AFT engine nacelle shape for an aircraft

Patent metadata

Field	Value
Publication number	US-9815560-B2
Application number	US-201514859566-A
Country	US
Kind code	B2
Filing date	Sep 21, 2015
Priority date	Sep 21, 2015
Publication date	Nov 14, 2017
Grant date	Nov 14, 2017

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 aft engine defining a central axis mounted to an aircraft at an aft end of the aircraft, the aft engine comprising:
a fan rotatable about the central axis and including a plurality of fan blades;
a nacelle surrounding the plurality of fan blades of the fan and defining a bottom portion having a forward end and a top portion forward end, the nacelle defining a curved surface at the forward end of the bottom portion including a reference point where the curved surface defines the smallest radius of curvature, the nacelle further defining a normal reference line extending normal from the reference point, the normal reference line defining a first angle with the central axis of the aft engine greater than zero; and
a chord line defined by the bottom portion of the nacelle and forming a second angle with the central axis of the aft engine,
wherein said forward end of the bottom portion is farther forward along said central axis than said top portion forward end,
wherein the second angle is between 5 and 20 degrees; and
wherein the aft engine ingests air from a boundary layer of air, and speeds up such air without generating any measurable amount of thrust.

2. The aft engine of claim 1 ,
wherein the bottom portion of the nacelle includes an inside surface and an outside surface,
wherein the inside surface is located within the nacelle, defines a nacelle interior and is adjacent the curved surface at the forward end,
wherein the outside surface is located outside the nacelle, defines a nacelle exterior and is adjacent the curved surface at the forward end, and
wherein the reference point is positioned closer to the outside surface than the inside surface.

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

4. The aft engine of claim 1 , wherein said first angle is greater than about ten degrees.

5. The aft engine of claim 1 , wherein said first angle is greater than about twenty degrees.

6. The aft engine of claim 1 , wherein the nacelle surrounds the central axis of the aft engine.

7. The aft engine of claim 1 further comprising a power source,
wherein the aft engine is powered by the power source, and
wherein the power source is an electric power source.

8. An aircraft extending between a forward end and an aft end and defining a longitudinal centerline, the aircraft comprising:
a fuselage extending from the forward end of the aircraft towards the aft end of the aircraft;
an aircraft frustum;
a bottom reference line extending along the aircraft frustum; and
an aft engine mounted to the fuselage proximate the aft end of the aircraft, the aft engine defining a central axis extending parallel to the longitudinal centerline of the aircraft, the aft engine comprising
a fan rotatable about the central axis and including a plurality of fan blades; and
a nacelle surrounding the plurality of fan blades of the fan and defining a bottom portion having a forward end and a top portion forward end, the nacelle defining a curved surface at the forward end of the bottom portion including a reference point where the curved surface defines the smallest radius of curvature, the nacelle further defining a normal reference line extending normal from the reference point, the normal reference line defining a first angle with the central axis of the aft engine greater than zero;

wherein said forward end of the bottom portion is farther forward along said central axis than said top portion forward end,
wherein the bottom portion of the nacelle further defines a chord line,
wherein the chord line is parallel to the bottom reference line,
wherein the central axis defines a second angle with the chord line between 5 and 20 degrees; and
wherein the aft engine ingests air from a boundary layer of air of the fuselage, and speeds up such air without generating any measurable amount of thrust.

9. The aircraft of claim 8 , 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.

10. The aircraft of claim 8 , wherein the forward end of the bottom portion of the nacelle defines a design stagnation point, and wherein the design stagnation point aligns with the reference point on the forward end having the smallest radius of curvature when the aft engine is operated at maximum capacity.

11. The aircraft of claim 8 , the aircraft further comprising;
a pair of wings;
the fuselage further comprising a recessed portion located along said fuselage aft of the pair of wings and located forward of the aft engine,
wherein the recessed portion comprises a bottom concave portion, and
wherein said first angle is greater than about ten degrees.

12. The aircraft of claim 11 further comprising a power source,
wherein the aft engine is powered by the power source, and
wherein the power source is an electric power source.

13. The aircraft of claim 8 , wherein said first angle is greater than about twenty degrees.

14. The aircraft of claim 8 , wherein said bottom portion has a maximum thickness at an aft-most location of said curved surface.

15. The aircraft of claim 8 , wherein the nacelle defines an inlet with the fuselage of the aircraft.

16. The aircraft of claim 15 , wherein the inlet defined by the nacelle extends substantially 360 degrees around the fuselage of the aircraft.

17. The aft engine of claim 2 , wherein said bottom portion has a max thickness at a location where said inside surface transitions to said curved surface.

18. An aft engine defining a central axis and configured to be mounted to an aircraft at an aft end of the aircraft, the aft engine comprising:
a fan rotatable about the central axis and including a plurality of fan blades; and
a nacelle surrounding the plurality of fan blades of the fan and defining a bottom portion having a forward end and a top portion forward end, the nacelle defining a design stagnation point at the forward end of the bottom portion of the nacelle having a normal reference line extending normal from the design stagnation point, the normal reference line defining a first angle with the central axis of the aft engine greater than zero;
wherein said forward end of the bottom portion is farther forward along said central axis than said top portion forward end,
wherein the bottom portion of the nacelle further defines a chord line,
wherein the normal reference line defines a second angle with the chord line between 5 and 20 degrees; and
wherein the aft engine ingests air from a boundary layer of air, and speeds up such air without generating any measurable amount of thrust.

19. The aft engine of claim 18 , wherein the forward end of the bottom portion of the nacelle defines a curved surface, and wherein the design 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.

Assignees

• Gen Electric

Inventors

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

Classifications

• B64D29/04 Primary

  associated with fuselages · 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