Patent
Retractable afterburner for jet engine
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TLDR
In this paper, a retractable afterburner cover for a jet engine has been proposed, which is affixed by a plurality of moveable support arms to the outer surface of the engine.Abstract:
The present invention is a retractable afterburner shroud for use upon a jet engine. The retractable shroud conforms to an outer surface of a jet engine. The afterburner shroud is affixed by a plurality of moveable support arms. The afterburner shroud is retractable. During operation of the afterburner shroud, the afterburner shroud is extended rearward toward the exhaust of the jet engine. A storage tank provides liquid oxygen through the support arms to a mixing ring located within the afterburner shroud. The mixing ring mixes the liquid oxygen and fuel to form a combustible mixture. The combustible mixture is injected into the exhaust wherein the mixture is ignited. The ignited mixture provides additional thrust for the jet engine.read more
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Gas turbine engine with low stage count low pressure turbine
TL;DR: In this article, a gas turbine engine according to an exemplary aspect of the present disclosure includes a gear train defined along an engine centeriine axis, and a spool along said engine center iine axis which drives the gear train, the spool includes a low stage count low pressure turbine.
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TL;DR: In this paper, a method to reduce the aerodynamic drag of an engine exhaust/engine nozzle is proposed, where the first and second drag control parameters corresponding to an angle of one or more variable area turbines of a turbine engine and a position of a variable area exhaust nozzle of the turbine engine are adjusted.
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Patent
Variable cycle gas turbine engines
TL;DR: In this article, a design technique, method, and apparatus for varying the bypass ratio and modulating the flow of a gas turbine engine of the bypass type in order to achieve improved mixed mission performance is presented.
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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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Aircraft engine frame construction
TL;DR: In this article, a gas turbine engine of the type having generally cylindrical casings defining concentric bypass and turbine discharge passages including a support structure in the turbine discharge passage is cooled with low pressure compressor discharge air through a scoop located in the bypass gas passage.