Patent
Supersonic missile turbojet engine
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TLDR
A turbojet engine includes a core engine, an afterburner, and a converging-diverging exhaust nozzle in serial flow communication as discussed by the authors, and a controller is operatively joined to the core engine and after-burner and configured for scheduling fuel for operating the after burners dry during subsonic flight operation of the engine, wet during transonic flight, and dry during supersonic flight.Abstract:
A turbojet engine includes a core engine, an afterburner, and a converging-diverging exhaust nozzle in serial flow communication. A controller is operatively joined to the core engine and afterburner and configured for scheduling fuel thereto for operating the afterburner dry during subsonic flight operation of the engine, wet during transonic flight, and dry during supersonic flight.read more
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Patent
Fladed supersonic missile turbojet
TL;DR: A turbojet engine includes a core engine, afterburner, and converging-diverging exhaust nozzle disposed in serial flow communication, and a bypass duct includes variable inlet guide vanes disposed forward of the flades for controlling airflow thereto.
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TL;DR: In this paper, a flowpath control mechanism is configured to selectively restrict fluid flow through the second engine core, where the first engine core is composed of a fan, a low pressure compressor, and a turbine.
References
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Differential geared turbine engine with torque modulation capability
Giuseppe Rago,Richard Harvey +1 more
TL;DR: In this paper, a method and apparatus for controllable distribution of power from a turbine of a gas turbine engine between two rotatable loads of the turbine engine, consisting of transferring a shaft power of a turbine to the respective rotatable loading using differential gearing operatively coupled with the turbine and the rotatable load, respectively, is presented.
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Engine power extraction control system
TL;DR: In this article, an engine power extraction control system is used to control the main propulsion engines and the electrical machines that are coupled to supply an appropriate amount of aircraft thrust and electrical energy to the aircraft.
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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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Modulating bypass variable cycle turbofan engine
TL;DR: In this article, a turbofan engine is provided with a core engine, a first fan and a second fan, and means are provided for varying the proportion of the flow of air among the fan ducts and core engine.