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US 12,338,770 B1Granted
Thrust diverter for an open rotor aircraft propulsion system
AssigneeRtx Corporation
InventorMarc J. Muldoon
Life of this patent
Estimating the term…
Abstract
A propulsion system is provided for an aircraft. This aircraft propulsion system includes an engine housing, an open propulsor rotor, an engine core and a thrust diversion system. The open propulsor rotor is outside of the engine housing. The engine core is within the engine housing and motively coupled to the open propulsor rotor. The thrust diversion system is configured with the engine housing. The thrust diversion system includes a door configured to move radially from a stowed position to a deployed position.
Claims14
A propulsion system for an aircraft, comprising:
- an engine housing;
- an open propulsor rotor outside of the engine housing;
- an engine core within the engine housing and motively coupled to the open propulsor rotor;
- a thrust diversion system configured with the engine housing, the thrust diversion system comprising a door configured to move radially from a stowed position to a deployed position, and the door seated in a recess of the engine housing when the door is in the stowed position, the door extending circumferentially between a first side of the door and a second side of the door, and at least one of the first side of the door or the second side of the door has a curved convex geometry at a radially inner end of the door when the door is in the deployed position;
- and
- an open guide vane array arranged with the open propulsor rotor upstream of the thrust diversion system, the open guide vane array comprising a plurality of guide vanes arranged circumferentially about the engine housing.
3 more elements
A propulsion system for an aircraft, comprising:
- an engine housing;
- an engine core within the engine housing and extending along an axial centerline, and the engine core including a compressor section, a combustor section aft of the compressor section, and a turbine section aft of the combustor section;
- an unducted rotor outside of the engine housing;
- a thrust diversion system configured with the engine housing downstream of the unducted rotor, the thrust diversion system comprising a door configured to pivot radially about an upstream end outward from a stowed position to a deployed position, and the thrust diversion system configured to redirect a gas flow radially outward from the propulsion system when the door is pivoted radially outward to the deployed position, and in the stowed position the door extends along the engine housing from the upstream end radially outboard of the compressor section to a downstream end radially outboard of the turbine section;
- and
- an unducted guide vane arranged with the unducted rotor upstream of the thrust diversion system, the unducted guide vane projecting radially outward from the engine housing to a tip.
3 more elements
A propulsion system for an aircraft, comprising:
- an engine housing;
- an open propulsor rotor outside of the engine housing;
- an engine core within the engine housing and motively coupled to the open propulsor rotor, the engine core comprising an upstream portion and a downstream portion, the upstream portion including a compressor section, and the downstream portion including a turbine section;
- and
- a plurality of exterior doors arranged in an array at an exterior of the engine housing, the array extending circumferentially about a centerline of the propulsion system, and each of the plurality of exterior doors configured to move radially from a stowed position to a deployed position to divert air, propelled by the open propulsor rotor outside of the engine housing, radially outwards away from the centerline of the propulsion system;
- wherein a downstream end of each of the plurality of exterior doors moves radially outward when moving from the stowed position to the deployed position;
- and
- wherein, in the stowed position, each of the plurality of exterior doors extends along the engine housing from an upstream end that is radially outboard of the compressor section to the downstream end that is radially outboard of the turbine section.
5 more elements
Dependencies are inferred from the claim text.