Aircraft having embedded engines

Patent metadata

Field	Value
Publication number	US-11247776-B2
Application number	US-201916372337-A
Country	US
Kind code	B2
Filing date	Apr 1, 2019
Priority date	Apr 1, 2019
Publication date	Feb 15, 2022
Grant date	Feb 15, 2022

Abstract

An aircraft having a blended-wing-body configuration includes a centerbody, a pair of wings, at least one pair of engines, a pair of air inlets, and a pair of exhaust outlets. The centerbody has an airfoil-shaped cross section, an aircraft centerline, an aft portion, an upper mold line, a lower mold line, and a pair of centerbody leading edge portions respectively on opposite sides of the aircraft centerline. The wings are integral with the centerbody. The pair of engines are located on opposite sides of the aircraft centerline and are mounted within the centerbody between the upper mold line and the lower mold line. The pair of air inlets are located respectively along the centerbody leading edge portions and are respectively fluidly coupled to the pair of engines. The pair of exhaust outlets our located in the aft portion of the centerbody and our respectively fluidly coupled to the pair of engines.

First claim

What is claimed is:

1. An aircraft having a blended-wing-body configuration, comprising:
a centerbody having an airfoil-shaped cross section, an aircraft centerline, an aft portion, an upper mold line, a lower mold line, and a pair of centerbody leading edge portions respectively on opposite sides of the aircraft centerline;
a pair of wings integral with the centerbody;
at least one pair of engines located on opposite sides of the aircraft centerline and mounted within the centerbody between the upper mold line and the lower mold line, each engine has an engine centerline;
a pair of air inlets located respectively along the pair of centerbody leading edge portions and respectively fluidly coupled to the pair of engines;
a pair of exhaust outlets located in the aft portion of the centerbody and respectively fluidly coupled to the pair of engines, each exhaust outlet has an outlet geometric center located inboard of the engine centerline; and
a pair of exhaust ducts respectively fluidly coupling the pair of exhaust outlets to the pair of engines, each exhaust duct has a slight S-shaped configuration when the aircraft is viewed from a top-down direction, the S-shaped configuration allowing exhaust from each engine to smoothly flow to the exhaust outlet.

2. The aircraft of claim 1 wherein:
the pair of exhaust outlets are defined in the upper mold line of the aft portion of the centerbody.

3. The aircraft of claim 2 wherein:
each exhaust outlet has an exhaust duct cowling protruding above the upper mold line of the centerbody.

4. The aircraft of claim 1 , wherein:
the centerbody has an airfoil thickness-to-chord ratio of at least 10 percent;
each wing has an airfoil thickness-to-chord ratio of less than 10 percent; and
the aircraft has a wing-centerbody juncture at a location where the airfoil thickness-to-chord ratio changes from less than 10 percent to at least 10 percent.

5. The aircraft of claim 1 , further including:
a transverse axis oriented perpendicular to the aircraft centerline;
the centerbody having a centerbody trailing edge portion having a centerbody trailing edge sweep angle defined relative to the transverse axis;
each one of the wings having a wing trailing edge portion having a wing trailing edge sweep angle defined relative to the transverse axis; and
the wing trailing edge sweep angle being different than the centerbody trailing edge sweep angle on each side of the aircraft such that an intersection of the wing trailing edge portion with the centerbody trailing edge portion defines a trailing edge planform break.

6. The aircraft of claim 1 wherein:
each exhaust outlet has a rectangular shape with rounded corners.

7. A method of operating an aircraft having a blended-wing-body configuration, comprising:
drawing air into a pair of air inlets located respectively along a pair of centerbody leading edge portions on opposite sides of an aircraft centerline of a centerbody of the aircraft, the centerbody having an airfoil-shaped cross section, the aircraft including a pair of wings integral with the centerbody;
passing the air from the air inlets into a pair of engines on opposite sides of the aircraft centerline and mounted within the centerbody between an upper mold line and a lower mold line of the centerbody;
combusting a fuel-air mixture within the pair of engines; and
discharging an exhaust of combustion of the fuel-air mixture from a pair of exhaust outlets respectively fluidly coupled to the pair of engines, the pair of exhaust outlets each located inboard of an engine centerline respectively of the pair of engines, the exhaust passing through a pair of exhaust ducts respectively fluidly coupling the pair of exhaust outlets to the pair of engines, each exhaust duct has a slight S-shaped configuration when the aircraft is viewed from a top-down direction, the S-shaped configuration allowing the exhaust from each engine to smoothly flow to the exhaust outlet.

8. The method of claim 7 , wherein combusting the fuel-air mixture within the pair of engines comprises:
combusting the fuel-air mixture within a pair of turbine engines each having a bypass ratio of from about 5-20.

9. The method of claim 7 , further comprising:
acoustically blocking, using a pair of vertical stabilizers located on opposite sides of an aft portion of the centerbody, at least a portion of exhaust noise emanating from the pair of exhaust outlets.

10. The method of claim 7 wherein discharging the exhaust from the pair of exhaust outlets further comprises:
discharging the exhaust from the pair of exhaust outlets, each exhaust outlet having an exhaust duct cowling protruding above the upper mold line of the centerbody.

11. An aircraft having a flying wing configuration, comprising:
a pair of wings integral with each other and collectively defining an aircraft centerline, each one of the wings having an upper mold line, a lower mold line, a wing leading edge portion and a wing trailing edge portion;
at least one pair of engines located on opposite sides of the aircraft centerline and mounted respectively within the pair of wings between the upper mold line and the lower mold line, each engine has an engine centerline;
a pair of air inlets located respectively along the wing leading edge portions and respectively fluidly coupled to the pair of engines;
a pair of exhaust outlets respectively fluidly coupled to the pair of engines, each exhaust outlet has an outlet geometric center located inboard of the engine centerline; and
a pair of exhaust ducts respectively fluidly coupling the pair of exhaust outlets to the pair of engines, each exhaust duct has a slight S-shaped configuration when the aircraft is viewed from a top-down direction, the S-shaped configuration allowing exhaust from each engine to smoothly flow to the exhaust outlet.

12. The aircraft of claim 11 , wherein:
each one of the engines of the pair has a bypass ratio of from 5 to 20.

13. The aircraft of claim 11 , wherein:
the pair of exhaust outlets are defined in the upper mold line respectively of the pair of wings.

14. The aircraft of claim 13 wherein:
each exhaust outlet has an exhaust duct cowling protruding above the upper mold line of one of the wings.

15. The aircraft of claim 11 , wherein:
the aircraft has a nose and an aircraft center of gravity;
each one of the engines has an engine center of gravity;
the engine center of gravity of each one of the engines is located within a distance, from the aircraft center of gravity, of 20 percent of a distance from of a forwardmost point of the nose to the aircraft center of gravity; and
the distance being measured along the aircraft centerline.

16. A method of operating an aircraft having a flying wing configuration, comprising:
drawing air into a pair of air inlets located respectively along a pair of wing leading edge portions respectively of a pair of wings on opposite sides of an aircraft centerline of the aircraft, the pair of wings being integral with each other;
passing the air from the air inlets into a pair of engines on opposite sides of the aircraft centerline and mounted respectively within the pair of wings between an upper mold line and a lower mold line, each one of the pair of engines configured as a turbofan engine;
combusting a fuel-air mixture within the pair of engines; and
discharging an exhaust of combustion of the fuel-air mixture from a pair of exhaust outlets respectively fluidly coupled to the pair of engines, the pair of exhaust outlets each located inboard of an engine centerline respectively of the pair of engi

Assignees

• Boeing Co

Inventors

• Princen Norman H
• Liebeck Robert H
• Lawson Edward L
• Harber Benjamin A

Classifications

• B64D33/06

  Silencing exhaust or propulsion jets · CPC title

• B64D2033/0253

  specially adapted for particular type of aircraft · CPC title

• B64D33/02

  of combustion air intakes · CPC title

• B64C2039/105

  of blended wing body type · CPC title

• B64D2033/0286

  for turbofan engines · CPC title