A propulsion system for an aircraft is provided having a propulsion engine configured to be mounted to the aircraft. The propulsion engine includes an electric machine defining an electric machine tip speed during operation. The propulsion system additionally includes a fan rotatable about a central
A propulsion system for an aircraft is provided having a propulsion engine configured to be mounted to the aircraft. The propulsion engine includes an electric machine defining an electric machine tip speed during operation. The propulsion system additionally includes a fan rotatable about a central axis of the electric propulsion engine with the electric machine. The fan defines a fan pressure ratio, RFP, and includes a plurality of fan blades, each fan blade defining a fan blade tip speed. The electric propulsion engine defines a ratio of the fan blade tip speed to electric machine tip speed that is within twenty percent of the equation, 1.01×RFP−0.311, such that the propulsion engine may operate at a desired efficiency.
대표청구항▼
1. A propulsion system for an aircraft having a fuselage and an aft end, the propulsion system comprising: an electric propulsion engine configured to be mounted to the aircraft, the propulsion engine defining a central axis and comprising: an electric machine defining an electric machine tip speed
1. A propulsion system for an aircraft having a fuselage and an aft end, the propulsion system comprising: an electric propulsion engine configured to be mounted to the aircraft, the propulsion engine defining a central axis and comprising: an electric machine defining an electric machine tip speed during operation of the propulsion engine;a fan rotatable about the central axis of the electric propulsion engine with the electric machine, the fan defining a fan pressure ratio (RFP) and comprising a plurality of fan blades, each fan blade defining a fan blade tip speed during operation of the electric propulsion engine, the electric propulsion engine defining a ratio of fan blade tip speed to electric machine tip speed; anda power gearbox mechanically coupled to the electric machine, the fan mechanically coupled to the power gearbox and rotatable about the central axis of the electric propulsion engine by the electric machine through the power gearbox, the power gearbox defining a gear ratio between about 1:1 and about 1:5;wherein during operation of the electric propulsion engine, the ratio of fan blade tip speed to electric machine tip speed is within twenty percent of the following equation: 1.01×RFP−0.311. 2. The propulsion system of claim 1, wherein the ratio of fan blade tip speed to electric machine tip speed is within ten percent of the following equation: 1.01×RFP−0.311. 3. The propulsion system of claim 1, wherein the fan pressure ratio, RFP, is greater than one and less than about three during operation of the electric propulsion engine. 4. The propulsion system of claim 1, wherein the propulsion engine is an electric propulsion engine, wherein the electric machine is an electric motor, and wherein the fan is rotatable about the central axis of the electric propulsion engine by the electric motor. 5. The propulsion system of claim 1, wherein the fan is positioned forward of the power gearbox along the central axis of the electric propulsion engine, and wherein the electric machine is positioned forward of the fan along the central axis of the electric propulsion engine. 6. The propulsion system of claim 1, wherein the power gearbox is positioned forward of the fan along the central axis of the electric propulsion engine and forward of the electric machine along the central axis of the electric propulsion engine, and wherein the fan is positioned forward of the electric machine along the central axis of the electric propulsion engine. 7. The propulsion system of claim 1, wherein the electric propulsion engine is configured as a boundary layer ingestion fan. 8. The propulsion system of claim 1, wherein the electric propulsion system is configured as an aft fan configured to be mounted at the aft end of the aircraft, and along a mean line of the aircraft. 9. The propulsion system of claim 1, further comprising: a gas turbine engine; andan electric generator operable with the gas turbine engine, and wherein the electric machine is in electrical communication with the electric generator. 10. The propulsion system of claim 1, wherein the electric machine comprises a stator having a stator magnetic field and a rotor configured to generate a magnetic field that interacts with the stator magnetic field, the rotor comprising a rotor core, the rotor core comprising a plurality of permanent magnets and a sleeve component including a plurality of cavities formed therein, wherein the plurality of permanent magnets are disposed in the plurality of cavities formed in the sleeve component to form an interior permanent magnet machine. 11. The propulsion system of claim 10, wherein the sleeve component comprises one or more land portions and one or more disc portions defining the plurality of cavities. 12. The propulsion system of claim 1, wherein the electric machine tip speed is greater than about 750 feet per second and less than about 1150 feet per second. 13. The propulsion system of claim 1, wherein the propulsion engine is an electric-only propulsion engine. 14. The propulsion system of claim 1, wherein the fan is rotatable about the central axis of the propulsion engine by a driveshaft. 15. A method for operating a propulsion system for an aircraft, the propulsion system comprising a propulsion engine comprising an electric machine and a fan, the electric machine defining an electric machine tip speed and the fan defining a fan tip speed, the method comprising: operating the fan of the electric propulsion engine to define a fan pressure ratio (RFP) greater than one and less than about three, a ratio of fan blade tip speed to electric machine tip speed being within twenty percent of the equation 1.01×RFP−0.3116-8;wherein the propulsion engine is an electric propulsion engine comprising a power gearbox mechanically coupled to the electric machine, the fan mechanically coupled to the power gearbox and rotatable about the central axis of the electric propulsion engine by the electric machine through the power gearbox, the power gearbox defining a gear ratio between about 1:1 and about 1:5. 16. The method of claim 15, wherein the ratio of fan blade tip speed to electric machine tip speed is within about ten percent of the equation 1.01×RFP−0.311. 17. The method of claim 15, wherein the ratio of fan blade tip speed to electric machine tip speed is within about five percent of the equation 1.01×RFP−0.311. 18. The method of claim 15 wherein the propulsion engine is a boundary layer ingestion aft engine.
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