Aft engine for an aircraft

Patent metadata

Field	Value
Publication number	US-9821917-B2
Application number	US-201514859514-A
Country	US
Kind code	B2
Filing date	Sep 21, 2015
Priority date	Sep 21, 2015
Publication date	Nov 21, 2017
Grant date	Nov 21, 2017

Abstract

A propulsion system for an aircraft is provided having an aft engine configured to be mounted to the aircraft at an aft end of the aircraft. The aft engine includes a fan rotatable about a central axis of the aft engine having a plurality of fan blades. The aft engine also includes a nacelle encircling the plurality of fan blades with one or more structural members extending between the nacelle and the mean line of the aircraft at a location forward of the plurality of fan blades when the aft engine is mounted to the aircraft. The aft engine may increase a net thrust of the aircraft when mounted to the aircraft.

First claim

What is claimed is:

1. A propulsion system for an aircraft having a fuselage, the propulsion system comprising:
an aft engine configured to be mounted to the aircraft at an aft end of the aircraft, the aft engine defining a central axis and including
a fan rotatable about the central axis of the aft engine and including a plurality of fan blades;
a nacelle encircling the plurality of fan blades of the fan and extending around the mean line of the aircraft at the aft end of the aircraft when the aft engine is mounted to the aircraft; and
one or more structural members extending between the nacelle and the fuselage of the aircraft at a location forward of the plurality of fan blades when the aft engine is mounted to the aircraft,
wherein the fan of the aft engine includes a fan shaft and a tail cone, wherein fan shaft is rotatable about the axial centerline of the aft engine, and wherein the tail cone is attached to the fan shaft such that the tail cone is also rotatable about the axial centerline of the aft engine.

2. The propulsion system of claim 1 , wherein the aft engine is configured as a boundary layer ingestion fan.

3. The propulsion system of claim 1 , wherein the aft engine further includes a tail cone and one or more outlet guide vanes, wherein the one or more outlet guide vanes extend from the nacelle to the tail cone.

4. The propulsion system of claim 1 , wherein the fan of the aft engine is configured as a variable pitch fan.

5. The propulsion system of claim 1 , wherein the nacelle defines an inlet extending substantially 360 degrees around the mean line of the aircraft when the aft engine is mounted to the aircraft.

6. The propulsion system of claim 1 , wherein the aft engine defines a circumferential direction, and wherein the one or more structural members include a plurality of structural members spaced along the circumferential direction of the aft engine.

7. The propulsion system of claim 1 , wherein the aft engine defines a radial direction, and wherein the one or more structural members include a plurality of structural members extending substantially along the radial direction of the aft engine.

8. The propulsion system of claim 1 , wherein the one or more structural members are configured as inlet guide vanes.

9. The propulsion system of claim 1 , wherein the one or more structural members are configured as variable inlet guide vanes.

10. The propulsion system of claim 1 , wherein the one or more structural members include at least one of stabilizer of the aircraft.

11. The propulsion system of claim 1 , wherein the aft engine defines an axial direction, and wherein the one or more structural members define an angle with the axial direction between about zero degrees and about ninety degrees.

12. The propulsion system of claim 1 , wherein the aft engine is configured to be mounted to an aircraft having a pair of wings, and wherein the propulsion system further includes two or more aircraft engines, each of which mounted to one of the pair of wings of the aircraft.

13. A boundary layer ingestion fan for mounting to an aircraft at an aft end of the aircraft, the boundary layer ingestion fan comprising:
a fan rotatable about a central axis of the boundary layer ingestion fan and including a plurality of fan blades;
a nacelle encircling the plurality of fan blades of the fan and defining an inlet with the fuselage of the aircraft, the inlet extending substantially around the fuselage of the aircraft when the boundary layer ingestion fan is mounted at the aft end of the aircraft; and
one or more structural members attached to the nacelle at a location forward of the plurality of fan blades of the fan for mounting the boundary layer ingestion fan to the aircraft,
wherein the fan of the aft engine includes a fan shaft, wherein the fan shaft is mechanically coupled, through a gearbox, to a power source located forward of the plurality of fan blades of the fan.

14. The boundary layer ingestion fan of claim 13 , wherein the boundary layer ingestion fan defines a circumferential direction, and wherein the one or more structural members include a plurality of structural members spaced along the circumferential direction of the boundary layer ingestion fan.

15. The boundary layer ingestion fan of claim 13 , wherein the boundary layer ingestion fan defines a radial direction, and wherein the one or more structural members include a plurality of structural members extending substantially along the radial direction of the boundary layer ingestion fan.

16. The boundary layer ingestion fan of claim 13 , wherein the one or more structural members are configured as inlet guide vanes.

17. The boundary layer ingestion fan of claim 13 , wherein the boundary layer ingestion fan further includes a tail cone and one or more outlet guide vanes, wherein the one or more outlet guide vanes extend from the nacelle to the tail cone.

Assignees

• Gen Electric

Inventors

• Becker Thomas Lee
• Murrow Kurt David
• Marrinan Patrick Michael
• Miller Brandon Wayne

Classifications

• B64D27/14 Primary

  within, or attached to, fuselages · CPC title

• B64D2033/0226

  comprising boundary layer control means · CPC title

• B64D27/20 Primary

  within, or attached to, fuselages · CPC title

• B64C2230/00

  Boundary layer controls · CPC title

• B64D29/04

  associated with fuselages · CPC title