Back to results
US 10,793,281 B2Granted
Propulsion system for an aircraft
AssigneeGeneral Electric Company
InventorsRandy M. Vondrell, Glenn David Crabtree
Life of this patent
Estimating the term…
Abstract
A propulsion system for an aircraft includes a turbomachine having a first turbine, a primary fan mechanically driven by the first turbine of the turbomachine, and an electric generator mechanically driven by the first turbine of the turbomachine. The propulsion system also includes an electric fan assembly, the electric generator electrically connected to the electric fan assembly for powering the electric fan assembly.
Claims20
An aircraft having propulsion system and a wing assembly, the aircraft comprising:
- a turbomachine comprising a first turbine;
- a primary fan mechanically driven by the first turbine of the turbomachine;
- an electric generator mechanically driven by the first turbine of the turbomachine;
- and
- an electric fan assembly, the electric generator electrically connected to the electric fan assembly for powering the electric fan assembly, the electric fan assembly including at least one blade disposed longitudinally-forward of the wing assembly and longitudinally-rearward of at least one blade of the primary fan;
- wherein the turbomachine and primary fan are an under-wing mounted engine mounted to the wing assembly, and wherein the electric fan assembly is an under-wing mounted electric fan assembly mounted to the wing assembly at one or more locations spaced apart from the turbomachine and primary fan.
3 more elements
An aircraft comprising:
- a wing assembly;
- a first propulsion system comprising a first turbomachine, a first primary fan, a first electric generator, and a first electric fan assembly, the first turbomachine drivingly connected to the first primary fan and the first electric generator, and the first electric generator electrically coupled to the first electric fan assembly for driving the first electric fan assembly, wherein the first turbomachine and first primary fan are a first under-wing mounted engine mounted to the wing assembly, and wherein the first electric fan assembly is a first under-wing mounted electric fan assembly mounted to the wing assembly;
- and
- a second propulsion system comprising a second turbomachine, a second primary fan, a second electric generator, and a second electric fan assembly, the second turbomachine drivingly connected to the second primary fan and the second electric generator, and the second electric generator electrically coupled to the second electric fan assembly for driving the second electric fan assembly, wherein the first turbomachine and first primary fan are a first under-wing mounted engine mounted to the wing assembly, and wherein the second electric fan assembly is a second under-wing mounted electric fan assembly mounted to the wing assembly;
- wherein the first propulsion system is in electrical communication with the second propulsion system and each of the first and second electric fan assemblies extending at least partially longitudinally-forward of the wing assembly and longitudinally-rearward of each respective first and second turbomachine.
2 more elements
An aircraft having a propulsion system, the aircraft comprising:
- a turbomachine;
- a primary fan mechanically driven by the turbomachine;
- an electric generator mechanically driven by the turbomachine;
- and
- an electric fan assembly comprising a plurality of electric fans, the electric generator electrically connected to each of the plurality of electric fans of the electric fan assembly for powering each of the plurality of electric fans of the electric fan assembly;
- wherein at least one of the plurality of electric fans is positioned at least partially longitudinally-forward of a wing of the aircraft and at least partially longitudinally-rearward of the primary fan, and wherein the turbomachine and primary fan are an under-wing mounted engine and each of the plurality of electric fans is an under-wing mounted electric fan.
3 more elements
Dependencies are inferred from the claim text.