Method and system for a stowable bell-mouth scoop

Patent metadata

Field	Value
Publication number	US-11078870-B2
Application number	US-201716311313-A
Country	US
Kind code	B2
Filing date	Jul 4, 2017
Priority date	Jul 4, 2016
Publication date	Aug 3, 2021
Grant date	Aug 3, 2021

Abstract

A bell-mouth scoop assembly includes an actuator comprising a plurality of hinge members configured to rotate in unison about a respective hinge axis of rotation from a first stowed position to a second deployed position and at least one linkage arm extending outwardly from at least one of the plurality of hinge members. The bell-mouth scoop assembly further comprises a bell-mouth panel comprising a panel longitudinal centerline and pivotably coupled to each linkage arm, in the first stowed position the bell-mouth panel (configured to conform to an outer surface of the with the panel longitudinal centerline aligned about a circumference of the flow discharge nozzle, in the second deployed position the bell-mouth panel configured to extend away from the outer surface of the flow discharge nozzle with the longitudinal centerline aligned parallelly with the nozzle centerline.

First claim

What is claimed is:

1. A bell-mouth scoop assembly for a flow discharge nozzle, the flow discharge nozzle defining an axial direction, a radial direction, and a circumferential direction and comprising a flow discharge nozzle centerline extending in the axial direction which is a direction of flow into or out of the flow discharge nozzle, the bell-mouth scoop assembly comprising:
an actuator comprising:
a plurality of hinge members configured to rotate in unison about a respective hinge axis of rotation from a first stowed position to a second deployed position; and
at least one linkage arm extending outwardly from at least one of the plurality of hinge members, said linkage arm comprising a first hinge connection end, a second distal end, and a body extending therebetween; and

a bell-mouth panel comprising a panel longitudinal centerline and pivotably coupled to each at least one linkage arm,
wherein, in the first stowed position, said bell-mouth panel is oriented with the panel longitudinal centerline aligned with the circumferential direction about a circumference of said flow discharge nozzle, and
wherein, in the second deployed position, said bell-mouth panel is configured to extend away from an outer surface of said flow discharge nozzle with the panel longitudinal centerline having a larger component in the axial direction than in the radial direction or the circumferential direction.

2. The assembly of claim 1 , wherein the hinge axis of rotation is radially displaced from the nozzle centerline and positioned at an angle with respect to the nozzle centerline.

3. The assembly of claim 2 , wherein the angle between each hinge axis of rotation and the nozzle centerline are constant during operation between the first stowed position and the second deployed position.

4. The assembly of claim 1 , wherein a number of said plurality of hinge members is less than a number of said at least one linkage arm, said at least one linkage arms ganged onto said plurality of hinge members.

5. The assembly of claim 1 , wherein said actuator comprises a plurality of actuating devices, each actuating device of the plurality of actuating devices coupled to a single respective hinge member.

6. The assembly of claim 1 , wherein said actuator comprises a plurality of actuating devices, each actuating device of the plurality of actuating devices coupled to more than one hinge member of the plurality of hinge members.

7. The assembly of claim 1 , wherein in the first stowed position, a radially outer extent of said bell-mouth panels is flush with said radially outer surface.

8. The assembly of claim 1 , wherein rotation of the plurality of hinge members about its respective hinge axis of rotation from the first stowed position to the second deployed position causes at least one of a respective bell-mouth panel to rotate from the first stowed position to a second deployed position.

9. The assembly of claim 1 , wherein said flow discharge nozzle further comprises a radially outer surface and a circumferential stowage channel configured to receive said bell-mouth scoop assembly.

10. The assembly of claim 1 , wherein said bell-mouth panel is configured to conform to a radially outer surface of said flow discharge nozzle.

11. The assembly of claim 1 , wherein the hinge axis of rotation is directed at an angle with respect to the circumferential direction.

12. A turbofan engine defining an axial direction, a radial direction, and a circumferential direction, the turbofan engine comprising:
a core turbine engine configured to generate a stream of high energy exhaust gases;
a fan powered by a power turbine driven by the high energy exhaust gases;
a fan bypass duct at least partially surrounding said core turbine engine and said fan; and
a bell-mouth scoop assembly coupled to an aft end of said fan bypass duct, the bell-mouth scoop assembly comprising:
a plurality of hinge members configured to rotate in unison about a respective hinge axis of rotation from a first stowed position to a second deployed position;
at least one linkage arm extending outwardly from at least one of the plurality of hinge members, said linkage arm comprising a first hinge connection end, a second panel connection end, and a body extending therebetween; and
a bell-mouth panel comprising a panel longitudinal centerline and pivotably coupled to each at least one linkage arm,
wherein, in the first stowed position, said bell-mouth panel is configured to conform to an outer surface of said fan bypass duct with the panel longitudinal centerline aligned with the circumferential direction about a circumference of said fan bypass duct, and
wherein, in the second deployed position, said bell-mouth panel is configured to extend away from said outer surface of said fan bypass duct with the panel longitudinal centerline having a larger component in the axial direction than in the radial direction or the circumferential direction.

13. The assembly of claim 12 , wherein the hinge axis of rotation is radially displaced from the rotational axis of the turbofan engine and positioned at an angle with respect to the rotational axis.

14. The assembly of claim 13 , wherein the angle between each hinge axis of rotation and the rotational axis of the turbofan engine is constant during operation between the first stowed position and the second deployed position.

15. The assembly of claim 12 , wherein a number of said plurality of hinge members is less than a number of said at least one linkage arm, said at least one linkage arms ganged onto said plurality of hinge members.

16. The assembly of claim 12 , wherein said actuator comprises a plurality of actuating devices, each actuating device of the plurality of actuating devices coupled to a single respective hinge member.

17. The assembly of claim 12 , wherein the hinge axis of rotation is directed at an angle with respect to the circumferential direction.

Assignees

• Gen Electric

Inventors

• Iglewski Tomasz

Classifications

• F02K1/70 Primary

  using thrust reverser flaps or doors mounted on the fan housing · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F05D2240/128

  Nozzles · CPC title

• B64C9/36

  the members being fuselages or nacelles · CPC title

• F02K1/64 Primary

  Reversing fan flow · CPC title