Dual power lift system

Patent metadata

Field	Value
Publication number	US-11859542-B2
Application number	US-202117645162-A
Country	US
Kind code	B2
Filing date	Dec 20, 2021
Priority date	Dec 20, 2021
Publication date	Jan 2, 2024
Grant date	Jan 2, 2024

Abstract

A system including a turbine engine configured to generate rotor power and produce an engine air flow. The system is configured to provide rotor power to one of more shaft-driven lift fans to generate a first thrust on an aircraft body and provide a gas flow to one or more gas-driven lift fans to generate a second thrust on the aircraft body. The gas flow may be at least a portion of the engine air flow produced by the turbine engine. The turbine engine may be configured to exhaust another portion of the engine air flow through a jet nozzle to generate an engine thrust. In examples, the system includes at least a second turbine engine. The one of more shaft-driven lift fans and/or one of more gas-driven lift fans be powered by the turbine engine, the second turbine engine, or both the turbine engine and the second turbine engine.

First claim

What is claimed is:

1. A system comprising:
a turbine engine configured to combust a fuel to mechanically rotate a rotor to generate shaft power and generate an engine air flow through the turbine engine using a first portion of the shaft power, wherein the turbine engine is configured to provide a forward thrust to an aircraft body by exhausting an exhaust flow through a nozzle of the turbine engine, and wherein the exhaust flow is a portion of the engine air flow;
a second turbine engine configured to generate a second engine air flow through the second turbine engine, wherein the second turbine engine is configured to provide a second forward thrust to the aircraft body by exhausting a second exhaust flow through a second nozzle, wherein the second exhaust flow is a portion of the second engine air flow;
a shaft-driven lift fan configured to rotate to provide a first vertical thrust to the aircraft body using rotor power transferred from the rotor, wherein the rotor power is a second portion of the shaft power;
a gas-driven lift fan configured to rotate to provide a second vertical thrust to the aircraft body using a gas flow, wherein the gas flow is at least one of another portion of the engine air flow or another portion of the second engine air flow; and
a duct configured to cause the gas flow to selectively bypass at least one of the nozzle or the second nozzle to supply the gas flow to the gas-driven lift fan.

2. The system of claim 1 , wherein the gas-driven lift fan includes tip turbine blades configured to generate a rotary motion when the gas flow impinges on one or more tips of the tip turbine blades, and wherein the gas-driven lift fan is configured to generate the second vertical thrust using the rotary motion.

3. The system of claim 1 , wherein the shaft-driven lift fan includes a fan shaft and a plurality of vanes, wherein the fan shaft is configured to generate a rotary torque using the rotor power, and wherein the plurality of vanes are configured to generate the first vertical thrust when the fan shaft transmits the rotary torque to the plurality of vanes.

4. The system of claim 3 , further comprising a transmission system operably coupled to the rotor and the fan shaft, wherein the transmission system is configured to control the rotor power transferred from the rotor to the fan shaft.

5. The system of claim 4 , wherein the transmission system includes a gearbox mechanically coupled to the rotor and the fan shaft, wherein the gearbox is configured to provide the rotor power to the fan shaft to cause the fan shaft to generate the rotary torque.

6. The system of claim 4 , wherein the transmission system includes a generator configured to generate electrical power using the rotor power, and wherein the transmission system is configured to provide the electrical power to a motor operably coupled to the fan shaft to cause the fan shaft to generate the rotary torque.

7. The system of claim 1 , wherein the second turbine engine is configured to mechanically rotate a second rotor to generate a second shaft power, and wherein the shaft-driven lift fan is configured to rotate to provide the first vertical thrust to the aircraft body using the shaft power and the second shaft power.

8. The system of claim 7 , further comprising a control system configured to adjust one or more components of the system to cause the turbine engine and the second turbine engine to provide at least one of the first shaft power or the second shaft power to generate at least one of a flow energy of the another portion of the engine air flow or a flow energy of the another portion of the second engine air flow sufficient to provide the second vertical thrust as the shaft-driven lift fan rotates to provide the first vertical thrust using the shaft power and the second shaft power.

9. The system of claim 1 , further comprising control circuitry configured to:
determine a first power requirement required for the shaft-driven lift fan to provide the first vertical thrust;
determine a second power requirement required for the gas-driven lift fan to provide the second vertical thrust as the shaft-driven lift fan provides the first vertical thrust; and
adjust one or more components of the system to cause the turbine engine to generate a shaft power sufficient to provide the first power requirement and the second power requirement.

10. The system of claim 9 , wherein the control circuitry is configured to:
determine a third power requirement required for the turbine engine to provide the forward thrust; and
control the operating point of the turbine engine based on at least the first power requirement, the second power requirement, and the third power requirement.

11. The system of claim 1 , further comprising:
an attitude control system configured to monitor an attitude of the aircraft body; and
control circuitry configured to cause the shaft-driven lift fan to provide an amount of the first vertical thrust and cause the gas-driven lift fan to provide an amount of the second vertical thrust based at least in part on a signal indicative of the attitude from the attitude control system.

12. The system of claim 1 , wherein at least one of the shaft-driven lift fan is configured to vary a direction of the first vertical thrust relative to the aircraft body or the gas-driven lift fan is configured to vary a direction of the second vertical thrust relative to the aircraft body.

13. The system of claim 1 , further comprising a control system configured to adjust one or more components of the system to cause the turbine engine to:
provide the first portion of the shaft power to generate a flow energy of the gas flow sufficient to provide the second vertical thrust, and
provide the second portion of the shaft power sufficient to generate the first vertical thrust as the turbine engine provides the first portion of the shaft power sufficient to provide the second vertical thrust.

14. The system of claim 13 , wherein the first portion of the shaft power generates a flow energy of the engine air flow, and wherein the flow energy of the gas flow is a portion of a flow energy of the engine air flow.

15. An aircraft comprising:
a turbine engine configured to combust a first fuel to mechanically rotate a rotor to generate shaft power and generate an engine air flow through the turbine engine using a portion of the shaft power, wherein the turbine engine is configured to provide a forward thrust to an aircraft body of the aircraft using a first exhaust flow, and wherein the first exhaust flow is a portion of the engine air flow;
two or more shaft-driven lift fans, a shaft-driven lift fan of the two or more shaft-driven lift fans configured to rotate to provide a first vertical thrust to the aircraft body using rotor power transferred from the rotor, wherein the rotor power is a second portion of the shaft power;
a single gas-driven lift fan configured to rotate to provide a second vertical thrust to the aircraft body using a gas flow, wherein the gas flow is another portion of the engine air flow,
wherein the two or more shaft-driven lift fans are forward of the single gas-driven lift fan.

16. The system of claim 15 , wherein the turbine is configured to generate the forward thrust by exhausting the exhaust flow through a nozzle of the turbine engine, and further comprising:
a duct configured to cause the gas flow to selectively bypass the nozzle to supply the gas flow to the single gas-driven lift fan.

17. The system of claim 15 , wherein at least one of the single shaft-driven lift fan is configur

Assignees

• Rolls Royce Nam Tech Inc

Inventors

• Keller Richard K
• Johnson Paul

Classifications

• F02C6/04 Primary

  Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output (F02C6/18 takes precedence {; for a fluidised-bed combustor F02C3/205}) · CPC title

• F02C9/18

  by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} · CPC title

• F02K3/025

  the by-pass flow being at least partly used to create an independent thrust component · CPC title

• F05D2220/90

  in vehicles adapted for vertical or short take off and landing (v/stol vehicles) · CPC title

• F05D2240/128

  Nozzles · CPC title