Nacelle for an aircraft aft fan

Patent metadata

Field	Value
Publication number	US-10501196-B2
Application number	US-201615281990-A
Country	US
Kind code	B2
Filing date	Sep 30, 2016
Priority date	Sep 30, 2016
Publication date	Dec 10, 2019
Grant date	Dec 10, 2019

Abstract

An aircraft includes a fuselage extending between a forward end and an aft end. An aft engine is mounted to the aft end of the fuselage, the aft engine defining a centerline. The aft engine further includes a nacelle having a bottom section, the bottom section having a forward lip. The forward lip of the bottom section defines a camber line. The camber line, in turn, defines an angle relative to the centerline of the aft engine greater than or equal to at least about five degrees.

First claim

What is claimed is:

1. An aircraft defining a longitudinal direction and comprising:
a fuselage extending between a forward end and an aft end along the longitudinal direction of the aircraft; and
an aft engine mounted to the aft end of the fuselage and defining a centerline, the aft engine further comprising a nacelle including a bottom section having a forward lip, the forward lip defining a camber line and the camber line of the forward lip defining an angle relative to the centerline of the aft engine greater than or equal to at least about five degrees;
wherein the nacelle of the aft engine further includes a body portion, wherein the nacelle of the aft engine defines an outer surface, wherein the outer surface of the nacelle includes a concave shape between the forward lip of bottom section and the body portion.

2. The aircraft of claim 1 , wherein the camber line of the forward lip is a best fit linear camber line for a forward ten percent of the bottom section of the nacelle.

3. The aircraft of claim 1 , wherein the camber line of the forward lip defines an angle relative to the centerline of the aft engine greater than or equal to at least about ten degrees.

4. The aircraft of claim 1 , wherein the fuselage defines a bottom side having a slanted surface extending towards the aft engine, wherein the slanted surface of the bottom side of the fuselage extends in a first direction, and wherein the camber line of the forward lip is within about ten degrees of being parallel to the first direction.

5. The aircraft of claim 1 , wherein the fuselage defines a bottom side having a slanted surface extending towards the aft engine, wherein the slanted surface of the bottom side of the fuselage extends in a first direction, and wherein the camber line of the forward lip defines an angle with the first direction between about five degrees and about fifteen degrees.

6. The aircraft of claim 1 , wherein the nacelle further comprises a top section, wherein the bottom section of the nacelle defines a forward edge at the forward lip, wherein the top section of the nacelle defines a forward edge, wherein the forward edge of top section is positioned farther forward than a forward edge of the bottom section along the longitudinal direction and defines a reference line extending therebetween, and wherein the reference line defines an angle with the centerline of the aft engine less than about eighty-five degrees.

7. The aircraft of claim 1 , further comprising:
a gas turbine engine; and
an electric generator driven by the gas turbine engine, wherein the aft engine is an electric fan powered by the electric generator.

8. The aircraft of claim 1 , wherein the aft engine is a boundary layer ingestion fan.

9. The aircraft of claim 1 , wherein the nacelle defines an inlet having a top half positioned above the centerline and a bottom half positioned below the centerline, wherein the top half of the inlet defines a top half inlet area, wherein the bottom half of the inlet defines a bottom half inlet area, and wherein the bottom half inlet area is greater than the top half inlet area.

10. The aircraft of claim 1 , wherein the bottom section of the nacelle further comprises the body portion extending from the forward lip to an aft edge, wherein the body section defines a camber line, and wherein a length of the camber line of the forward lip is at least about five percent of the length of the camber line of the body portion of the bottom section.

11. The aircraft of claim 1 , wherein the bottom section of the nacelle further comprises the body portion extending from the forward lip to an aft edge, wherein the body section defines a camber line, and wherein a length of the camber line for the forward lip is at least about ten percent of the length of the camber line of the body portion of the bottom section.

12. The aircraft of claim 1 , wherein the aircraft defines a vertical direction, and wherein the forward lip of the bottom section is oriented downwardly along the vertical direction.

13. A propulsion system for an aircraft, the aircraft comprising a fuselage defining an aft end, the propulsion system comprising:
an aft engine configured to be mounted to the aft end of the fuselage and defining a centerline, the aft engine further comprising a nacelle including a bottom section having a forward lip, the forward lip defining a camber line and the camber line defining an angle relative to the centerline of the aft engine greater than or equal to at least about five degrees;
wherein the nacelle of the aft engine further includes a body portion, wherein the nacelle of the aft engine defines an outer surface, wherein the outer surface of the nacelle includes a concave shape between the forward lip of bottom section and the body portion.

14. The propulsion system of claim 13 , wherein the camber line of the forward lip defines an angle relative to the centerline of the aft engine greater than or equal to at least about ten degrees.

15. The propulsion system of claim 13 , wherein the nacelle of the aft engine further includes the body portion, wherein the nacelle of the aft engine defines an outer surface, wherein the outer surface of the nacelle includes a concave shape between the forward lip of bottom section and the body portion.

16. The propulsion system of claim 13 , wherein the nacelle further comprises a top section, wherein the bottom section of the nacelle defines a forward edge at the forward lip, wherein the top section of the nacelle defines a forward edge, wherein the forward edge of top section is positioned farther forward than a forward edge of the bottom section along the longitudinal direction and defines a reference line extending therebetween, and wherein the reference line defines an angle with the centerline of the aft engine less than about eighty-five degrees.

17. The propulsion system of claim 13 , further comprising:
a gas turbine engine; and
an electric generator driven by the gas turbine engine, wherein the aft engine is an electric fan powered by the electric generator.

18. The propulsion system of claim 13 , wherein the aft engine is a boundary layer ingestion fan.

19. The propulsion system of claim 13 , wherein the bottom section of the nacelle further comprises the body portion extending from the forward lip to an aft edge, wherein the body section defines a camber line, and wherein a length of the camber line of the forward lip is at least about five percent of the length of the camber line of the body portion of the bottom section.

20. A propulsion system for an aircraft, the aircraft comprising a fuselage defining an aft end, the propulsion system comprising:
an aft engine configured to be mounted to the aft end of the fuselage and defining a centerline, the aft engine further comprising a nacelle including a bottom section having a forward lip, the forward lip defining a camber line and the camber line defining an angle relative to the centerline of the aft engine greater than or equal to at least about five degrees; and
one or more structural members extending between the nacelle and the fuselage, the one or more structural members comprising one or more inlet guide vanes, the one or more inlet guide vanes further comprising:
a body portion that is fixed relative to the nacelle; and
at least one tail flap, the at least one tail flap configured to rotate about a substantially radial axis.

21. A propulsion system for an aircraft, the aircraft comprising a fuselage defining an aft en

Assignees

• Gen Electric

Inventors

• Ramakrishnan Kishore
• Marrinan Patrick Michael

Classifications

• B64D29/04 Primary

  associated with fuselages · CPC title

• B64D27/14

  within, or attached to, fuselages · CPC title

• B64D27/18

  within, or attached to, wings · CPC title

• B64D27/08

  within, or attached to, fuselages · CPC title

• B64D27/20

  within, or attached to, fuselages · CPC title