Pratt and Whitney Aircraft Nuclear JT-11 Turbojet Engine Performance with Advanced Nuclear System
, 1959 J. W. Larson
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Mach 5 inlet CFD and experimental results [PDF]
An experimental research program was conducted in the NASA Lewis Research Center 10 x 10 ft supersonic wind tunnel. The 2-D inlet model was designed to study the Mach 3.0 to 5.0 speed range for an over-under turbojet plus ramjet propulsion system.
Reddy, D. R. +2 more
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Durability of zirconia thermal-barrier ceramic coatings on air-cooled turbine blades in cyclic jet engine operation [PDF]
Thermal barrier ceramic coatings of stabilized zirconia over a bond coat of Ni Cr Al Y were tested for durability on air cooled turbine rotor blades in a research turbojet engine.
Jacobs, R. E. +3 more
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On the effects of flight on jet engine exhaust noise [PDF]
Differences between flight data and predictions of jet engine exhaust noise were reconciled by considering the combined effects of jet mixing noise and internally generated engine exhaust noise.
Stone, J. R.
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A computer program for calculating design and off-design performance for turbojet and turbofan engines [PDF]
, 1973 Program uses component performance maps to enable user to do analytical engine cycle calculations. Through scaling procedure, each of the component maps can be used to represent a family of maps.
Fishbach, L. H., Koenig, R. W.
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Engineering Proposal for Design and Development Work on a Nuclear Turbojet Propulsion Unit
, 1960 B. A. Schmickrath
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Effect of afterburner lights and inlet unstarts on a mixed compression inlet turbofan engine operating at Mach 2.5 [PDF]
Data are presented to show the response of an uncontrolled inlet to afterburner lightoff disturbances when a mixed-compression inlet is coupled to a turbofan engine.
Batterton, P. G. +2 more
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Fuzzy Logic Control of Compressor Surge in a Turbojet Engine Model [PDF]
, 2021 Mark Laderman
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Engineering Transactions, 1991 The relations are derived enabling to estimate the acceleration time of the turbojet engine rotor set. The terms are established allowing for the determination of the effect of individual operational and structural engine parameters upon the time needed
M. Orkisz
doaj
Performance of an annual combustor designed for a low-cost turbojet engine [PDF]
Performance tests were conducted on a combustor designed for use in a low-cost turbojet engine. Low-cost features included the use of very inexpensive simplex fuel nozzles and combustor liners of perforated sheet material.
Fear, J. S.
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