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Correlation of isothermal contours formed by penetration of jet of liquid ammonia directed normal to an airstream

Description: Report presenting an investigation to correlate the isothermal contour lines formed downstream of a single jet of liquid ammonia directed normal to an air stream. Criteria are presented to facilitate the design of jet-engine thrust-augmentation systems utilizing the injection of liquid ammonia to cool the air at the compressor inlet.
Date: February 3, 1954
Creator: Fenn, David B.
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

Performance of a Short Combustor at High Altitudes Using Hydrogen Fuel

Description: Report presenting an investigation in the altitude test chamber to evaluate the performance of a 16-inch-long combustor designed for use with gaseous-hydrogen fuel. The investigation covered a range of combustor pressures and simulated altitudes at Mach number 0.8. Results regarding operational characteristics, combustor performance, and temperature profiles are provided.
Date: August 7, 1956
Creator: Sivo, Joseph N. & Fenn, David B.
Partner: UNT Libraries Government Documents Department

Effect of inlet flow distortion on compressor stall and acceleration characteristics of a J65-B-3 turbojet engine

Description: Report presenting an investigation to determine the effects of inlet flow distortion on the compressor stall and engine acceleration characteristics of a J65-B-3 turbojet engine. A sinusoidal circumferential distortion and two abrupt radial tip flow distortions were introduced at the engine inlet at several altitudes and Mach number 0.8. Results regarding the definition of inlet flow distortions, acceleration limits, compressor pressure ratio at stall, fuel flow for stall, and maximum acceleration rate are provided.
Date: November 18, 1955
Creator: Fenn, David B. & Sivo, Joseph N.
Partner: UNT Libraries Government Documents Department

Performance of a short combustor at high altitudes using hydrogen fuel

Description: Performance characteristics of a 16-inch annular-type combustor installed in a full-scale engine using gaseous-hydrogen fuel were obtained at simulated altitudes from 66,000 to 86,000 feet at a flight Mach number of 0.8. Combustion efficiencies of 86 percent were obtained at 86,000 feet (combustor pressure, 420 lb/sq ft abs). Combustor blowout was not encountered during the investigation.
Date: August 7, 1956
Creator: Sivo, Joseph N. & Fenn, David B.
Partner: UNT Libraries Government Documents Department

A method of measuring jet thrust of turbojet engines in flight installations

Description: "Measurement of the jet thrust of a turbojet engine in flight becomes more difficult as the number and complexity of the engine components increase. It is desirable, therefore, that a general correlation of jet thrust be developed which is applicable to a simple direct reading thrustmeter. In view of this need a correlation is presented which is independent of flight conditions and applicable to both non-afterburning and afterburning engines equipped with nonejector type fixed- and variable-area convergent exhaust nozzles" (p. 1)
Date: January 21, 1954
Creator: Sivo, Joseph N. & Fenn, David B.
Partner: UNT Libraries Government Documents Department

Design and performance of flight-type liquid-hydrogen heat exchanger

Description: Report presenting an investigation of a liquid-hydrogen fuel system developed to operate one of the turbojet engines in a twin-engine light bomber at an altitude of 50,000 feet and Mach number 0.75. The heat exchanger was evaluated in an altitude test chamber in conjunction with the complete aircraft fuel system. Results regarding calculated heat-exchanger performance, experimental heat-exchanger performance, and reliability are provided.
Date: August 19, 1957
Creator: Fenn, David B.; Braithwaite, Willis M. & Ordin, Paul M.
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

Combined compressor coolant injection and afterburning for turbojet thrust augmentation

Description: Report presenting a discussion of some of the requirements and of the application of the augmented performance of compressor coolant injection and afterburning in a turbojet engine in a high-speed, high-altitude flight. Results regarding the experimental performance of a combined system and the application of augmented performance to high-speed flight are provided.
Date: September 16, 1954
Creator: Useller, James W.; Huntley, S. C. & Fenn, David B.
Partner: UNT Libraries Government Documents Department

Over-All Performance of J65-B3 Turbojet Engine for Reynolds Number Indices from 0.8 to 0.2

Description: The steady-state over-all performance characteristics of the J65-B3 turbojet engine were determined in an altitude test chamber for four exhaust-nozzle areas at Reynolds number indices of 0.8, 0.4, and 0.2. This range of Reynolds number indices corresponds to a range of altitudes from about sea level to 51,500 feet at a flight Mach number of 0.8. Generalized data are presented to allow calculation of engine performance at any flight condition corresponding to a Reynolds number index within the range investigated. Engine performance calculated from these generalized data is presented for seven altitudes over a range of flight speeds from zero to about 1100 knots. The use of an exhaust nozzle sized to give rated perforce at sea level would permit operation near the point of minimum specific fuel consumption for a wide range of flight conditions and engine speeds.
Date: March 9, 1955
Creator: Fenn, David B. & Jones, William L.
Partner: UNT Libraries Government Documents Department

Turbojet-engine thrust augmentation at altitude by combined ammonia injection into the compressor inlet and afterburning

Description: Report presenting an experimental investigation in the altitude test chamber on an axial-flow turbojet engine at transonic flight conditions to determine the magnitude of thrust augmentation and to ascertain the operational characteristics of a combined augmentation system. Results regarding the augmented engine performance, influence of coolant on afterburner combustion, performance losses, and operational problems are provided.
Date: February 12, 1953
Creator: Useller, James W.; Harp, James L., Jr. & Fenn, David B.
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: Braithwaite, Willis M.; Fenn, David B. & Algranti, Joseph S.
Partner: UNT Libraries Government Documents Department

Effect of inlet temperature on rotating stall and blade vibrations in a multistage axial-flow compressor

Description: Report presenting rotating-stall and blade-vibration data for the first three rotor blade rows of a 13-stage axial-flow compressor at several inlet temperatures. Stall patterns of 1 through 5 stall zones were detected at all inlet temperatures in the equivalent compressor speed ranges between 4600 and 6200 rpm.
Date: August 5, 1955
Creator: Medeiros, Arthur A.; Calvert, Howard F. & Fenn, David B.
Partner: UNT Libraries Government Documents Department

Design and performance of flight-type liquid-hydrogen heat exchanger

Description: Report presenting a liquid-hydrogen fuel system developed to operate one of the turbojet engines in a twin-engine light bomber at an altitude of 50,000 feet and Mach number 0.75. A ram-air heat exchanger was used to vaporize liquid hydrogen. Results regarding calculated heat-exchanger performance, experimental heat-exchanger performance, and reliability are provided.
Date: August 19, 1957
Creator: Fenn, David B.; Braithwaite, Willis M. & Ordin, Paul M.
Partner: UNT Libraries Government Documents Department