초록 ▼

An engine system with a multi-gas-generator, tip-turbine driven lift fan with pressurized air circulation control for use on vertical and short-take-off and landing (V/STOL) aircraft is disclosed. Gas generators located around the periphery of the fan drive the fan through action on a fan blade-tip

An engine system with a multi-gas-generator, tip-turbine driven lift fan with pressurized air circulation control for use on vertical and short-take-off and landing (V/STOL) aircraft is disclosed. Gas generators located around the periphery of the fan drive the fan through action on a fan blade-tip turbine or provide compressed gas (hot or cold) to circulation control devices. Variable pitch fan blades improve part-power cruise performance. Enclosed in a nacelle, the engine employs circulation control to enhance V/STOL performance. In some embodiments, a core cruise turbine gas generator mounted in the center of the fan duct powers the fan during cruise mode. In some hybrid gas and electric power embodiments, the core cruise gas generator is replaced by an electric motor that draws power from a battery in the fuselage. The battery may be charged by an electric generator driven by a gas generator around the periphery of the fan.

대표청구항 ▼

1. An engine system for vertical takeoff and landing (VTOL) aircraft comprising: a fan comprising a plurality of blades and having an axis of rotation, the fan providing at least horizontal thrust;at least one gas generator disposed relative to the plurality of blades so that exhaust gas exits from

1. An engine system for vertical takeoff and landing (VTOL) aircraft comprising: a fan comprising a plurality of blades and having an axis of rotation, the fan providing at least horizontal thrust;at least one gas generator disposed relative to the plurality of blades so that exhaust gas exits from the at least one gas generator in a direction substantially parallel to the axis of rotation and that impinges on the plurality of blades to generate rotational energy;a nacelle, the fan and the at least one gas generator are disposed in the nacelle, the nacelle comprising an inlet for air intake, the inlet comprising a leading edge blowing slot; anda valve selectively allowing pressurized gas to exit the leading edge blowing slot in a forward direction towards the inlet of the nacelle, the pressurized gas exiting the leading edge blowing slot modifying flow characteristics of the fan during a vertical mode of flight. 2. The engine system of claim 1, further comprising a controller for switching the VTOL aircraft between the vertical mode and the horizontal mode, the vertical mode for aircraft takeoff, the horizontal mode for aircraft cruising. 3. The engine system of claim 1, wherein the nacelle comprises a fan duct and a first gas generator duct, the fan being disposed in the fan duct and at least one of the at least one gas generator being disposed in the first gas generator duct. 4. The engine system of claim 3, wherein the first gas generator duct is disposed at a perimeter of the fan duct. 5. The engine system of claim 4, wherein the nacelle comprises a second gas generator duct disposed on an opposite side of the fan from the first gas generator duct, and wherein at least one of the at least one gas generator is disposed in the second gas generator duct. 6. The engine system of claim 2, further comprising an actuator, the controller actuating the actuator so as to move the fan and the at least one gas generator between the vertical mode and the horizontal mode. 7. The engine system of claim 2, wherein the controller adjusts a pitch of the plurality of blades. 8. The engine system of claim 1, further comprising: a core cruise turbine gas generator disposed below the fan and configured to rotate the fan. 9. The engine system of claim 2, wherein the controller controls operation of the at least one gas generator. 10. The engine system of claim 1, wherein the nacelle comprises a port door, and wherein the controller closes the port door when in the horizontal mode. 11. The engine system of claim 2, further comprising an electric motor disposed below the fan for rotating the fan. 12. The engine system of claim 11, further comprising a battery and an electric generator, the battery powering the electric motor, the electric generator being powered by the at least one gas generator so as to charge the battery. 13. The engine system of claim 1, wherein the nacelle comprises an exhaust duct disposed in a flow path between the at least one gas generator and the plurality of blades to maintain momentum of the exhaust gas. 14. A method for operating a vertical takeoff and landing (VTOL) aircraft comprising: providing a nacelle comprising at least one gas generator and a fan, the fan including a plurality of blades and having an axis of rotation, the fan providing at least horizontal thrust, the nacelle further comprising an inlet for air intake, the inlet comprising a leading edge blowing slot;exhausting gas from the at least one gas generator in a direction substantially parallel to the axis of rotation and that impinges on the plurality of blades so as to generate rotational energy for the fan;rotating the nacelle between a vertical mode and a horizontal mode during flight; andselectively allowing pressurized gas to exit the leading edge blowing slot in a forward direction towards the inlet of the nacelle, the pressurized gas exiting the leading edge blowing slot modifying flow characteristics of the fan during the vertical mode of flight. 15. An engine system for vertical takeoff and landing (VTOL) aircraft comprising: a fan rotatable about a shaft having an axis of rotation, the fan comprising a plurality of blades for providing at least horizontal thrust;a first gas generator disposed forward of the fan so that exhaust gas exits from the first gas generator in a direction substantially parallel to the axis of rotation and impinges on the plurality of blades;a nacelle, the fan and the at least one gas generator are disposed in the nacelle, the nacelle comprising an inlet for air intake, the inlet comprising a leading edge blowing slot; anda valve selectively allowing pressurized gas to exit the leading edge blowing slot in a forward direction towards the inlet of the nacelle, the pressurized gas exiting the leading edge blowing slot modifying flow characteristics of the fan during a vertical mode of flight. 16. The engine system of claim 15, further comprising an electric motor disposed aft of the fan to rotate the shaft. 17. The engine system of claim 15, wherein the nacelle comprises a fan duct and a gas generator duct, the fan being disposed in the fan duct and the first gas generator being disposed in the gas generator duct. 18. The method of claim 14, wherein the at least one gas generator comprises a plurality of gas generators, the method further comprising: operating a number of the plurality of gas generators during the vertical mode during takeoff; andoperating fewer than the number of the plurality of gas generators during the horizontal mode during flight.