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US 9,540,113 B2Granted
De-couple geared turbo-fan engine and aircraft
AssigneeUnited Technologies Corporation
InventorRobert L. Gukeisen
Life of this patent
Estimating the term…
Abstract
A turbofan engine includes a core engine section including a compressor section feeding air to a combustor to generate high speed exhaust gases that drive a turbine section all disposed about an engine axis, a geartrain driven by the core engine section, a fan section driven by the geartrain about a fan axis spaced apart from the engine axis, and an accessory gearbox driven by the geartrain and mounted apart from the core engine section and the fan section.
Claims11
An aircraft propulsion system comprising:
- a core engine section mounted within an aft portion of an aircraft fuselage, the core engine section including a compressor section feeding air to a combustor to generate high speed exhaust gases that drive a turbine section all disposed about an engine axis;
- a geartrain mounted within the aircraft fuselage and driven by the core engine section;
- a fan section externally mounted to the aircraft fuselage and driven by the geartrain about a fan axis spaced apart from the engine axis;
- and
- an accessory gearbox supported within the aircraft fuselage and driven by the geartrain and mounted apart from the core engine section and the fan section, the accessory gear box driving at least one system required for operation of the core engine section,
- wherein the core engine section comprises a first core engine section disposed about a first axis and a second core engine section disposed about a second axis different than the first axis, the first core engine section and the second core engine section mounted within the aft portion of the aircraft fuselage and the fan section comprises first and second fan sections driven by a corresponding one of the first and second core engine sections.
3 more elements
An aircraft system comprising:
- an elongated fuselage;
- a wing structure extending from opposing sides of the fuselage;
- a vertical stabilizer including a horizontal stabilizer surface mounted to an upper portion of the vertical stabilizer;
- a first core engine section and a second core engine section mounted within an aft portion of an aircraft fuselage, each of the first core engine section and the second core engine section including a compressor section feeding air to a combustor to generate high speed exhaust gases that drive a turbine section disposed about an corresponding first engine axis and second engine axis;
- a first geartrain and a second geartrain mounted within the aircraft fuselage and driven by a corresponding one of the first core section and the second core engine section;
- a first fan section and a second fan section externally mounted to the aircraft fuselage and driven by a corresponding one of the first geartrain and the second geartrain about a corresponding one of a first fan axis and a second fan axis spaced apart from a corresponding one of the first engine axis and the second engine axis;
- and
- an accessory gearbox supported within the aircraft fuselage and driven by at least one of the first geartrain and the second geartrain, the accessory gearbox mounted apart from the first core engine section, the second core engine section, the first fan section and the second fan section.
5 more elements
Dependencies are inferred from the claim text.