Effect of vane twist on the performance of dome swirlers for gas turbine airblast atomizers [PDF]
For advanced gas turbine engines, two combustor systems, the lean premixed/prevaporized (LPP) and the rich burn/quick quench/lean burn (RQL) offer great potential for reducing NO(x) emissions.
Dogra, Anju S. +2 more
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A theoretical study on throttle ranges of O/F controllable hybrid rocket propulsion systems
Journal of Fluid Science and Technology, 2018 The characteristics of several O/F control methods for hybrid rocket propulsion have been discussed and theoretically analyzed from the physical properties of propellants and fuel regression behavior.
Kohei OZAWA, Toru SHIMADA
doaj +1 more source
Predicting the Sauter Mean Diameter of Swirl Cup Airblast Fuel Injector Based on Backpropagation (BP) Neural Network Model. [PDF]
ACS Omega, 2023 Fang C +8 more
europepmc +1 more source
Investigation of the spray formation and breakup process in an open-end swirl injector. [PDF]
Sci Prog, 2020 Chen C, Tang Z.
europepmc +1 more source
Fuel injector: Air swirl characterization aerothermal modeling, phase 2, volume 1 [PDF]
A well integrated experimental/analytical investigation was conducted to provide benchmark quality relevant to a prefilming type airblast fuel nozzle and its interaction with the combustor dome air swirler.
Mcdonell, V. G. +3 more
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Some aspects of flox-methane rocket engine throttling [PDF]
Four injector designs and two chamber profiles were experimentally evaluated for structural integrity, combustion efficiency, and resistance to combustion instabilities.
Hannum, N. P. +2 more
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Energy efficient engine sector combustor rig test program [PDF]
Under the NASA-sponsored Energy Efficient Engine program, Pratt & Whitney Aircraft has successfully completed a comprehensive combustor rig test using a 90-degree sector of an advanced two-stage combustor with a segmented liner.
Dubiel, D. J. +4 more
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Effect of Upstream Valve Opening Process on Dynamic Spray Atomization of Bipropellant Thruster Injector. [PDF]
Micromachines (Basel), 2022 Zhang Z, Yu Y, Cao J.
europepmc +1 more source
Aerothermal modeling program, phase 2 [PDF]
The main objectives of the Aerothermal Modeling Program, Phase 2 are: to develop an improved numerical scheme for incorporation in a 3-D combustor flow model; to conduct a benchmark quality experiment to study the interaction of a primary jet with a ...
Mongia, H. C. +4 more
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Hypersonic research engine project. Phase 2: Some combustor test results of NASA aerothermodynamic integration model [PDF]
Combustor test results of the NASA Aerothermodynamic Integration Model are presented of a ramjet engine developed for operation between Mach 3 and 8.
Gaede, A. E., Sainio, W. C., Sun, Y. H.
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