A generalized computer code for developing dynamic gas turbine engine models (DIGTEM) [PDF]
This paper describes DIGTEM (digital turbofan engine model), a computer program that simulates two spool, two stream (turbofan) engines. DIGTEM was developed to support the development of a real time multiprocessor based engine simulator being designed ...
Daniele, C. J.
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Dual cycle aircraft turbine engine [PDF]
, 1977 A method and apparatus are presented for improving operating efficiency over broad ranges of flight conditions and for reducing jet engine noise output in takeoff and landing by controlling the airflow entering and exiting the engines.
Nichols, M. R.
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Closure to “Discussions of ‘A Rotating Stall Control System for Turbojet Engines’” (1979, ASME J. Eng. Power, 101, pp. 313–314) [PDF]
, 1979 G. R. Ludwig, J. P. Nenni
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Turbine for ordnance turbojet engine. 2: Cold-air performance with opened stator [PDF]
A single-stage axial-flow turbine was investigated to determine the effect of increased stator throat area on the performance level of a turbojet engine turbine.
Haas, J. E. +2 more
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Design and Operating Factors in the Noise Output of Turbojet Engines
, 1955 Derwent M. A. Mercer
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Discussion: “A Rotating Stall Control System for Turbojet Engines” (Ludwig, G. R., and Nenni, J. P., 1979, ASME J. Eng. Power, 101, pp. 305–313) [PDF]
, 1979 STEPHEN ARNETT
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The design and performance estimates for the propulsion module for the booster of a TSTO vehicle [PDF]
A NASA study of the propulsion systems for possible low-risk replacements for the Space Shuttle is presented. Results of preliminary studies to define the USAF two-stage-to-orbit (TSTO) concept to deliver 10,000 pounds to low polar orbit are described ...
Maldonado, Jaime J. +1 more
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Diffusion Principles for Suppressing Turbojet Exhaust Noise
, 1959 J. A. Sobel
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Identification and dual adaptive control of a turbojet engine [PDF]
, 1981 Walter C. Merrill, GARY LELNINGER
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Emission calibration of a J-58 afterburning turbojet engine at simulated supersonic stratospheric flight conditions [PDF]
Emissions of total oxides of nitrogen, unburned hydrocarbons, and carbon monoxide from a J-58 engine at simulated flight conditions of Mach 2.0, 2.4, and 2.8 at 19.8 km altitude are reported.
Holdeman, J. D.
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