design problems encountered in a single-spool engine with current compressor pressure ratio (7.32 at design) were investigated in reference 1. The investigation was extended in reference 2 to cover the effect of mode of engine operation on the turbine design requirements and engine performance for a single-spool engine with current compressor pressure ratio."
Date: June 3, 1957
Creator: Davison, Elmer H
Partner: UNT Libraries Government Documents Department

Analysis of coolant flow and pressure requirements for a return-flow turbine rotor blade design using hydrogen, helium, or air as coolant

Description: From Introduction: "This report presents the results of an analysis to determine the coolant flow and pressure requirements for a particular return-flow turbine rooter blade design utilizing hydrogen, helium, or air as the coolant."
Date: May 7, 1957
Creator: Slone, Henry O & Donoughe, Patrick L
Partner: UNT Libraries Government Documents Department