Nacelle for a boundary layer ingestion propulsor
An aircraft is disclosed having a boundary layer ingestion propulsor. The aircraft comprises an elongated fuselage extending between a nose section and a tail section. The fuselage has an upswept underside in the tail section. The boundary layer ingestion propulsor is positioned in the tail section. The propulsor comprises a fan radially encased by a nacelle circumscribing the fuselage. The nacelle defines a leading edge line extending from a top dead center to a bottom dead center of the nacelle intersecting an axis of rotation of the fan at an angle no greater than seventy degrees.
1. An aircraft comprising:
an elongated fuselage extending between a nose section and a tail section thereof, said fuselage having an upswept underside in said tail section; and
a boundary layer ingestion propulsor positioned in said tail section, said propulsor comprising a fan radially encased by a nacelle circumscribing the elongated fuselage, said nacelle defining a leading edge line extending from a top dead center to a bottom dead center of said nacelle intersecting an axis of rotation of said fan at an angle no greater than seventy degrees
wherein said bottom dead center is positioned forward of said top dead center along the axis of rotation at an axial distance greater than a shortest distance from said top dead center to said axis of rotation.
2. The aircraft of claim 1 wherein said leading edge line intersects said axis of rotation at an angle of no greater than sixty degrees.
3. The aircraft of claim 1 further comprising:
a gas turbine engine mounted to said aircraft; and
an electric motor driven by the gas turbine engine, wherein said propulsor is an electric fan powered by the electric motor.
4. The aircraft of claim 3 wherein said nacelle defines a chamber, and wherein said electric motor is positioned in the chamber.
5. The aircraft of claim 4 wherein said electric motor is coupled to said propulsor via a shaft and a gearbox.
6. The aircraft of claim 1 wherein a leading edge of the nacelle extends 360 degrees about the axis of rotation and intersects said top dead center and said bottom dead center.
7. The aircraft of claim 1 wherein a tail strike limit of the aircraft is defined as a plane tangential to the upswept underside of the tail section, and wherein the nacelle is positioned entirely within said tail strike limit.
8. An aircraft comprising:
an elongated fuselage extending between a nose section and a tail section thereof, said fuselage having an upswept underside in said tail section; and
a boundary layer ingestion propulsor positioned in said tail section, said propulsor comprising a fan radially encased by a nacelle circumscribing the fuselage, said fan defining an axis of rotation and said nacelle defining a leading edge line extending from a top dead center to a bottom dead center of said nacelle;
wherein said bottom dead center is positioned forward of said top dead center along the axis of rotation at an axial distance greater than a shortest distance from said top dead center to said axis of rotation.
9. The aircraft of claim 8 wherein said bottom dead center is positioned forward of said top dead center along the axis of rotation at an axial distance greater than 120% of the shortest distance from said top dead center to said axis of rotation.
10. The aircraft of claim 8 wherein an inlet duct is formed between the nacelle and the fuselage, said inlet duct being substantially asymmetrical between a top half and a bottom half of the inlet duct.
11. The aircraft of claim 10 further comprising a pair of struts positioned in said bottom half of the inlet duct.
12. The aircraft of claim 10 further comprising a plurality of inlet members positioned about a circumference of said inlet duct.
13. The aircraft of claim 12 wherein a portion of said plurality of inlet members are struts.
14. The aircraft of claim 12 wherein one or more of said plurality of inlet members is shaped, dimensioned, and positioned in said inlet duct to condition airflow through the inlet duct.
15. A method of operating a boundary layer ingestion propulsor in an aircraft comprising an elongated fuselage extending between a nose section and a tail section, said method comprising:
positioning said boundary layer ingestion propulsor in said tail section, wherein said elongated fuselage has an upswept underside in said tail section;
ingesting boundary layer air through an inlet duct of the propulsor, said inlet duct defined between a nacelle and said fuselage, said nacelle circumscribing the elongate fuselage and defining a leading edge line extending from a top dead center to a bottom dead center of said nacelle intersecting an axis of rotation of the propulsor at an angle no greater than seventy degrees, wherein said bottom dead center is positioned forward of said top dead center along the axis of rotation at an axial distance greater than a shortest distance from said top dead center to said axis of rotation; and
rotating a fan of the propulsor, said fan receiving the ingested boundary layer air via the inlet duct, and said fan being radially encased by the nacelle.
16. The method of claim 15 further comprising:
conditioning the effluent of the propulsor by adjusting the position of one or more exit guide vanes positioned within the nacelle downstream of said fan.
17. The method of claim 15 wherein the step of rotating the fan further comprises providing power to the fan from an electric motor.
18. The method of claim 17 wherein said electric motor is positioned in a chamber defined by the nacelle, and wherein said electric motor provides power to the fan via a shaft and a gearbox.