Inlet vane forward of aircraft propulsion system airflow inlet

Patent metadata

Field	Value
Publication number	US-2026070647-A1
Application number	US-202418827084-A
Country	US
Kind code	A1
Filing date	Sep 6, 2024
Priority date	Sep 6, 2024
Publication date	Mar 12, 2026
Grant date	—

Abstract

An assembly is provided for an aircraft. This aircraft assembly includes an airframe structure, a propulsion system and a vane. The airframe structure includes a fuselage and at least two wings. The fuselage extends longitudinally along a longitudinal centerline from a forward end of the fuselage to an aft end of the fuselage. The wings extend laterally from opposing sides of the fuselage. The propulsion system is mounted to the airframe structure. The propulsion system includes an airflow inlet into the propulsion system. The airflow inlet is spaced vertically out from a top side of the airframe structure. The vane projects vertically out from the top side of the airframe structure to a distal end of the vane. The vane laterally overlaps and is longitudinally forward of the airflow inlet.

First claim

1 . An assembly for an aircraft, comprising:
an airframe structure including a fuselage and at least two wings, the fuselage extending longitudinally along a longitudinal centerline from a forward end of the fuselage to an aft end of the fuselage, and the at least two wings extending laterally from opposing sides of the fuselage; a propulsion system mounted to the airframe structure, the propulsion system including an airflow inlet into the propulsion system, and the airflow inlet spaced vertically out from a top side of the airframe structure; and a vane projecting vertically out from the top side of the airframe structure to a distal end of the vane, the vane laterally overlapping and longitudinally forward of the airflow inlet; wherein the propulsion system further includes a duct and a propulsor rotor within the duct downstream of the airflow inlet; wherein the propulsor rotor has a diameter; wherein a length of the vane extends from a leading edge of the vane to a trailing edge of the vane; and wherein a quotient of the length of the vane divided by the diameter is between 0.4 and 2.1.

2 . The assembly of claim 1 , wherein the vane is longitudinally next to the airflow inlet.

3 . The assembly of claim 1 , wherein
the vane extends along a vane centerline from a leading edge of the vane to a trailing edge of the vane; and the vane centerline is parallel with the longitudinal centerline.

4 . The assembly of claim 1 , wherein
the vane extends along a vane centerline from a leading edge of the vane to a trailing edge of the vane; and the vane centerline is angularly offset from the longitudinal centerline by a non-zero acute angle equal to or less than twenty degrees.

5 . The assembly of claim 1 , wherein
the vane extends along a vane centerline from a leading edge of the vane to a trailing edge of the vane; and a vertical height of a leading edge section of the vane at the leading edge is greater than the vertical height of a trailing edge section of the vane at the trailing edge.

6 . The assembly of claim 1 , wherein
the vane extends along a vane centerline from a leading edge of the vane to a trailing edge of the vane; and a vertical height of a leading edge section of the vane at the leading edge is less than the vertical height of a trailing edge section of the vane at the trailing edge.

7 . The assembly of claim 1 , wherein
the vane extends along a vane centerline from the leading edge of the vane to the trailing edge of the vane; and a vertical height of a leading edge section of the vane at the leading edge is equal to the vertical height of a trailing edge section of the vane at the trailing edge.

8 . (canceled)

9 . (canceled)

10 . The assembly of claim 1 , wherein
the leading edge of the vane is longitudinally spaced from the airflow inlet by a longitudinal distance; and a quotient of the longitudinal distance divided by the diameter is between 0.2 and 2.0.

11 . The assembly of claim 1 , wherein
the propulsion system is mounted to the airframe structure by a pylon; the leading edge of the vane is longitudinally spaced from the pylon by a longitudinal distance; and a quotient of the longitudinal distance divided by the diameter is between 0.3 and 3.0.

12 . The assembly of claim 1 , wherein a quotient of a maximum vertical height of the vane divided by the diameter is equal to or less than 1 . 0 .

13 . An assembly for an aircraft, comprising:
an airframe structure including a fuselage and at least two wings, the fuselage extending longitudinally along a longitudinal centerline from a forward end of the fuselage to an aft end of the fuselage, and the at least two wings extending laterally from opposing sides of the fuselage; a propulsion system mounted to the airframe structure, the propulsion system including an airflow inlet into the propulsion system, and the airflow inlet spaced vertically out from a top side of the airframe structure; and a vane projecting vertically out from the top side of the airframe structure to a distal end of the vane, the vane laterally overlapping and longitudinally forward of the airflow inlet; wherein the airflow inlet is spaced vertically out from the top side of the airframe structure by a vertical distance; and wherein a quotient of the vertical distance divided by a maximum vertical height of the vane is between 0.25 and 40.

14 . An assembly for an aircraft, comprising:
an airframe structure including a fuselage and at least two wings, the fuselage extending longitudinally along a longitudinal centerline from a forward end of the fuselage to an aft end of the fuselage, and the at least two wings extending laterally from opposing sides of the fuselage; a propulsion system mounted to the airframe structure, the propulsion system including an airflow inlet into the propulsion system, and the airflow inlet spaced vertically out from a top side of the airframe structure; and a vane projecting vertically out from the top side of the airframe structure to a distal end of the vane, the vane laterally overlapping and longitudinally forward of the airflow inlet; wherein a length of the vane extends from a leading edge of the vane to a trailing edge of the vane; and wherein a quotient of a maximum thickness of the vane divided by the length of the vane is between 0.05 and 0.2.

15 . The assembly of claim 1 , wherein
a point of a maximum thickness of the vane is spaced from the leading edge of the vane by a distance; and a quotient of the distance divided by the length of the vane is between 0.05 and 0.40.

16 . The assembly of claim 1 , wherein
the aircraft is a blended wing body aircraft; and the airframe structure is a structure of the blended wing body aircraft.

17 . The assembly of claim 1 , wherein the propulsion system is external to the airframe structure.

18 . The assembly of claim 1 , wherein
the propulsion system is mounted to the airframe structure by a pylon; and the pylon projects vertically out from the top side of the airframe structure to the propulsion system.

19 . (canceled)

20 . (canceled)

Assignees

• Rtx Corp

Inventors

• Kupratis Daniel B
• Hanrahan Paul R
• Mylrea Benjamin T

Classifications

• B64C2039/105

  of blended wing body type · CPC title

• B64C11/001

  Shrouded propellers · CPC title

• B64D27/14

  within, or attached to, fuselages · CPC title

• B64D29/04

  associated with fuselages · CPC title

• B64C1/068 Primary

  Fuselage sections · CPC title