Aft engine nacelle shape for an aircraft

Patent metadata

Field	Value
Publication number	US-11447259-B2
Application number	US-201916450131-A
Country	US
Kind code	B2
Filing date	Jun 24, 2019
Priority date	Sep 21, 2015
Publication date	Sep 20, 2022
Grant date	Sep 20, 2022

Abstract

An aircraft including a fuselage and an aft engine is provided. The fuselage extends from a forward end of the aircraft towards an aft end of the aircraft. The aft engine is mounted to the fuselage proximate the aft end of the aircraft and includes a fan and a nacelle. The fan is rotatable about a central axis of the aft engine and includes a plurality of fan blades. The nacelle of the aft engine surrounds the plurality of fan blades and defines a bottom portion having a forward end. Additionally, the nacelle defines a curved surface at the forward end of the bottom portion, the curved surface including a reference point where the curved surface defines the smallest radius of curvature. The nacelle further defines a normal reference line extending normal from the reference point. The normal reference line defines an angle with the central axis of the aft engine greater than zero to, e.g., allow for a maximum amount of airflow into the aft engine.

First claim

What is claimed is:

1. An aircraft extending between a forward end and an aft end, the aircraft comprising:
a fuselage defining a top side and a bottom side, the fuselage additionally defining a frustum located forward of the aft end of the aircraft, the fuselage further defining a recessed portion located aft of the frustum; and
an aft engine including a nacelle extending adjacent to the recessed portion of the fuselage;
wherein the frustum defines a bottom reference line extending along the frustum at the bottom side of the fuselage, and
wherein the nacelle of the aft engine includes at least a portion located inward of the bottom reference line.

2. The aircraft of claim 1 , wherein the aft engine defines a central axis, wherein the nacelle defines an inlet, and wherein the inlet defines a non-axis symmetrical shape with respect to the central axis.

3. The aircraft of claim 1 , wherein the nacelle defines an inlet with the fuselage, and wherein the inlet extends substantially 360 degrees around the fuselage.

4. The aircraft of claim 1 , wherein the nacelle of the aft engine extends at least partially around the recessed portion of the fuselage.

5. The aircraft of claim 1 , wherein the nacelle includes a forward end and a bottom portion, wherein the forward end of the bottom portion of the nacelle defines a stagnation point, wherein the forward end of the bottom portion of the nacelle defines a curved shape, and wherein the stagnation point aligns with a point on the forward end having the smallest radius of curvature when the aft engine is operated at maximum capacity.

6. The aircraft of claim 1 , wherein the frustum defines a top reference line extending along the frustum at the top side of the fuselage, the top reference line and the bottom reference line meet at a reference point located aft of the frustum, wherein the recessed portion of the fuselage is indented inwardly from the bottom reference line of the frustrum.

7. The aircraft of claim 6 , wherein the aircraft defines a vertical direction, wherein the frustum is defined in part by a forward plane and an aft plane, wherein the frustum defines a first height at the forward plane and a second height at the aft plane, and wherein the first height is greater than the second height.

8. The aircraft of claim 6 , wherein an entirety of a bottom portion of the nacelle of the aft engine is located inward of the bottom reference line.

9. The aircraft of claim 6 , wherein the nacelle includes a bottom portion, and wherein the bottom portion defines a cord line extending substantially parallel to the bottom reference line.

10. The aircraft of claim 6 , wherein in the nacelle includes a bottom portion and an outer surface, and wherein at least a portion of the outer surface of the nacelle at the bottom portion of nacelle extends substantially parallel to the bottom reference line.

11. The aircraft of claim 6 , wherein the frustum defines a length to average height ratio greater than or equal to about 0.2.

12. An aircraft extending between a forward end and an aft end, the aircraft comprising:
a fuselage defining a top side and a bottom side, the fuselage additionally defining a frustum located forward of the aft end of the aircraft, the fuselage further defining a recessed portion located aft of the frustum; and
an aft engine including a nacelle extending adjacent to the recessed portion of the fuselage;
wherein the aft engine defines a central axis, wherein the nacelle defines an inlet having a top half positioned above the central axis and a bottom half positioned below the central axis, 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.

13. An aircraft defining a longitudinal centerline, the aircraft comprising:
a pair of wings, each wing defining a top side and a bottom side and having landing gear extending from the bottom side thereof;
a fuselage defining a top side and a bottom side, the bottom side of the fuselage and the landing gear together defining a maximum takeoff angle with the longitudinal centerline, the fuselage further defining a recessed portion at the bottom side of the fuselage located aft of the pair of wings and defining an angle with the longitudinal centerline greater than the maximum takeoff angle; and
an aft engine located aft of the pair of wings and including a nacelle extending adjacent to the recessed portion of the fuselage;
wherein a bottom reference line extends along the bottom side of the fuselage, and
wherein the nacelle of the aft engine includes at least a portion located inward of the bottom reference line.

14. The aircraft of claim 13 , wherein the aircraft defines a mean line extending from a forward end to an aft end, and wherein the nacelle extends substantially 360 degrees around the mean line of the aircraft.

15. The aircraft of claim 13 , wherein the nacelle defines an inlet with the fuselage, and wherein the inlet extends substantially 360 degrees around the fuselage.

16. The aircraft of claim 13 , wherein the aft engine defines a central axis, wherein the nacelle defines an inlet, and wherein the inlet defines a non-axis symmetrical shape with respect to the central axis.

17. An aircraft defining a longitudinal centerline and extending between a forward end and an aft end, the aircraft comprising:
a fuselage defining a top side and a bottom side, the fuselage further defining a recessed portion located at the aft end of the aircraft, the recessed portion of the fuselage at the bottom side of the fuselage defining an angle relative to the longitudinal centerline of the aircraft; and
an aft engine located at the aft end of the aircraft and including a nacelle extending adjacent to the recessed portion of the fuselage, the angle defined by the recessed portion of the fuselage relative to the longitudinal centerline being greater than a threshold angle for creating separated flow during normal flight if not for operation of the aft engine;
wherein a bottom reference line extends along the bottom side of the fuselage, and
wherein the nacelle of the aft engine includes at least a portion located inward of the bottom reference line.

18. The aircraft of claim 17 , wherein the angle defined by the recessed portion of the fuselage is greater than about thirteen degrees.

19. The aircraft of claim 17 , wherein the angle defined by the recessed portion of the fuselage is greater than about fifteen degrees.

20. The aircraft of claim 17 , wherein the aircraft defines a mean line extending from the forward end to the aft end, and wherein the nacelle extends substantially 360 degrees around the mean line of the aircraft.

Assignees

• Gen Electric

Inventors

• Marrinan Patrick Michael
• Becker Thomas Lee
• Murrow Kurt David
• Yao Jixian

Classifications

• Y02T50/10

  Drag reduction · CPC title

• B64D27/20 Primary

  within, or attached to, fuselages · CPC title

• B64C1/16

  specially adapted for mounting power plant · CPC title

• B64D2033/0226

  comprising boundary layer control means · CPC title

• B64D33/02

  of combustion air intakes · CPC title