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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

Operational characteristics of RA-14 Avon turbojet engine

Description: Report presenting a determination of the windmilling and altitude starting characteristics for the RA-14 Avon turbojet engine over a range of altitudes and flight Mach numbers. Successful ignition and acceleration to idle speed were obtained up to an altitude of 33,000 feet at all Mach numbers and at 45,000 feet for Mach numbers below 0.5 and above 1.0. Results regarding throttle bursts and wave-off-type acceleration and compressor-outlet bleed are also provided.
Date: 1956
Creator: Sivo, Joseph N. & Jones, William L.
Partner: UNT Libraries Government Documents Department

Altitude performance of J71-A-2(600-D1) turbojet engine

Description: From Introduction: "As part of a complete investigation of the J71-A-2(600-D1) turbojet engine conducted in an altitude test chamber at the NACA Lewis laboratory, the steady-state altitude performance, with afterburner inoperative and ejector shroud removed, was obtained and is presented herein. The component performance of the J71-A-2(600-D1) turbojet engine is presented in reference 1. The effects of compressor interstage bleed and adjustable inlet guide vanes on compressor-stall characteristics are described in reference 2."
Date: December 28, 1956
Creator: Smith, Ivan D. & Sivo, Joseph N.
Partner: UNT Libraries Government Documents Department

Evaluation of Altitude-Ignition Characteristics of Three Fuels of Different Volatility in a Turbojet Engine

Description: Report presenting an investigation on a full-scale turbojet engine to obtain the altitude-ignition characteristics of three fuels with different ASTM distillation curves. Two of the fuels had a Reid vapor pressure of 2.7 pounds per square inch and the third had a vapor pressure of 1.7 pounds per square inch. Results regarding the effect of fuel volatility and fuel-air ratio on altitude-ignition and propagation characteristics and effect of altitude variation on altitude ignition and propagation characteristics of fuel 53-39 are provided.
Date: March 10, 1954
Creator: Braithwaite, Willis M. & Sivo, Joseph N.
Partner: UNT Libraries Government Documents Department

Use of highly reactive chemical additives to improve afterburner performance at altitude

Description: Report presenting an investigation in an altitude test chamber to evaluate the use of highly reactive chemicals injected into a turbojet afterburner to promote the combustion process. The chemicals evaluated were commercial hydrogen and aluminum trimethyl. Results regarding the afterburner efficiency, afterburner stability limits, afterburner-outlet total temperature, and an application of the results to other systems are provided.
Date: September 30, 1958
Creator: Wanhainen, John P. & Sivo, Joseph N.
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

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

Description: Report presenting testing of a turbojet engine incorporating a conventional-type afterburner over a range of afterburner pressure levels and engine-inlet water-air ratios. At each pressure level and water-air ratio, the afterburner fuel flow was varied from lean blowout to maximum burner-outlet temperature. Results regarding the effects of water vapor on engine performance, effects of water vapor on afterburner performance, and high Mach number performance with water injection are provided.
Date: July 22, 1958
Creator: Sivo, Joseph N.; Wanhainen, John P. & Jones, William L.
Partner: UNT Libraries Government Documents Department

Effect of unequal air-flow distribution from twin inlet ducts on performance of an axial-flow turbojet engine

Description: Report presenting an investigation in the NACA altitude test chamber to determine the effect of inlet-air-flow distortion on the performance of an axial-flow turbojet engine with simulated twin inlet ducts. Results regarding the pressure and temperature profiles, component performance, overall engine performance, and operational comments are provided.
Date: August 3, 1954
Creator: Walker, Curtis L.; Sivo, Joseph N. & Jansen, Emmert T.
Partner: UNT Libraries Government Documents Department

Altitude evaluation of several afterburner design variables on a J47-GE-17 turbojet engine

Description: From Introduction: "The investigation reported herein presents information on design factors and modifications of the production afterburner for the J47-GE-17 turbojet engine designed for medium temperature operation. The present report is concerned only with the afterburner performance and operating characteristics.Altitude-starting characteristics of two of the configurations in this report are discussed in reference 1."
Date: October 23, 1953
Creator: Braithwaite, Willis M.; Walker, Curtis L. & Sivo, Joseph N.
Partner: UNT Libraries Government Documents Department