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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: 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). 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: 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). 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

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

Acoustic analysis of ram-jet buzz

Description: From Introduction: "The surging of a system containing a centrifugal- or axial-flow compressor (e.g., refs. 1 to 4) is an example of self-sustained oscillation. Inlets designed for supersonic jet engines also have been observed to induce oscillations (e.g., refs. 5 to 11) which are usually referred to as "buzz." The origin of buzz in ram-jet engines is the subject of the present report."
Date: November 1955
Creator: Mirels, Harold
Partner: UNT Libraries Government Documents Department

Adaptation of aeronautical engines to high altitude flying

Description: Report discussing Issues and techniques relative to the adaptation of aircraft engines to high altitude flight. Covered here are the limits of engine output, modifications and characteristics of high altitude engines, the influence of air density on the proportions of fuel mixtures, methods of varying the proportions of fuel mixtures, the automatic prevention of fuel waste, and the design and application of air pressure regulators to high altitude flying. Summary: 1. Limits of engine output. 2. High altitude engines. 3. Influence of air density on proportions of mixture. 4. Methods of varying proportions of mixture. 5. Automatic prevention of fuel waste. 6. Design and application of air pressure regulators to high altitude flying.
Date: May 1923
Creator: Kutzbach, K
Partner: UNT Libraries Government Documents Department

Acoustic, thrust, and drag characteristics of several full-scale noise suppressors for turbojet engines

Description: From Introduction: " Considerable analytical and experimental research has been done to find means of reducing the noise levels of the turbojet transports. Noise levels can be decreased by engine redesign to reduce the jet-exit velocity (ref. 1), proper flight-climb techniques (ref. 2), and the use of noise-suppression exhaust nozzles (refs. 3 to 5). The present report is concerned with the last method."
Date: April 1958
Creator: Ciepluch, Carl C; North, Warren J; Coles, Willard D & Antl, Robert J
Partner: UNT Libraries Government Documents Department

Aerodynamic control of supersonic inlets for optimum performance

Description: From Introduction: "The purpose of this paper is to discuss and evaluate some of the input signals or control parameters which have been experimentally employed to operate turbojet inlet-control systems. These include the normal-shock position, the oblique-shock position, and the diffuser-exit Mach number. The discussion is based on results obtained at the NACA Lewis laboratory during control investigations of ram-jet engines (ref. 1 to 5) and during a study on the control of a supersonic inlet for the J34 turbojet engine (refs 6 and 7)."
Date: February 20, 1956
Creator: Wilcox, Fred A. & Perchonok, Eugene
Partner: UNT Libraries Government Documents Department

Air-consumption parameters for automatic mixture control of aircraft engines

Description: From Introduction: "The purpose of this analysis was to investigate the use of a function of intake-manifold pressure, exhaust back pressure, intake manifold temperature, and engine speed in place of a venturi as a means of measuring engine air consumption and to determine if this function is suitable for automatic mixture control."
Date: September 1, 1944
Creator: Shames, Sidney J
Partner: UNT Libraries Government Documents Department

Air-consumption parameters for automatic mixture control of aircraft engines

Description: From Introduction: "The purpose of this analysis was to investigate the use of function of intake-manifold temperature and pressure, exhaust back pressure, and engine speed in place of a ventri as a means of measuring engine air consumption and to determine if this function is suitable for automatic mixture control."
Date: September 1944
Creator: Shames, Sidney J
Partner: UNT Libraries Government Documents Department

Air admixture to exhaust jets

Description: From Introduction: "The problem of thrust increase for jet engines by air mixture to the exhaust jet was introduced into aviation techniques by the suggestions of Melot (ref.1). Due to a too general interpretation of several theoretical investigations of A. Busemann (ref.2), so far no practical use has been made of these suggestions. The following considerations show that, in the case of low-pressure mixing according to Melot's suggestions, probably no thrust increase of technical significance will occur for the flight speeds of interest (however, the low-pressure mixture is highly promising for ground test setups and for special power plants of relatively slow sea and land vehicles."
Date: July 1953
Creator: Sanger, Eugen
Partner: UNT Libraries Government Documents Department

Altitude performance characteristics of tail-pipe burner with variable-area exhaust nozzle

Description: From Introduction: "Data are presented to show the effects of tail-pipe fuel-air ratio, altitude, and flight Mach number on tail-pipe-burner performance at rated engine speed and approximately constant turbine-outlet temperature. Operational characteristics of the tail-pipe burner and variable-area exhaust nozzle are also reported."
Date: August 11, 1950
Creator: Jansen, Emmert T & Thorman, H Carl
Partner: UNT Libraries Government Documents Department

Altitude-performance and Reynolds number investigation of centrifugal-flow-compressor turbojet engine

Description: From Introduction: "Altitude-chamber and wind-tunnel investigations of the performance of turbojet engines such as those reported in references 1 to 4 have shown that the conventional correction factors fail to generalize the engine performance variables at high altitudes. An investigation was therefore made at the NACA Lewis laboratory to determine the altitude performance of the J33-A-23 turbojet engine and to demonstrate the magnitude of departure of actual altitude performance from that predicted from sea-level performance."
Date: May 15, 1951
Creator: Wilsted, H D & Grey, R E
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics of a 4-engine monoplane showing comparison of air-cooled and liquid-cooled engine installations

Description: From Introduction: "An investigation has been conducted in the N.A.C.A. full-scale wind tunnel to determine the aerodynamic characteristics of a 1/4-scale model of a 4-engine monoplane when equipped with comparable air-cooled engine and liquid-cooled engine installations. The air-cooled engine installation consisted of nacelles equipped with N..A.C.A. cowlings and oil coolers located in the leading edge of the wing."
Date: July 1939
Creator: Wilson, Herbert A , Jr & Silverstein, Abe
Partner: UNT Libraries Government Documents Department

Altitude performance of a full-scale turbojet engine using pentaborane fuels

Description: From Introduction: "The data presented herein include the standard engine performance parameters of net thrust, specific fuel consumption, and engine total-pressure ratio that reflect the performance available from the use of pentaborane as a fuel. The influence of the boric oxide deposits from the high-concentration pentaborane fuels on engine component performance is presented."
Date: February 28, 1957
Creator: Useller, James W; Kaufman, Warner B & Jones, William L
Partner: UNT Libraries Government Documents Department

Altitude chamber evaluation of an aircraft liquid hydrogen fuel system used with a turbojet engine

Description: From Introduction: "The objective of this report are (1) to describe the complete fuel system, (2) to discuss the procedure used for transitions between JP-4 fuel and hydrogen, and (3) to present and discuss engine performance obtained with both fuels, and (4) to review the reliability of the fuel system."
Date: August 19, 1957
Creator: Algranti, J. S.; Braithwaite, W. M. & Fenn, D. B.
Partner: UNT Libraries Government Documents Department

Altitude performance of a turbojet engine using pentaborane fuel

Description: From Summary: "The primary objectives of the investigation reported herein were to determine the effect of this new combuster design on boric oxide deposition on engine parts and to determine the effect of boric oxide on the performance of multistage turbine. Pentaborance fuel (approx. 130 lb) was used in the engine performance evaluation reported herein. The data presented herein show the engine component and over-all performance deterioration with operation on pentaborane fuel".
Date: May 20, 1957
Creator: Sivo, Joseph N
Partner: UNT Libraries Government Documents Department