AFT engine nacelle shape for an aircraft

Patent metadata

Field	Value
Publication number	US-10358228-B2
Application number	US-201715794648-A
Country	US
Kind code	B2
Filing date	Oct 26, 2017
Priority date	Sep 21, 2015
Publication date	Jul 23, 2019
Grant date	Jul 23, 2019

Abstract

An aircraft is provided including a fuselage and an aft engine. The fuselage defines a top side, a bottom side, and a frustum located proximate an aft end of the aircraft. The frustum defines a top reference line extending along the frustum at a top side of the fuselage, and a bottom reference line extending along the frustum at a bottom side of the fuselage. The top and bottom reference lines meet at a reference point aft of the frustum. The fuselage further defines a recessed portion located aft of the frustum and indented inwardly from the bottom reference line. The aft engine includes a nacelle extending adjacent to the recessed portion of the fuselage such that the aft engine may be included with the aircraft without interfering with, e.g., a takeoff angle of the aircraft.

First claim

What is claimed is:

1. An aircraft defining a longitudinal centerline and extending between a forward end and an aft end, the aircraft comprising:
a fuselage, extending between a forward end and an aft end of the aircraft, and defining a top side and a bottom side, the fuselage further defining a forward plane and an aft plane, the forward and aft planes being parallel to one another and perpendicular to the longitudinal centerline of the aircraft, the fuselage further defining a frustum lying between the forward and aft planes located at the aft end of the aircraft, wherein the frustum defines a top reference line extending along the frustum at the top side of the fuselage and a bottom reference line extending along the frustum at the bottom side of the fuselage;
a set of landing gear extending from the bottom side of the fuselage, wherein the bottom side of the fuselage and the landing gear together define a maximum takeoff angle with the longitudinal centerline, the fuselage further defining a back portion at the bottom side of the fuselage located at the aft end of the aircraft and defining an angle with the longitudinal centerline greater than the maximum takeoff angle; and
an aft engine located aft of a pair of wings and including a nacelle extending adjacent to the back portion of the fuselage;
wherein the aft engine defines a central axis, wherein the nacelle defines an inlet, wherein the inlet defines a non-axis symmetrical shape with respect to the central axis, wherein the aft engine is mounted to the fuselage at the aft end of the aircraft, wherein the aft engine includes a nacelle, and wherein at least a portion of the nacelle is located inward of at least one of the top reference line or the bottom reference line.

2. The aircraft of claim 1 , wherein the aircraft defines a mean line extending from the forward end to the aft end, and wherein the nacelle extends radially around at least a portion the mean line of the aircraft.

3. The aircraft of claim 1 , wherein the nacelle defines the inlet with the fuselage, and wherein the inlet extends radially around at least portion of the fuselage.

4. The aircraft of claim 1 , wherein the angle defined by the back portion of the fuselage is at least ten percent greater than the maximum takeoff angle.

5. The aircraft of claim 1 , wherein the nacelle defines the inlet with the fuselage, wherein the inlet extends radially around at least portion of the fuselage, wherein a top half of the inlet defines a top half inlet area and a bottom half of the inlet defines a bottom half inlet area, wherein the bottom half inlet area is greater than the top half inlet area.

6. An aircraft defining a longitudinal centerline and extending between a forward end and an aft end, the aircraft comprising:
a fuselage defining a forward plane and an aft plane, the forward and aft planes being parallel to one another and perpendicular to the longitudinal centerline of the aircraft, the fuselage further defining a top side, a bottom side, and a frustum lying between the forward and aft planes located at the aft end of the aircraft, wherein the frustum defines a top reference line extending along the frustum at the top side of the fuselage and a bottom reference line extending along the frustum at the bottom side of the fuselage; and
an aft engine mounted to the fuselage at the aft end of the aircraft, wherein the aft engine includes a nacelle, and wherein at least a portion of the nacelle is located inward of at least one of the top reference line or the bottom reference line.

7. The aircraft of claim 6 , wherein the aircraft defines a mean line extending from the forward end to the aft end, and wherein the nacelle at least partially extends around the mean line of the aircraft.

8. The aircraft of claim 6 , wherein the nacelle at least partially defines an inlet for the aft engine.

9. The aircraft of claim 8 , wherein the nacelle defines the inlet for the aft engine with the fuselage.

10. The aircraft of claim 8 , wherein the inlet extends at least partially around the fuselage of the aircraft, wherein the aft engine defines a central axis, and wherein the inlet defines a non-axis symmetrical shape with respect to the central axis.

11. The aircraft of claim 6 , wherein the frustum is a tapered shape between the forward and aft planes.

12. 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 defining an angle relative to the longitudinal centerline of the aircraft, the fuselage further defining a forward plane and an aft plane, the forward and aft planes being parallel to one another and perpendicular to the longitudinal centerline of the aircraft, the fuselage further defining a frustum lying between the forward and aft planes located at the aft end of the aircraft, wherein the frustum defines a top reference line extending along the frustum at the top side of the fuselage and a bottom reference line extending along the frustum at the bottom side of the fuselage; 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, wherein at least a portion of the nacelle is located inward of at least one of the top reference line or the bottom reference line;
wherein the recessed portion defines a bottom concave portion as viewed from the bottom side of the fuselage.

13. The aircraft of claim 12 , wherein the angle defined by the recessed portion of the fuselage is greater than at least one of about thirteen degrees or about fifteen degrees.

14. The aircraft of claim 12 , 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.

15. The aircraft of claim 12 , 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.

Assignees

• Gen Electric

Inventors

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

Classifications

• B64C1/16

  specially adapted for mounting power plant · CPC title

• B64D27/20 Primary

  within, or attached to, fuselages · CPC title

• B64D33/02

  of combustion air intakes · CPC title

• B64D2033/0226

  comprising boundary layer control means · CPC title

• B64D29/04 Primary

  associated with fuselages · CPC title