Patent
Turbofan gas turbine engine with variable fan outlet guide vanes
TLDR
A turbofan gas turbine engine (10) as mentioned in this paper includes a forward fan section (33) with a row of fan rotor blades (32), a core engine (18), and a fan bypass duct (40) downstream of the forward fan and radially outwardly of the core engine.Abstract:
A turbofan gas turbine engine (10) includes a forward fan section (33) with a row of fan rotor blades (32), a core engine (18), and a fan bypass duct (40) downstream of the forward fan section (33) and radially outwardly of the core engine (18). The forward fan section (33) has only a single stage of variable fan guide vanes which are variable fan outlet guide vanes (35) downstream of the forward fan rotor blades (32). An exemplary embodiment of the engine includes an afterburner (130) downstream of the fan bypass duct (40) between the core engine (18) and an exhaust nozzle (68). The variable fan outlet guide vanes (35) are operable to pivot from a nominal OGV position at take-off to an open OGV position at a high flight Mach Number which may be in a range of between about 2.5 - 4+. Struts (31) extend radially across a radially inwardly curved portion (131) of a flowpath (29) of the engine (10) between the forward fan section (33) and the core engine (18).read more
Citations
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References
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Patent
Turbofan engine with a core driven supercharged bypass duct
Rollin George Giffin,James Edward Johnson,David William Crall,John W. Salvage,Peter Nicholas Szucs +4 more
TL;DR: In this article, a multiple bypass turbofan engine including a core engine assembly has a fan bypass duct radially outward of the core engine assemblies and has first and second inlets disposed between forward and aft fans driven by a low pressure turbine and a turbine respectively.
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Turbofan engine with a core driven supercharged bypass duct and fixed geometry nozzle
TL;DR: In this paper, a multiple bypass turbofan engine including a core engine assembly has a fan bypass duct radially outward of the core engine assemblies and has first and second inlets disposed between forward and aft fans driven by a low pressure turbine and a turbine respectively.
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TL;DR: In this paper, a gas turbine engine has a fan section, at least one row of FLADE fan blades disposed radially outwardly of and drivingly connected to the fan section.