Apparatus for laminar flow control

Patent metadata

Field	Value
Publication number	US-11142296-B2
Application number	US-201816165260-A
Country	US
Kind code	B2
Filing date	Oct 19, 2018
Priority date	Oct 20, 2017
Publication date	Oct 12, 2021
Grant date	Oct 12, 2021

Abstract

Apparatus for laminar flow control for a skin panel for an aircraft including a body for receipt into a recess of the skin panel. The body defines a chamber. The body includes an outer portion defining one or more micro apertures through the outer portion, each of the one or more micro apertures being in fluid communication with the chamber. The body includes a support portion supporting the outer portion, the support portion defining at least one outlet for allowing air to be drawn from the chamber in use by a suction means in fluid communication with the outlet in use. The apparatus is arranged such that, in use, air is drawn through the one or more micro apertures into the chamber and out of the outlet, thereby to promote laminar airflow over the outer portion in use.

First claim

The invention claimed is:

1. A joint strap for controlling laminar flow over a skin of an aircraft, the joint strap configured to be received into a recess of the skin to join a first skin panel to a second skin panel, the joint strap comprising:
a body defining a chamber, and the body comprising:
an outer portion configured to align with an outer surface of the skin panel when the body is received in the recess, the outer portion defining one or more micro apertures through the outer portion, each of the one or more micro apertures in fluid communication with the chamber; and
a support portion configured to support outer portion, the support portion defining at least one outlet from the chamber for air drawn from the chamber by suction through the outlet,

wherein the joint strap is arranged such that, in use, air is drawn through the one or more micro apertures into the chamber and out of the outlet, thereby to promote laminar airflow over the outer portion in use;
wherein the chamber is between a base portion and the outer portion,
wherein the support portion comprises the base portion and at least one support member,
wherein the at least one support members extends from the base portion and through the chamber to support the outer portion;
wherein the body comprises at least one fastener receiving portion configured to receive a respective fastener to fasten the body to the first skin panel or the second skin panel, and -each of the at least one fastener receiving portion comprises a respective one of the at least one support members.

2. The joint strap according to claim 1 , wherein the outlet is defined in the base portion.

3. The joint strap according to claim 1 , wherein the outlet comprises a connector configured to connect the outlet to a suction device.

4. The joint strap according claim 1 , wherein the outer portion is integrally formed with the support portion, such that the outer portion and the support portion are a single piece component.

5. The joint strap according to claim 1 , wherein the outer portion is bonded to the support portion.

6. The joint strap according to claim 1 , wherein each of the one or more micro-apertures has a diameter in a range of 45 μm to 65 μm.

7. The joint strap according to claim 1 , wherein the outer portion has a thickness in a range 0.8 mm to 1.0 mm.

8. The joint strap according to claim 1 , wherein the apparatus is arranged for hybrid laminar flow control for an aircraft.

9. The joint strap according to claim 1 , wherein one or more of the micro apertures are adjacent to one or more of the fastener receiving portions.

10. The joint strap according to claim 1 , wherein one or more of the micro apertures are positioned such that in use the one or more micro apertures are immediately downstream of one or more of the fastener receiving portions.

11. The joint strap according to claim 1 , wherein one or more of the at least one fastener receiving portions comprises a respective aperture in a respective one of the support members, wherein the aperture is configured to receive the respective fastener.

12. A system for laminar flow control for an aircraft, the system comprising:
a first skin panel comprising a first recess and a first edge adjacent the first recess;
a second skin panel comprising a second recess, wherein the second skin panel includes a second edge adjacent both the second recess and the first edge;
a joint strap seated in the first and second recesses and spanning between the first and second skin panels, the joint strap including:
an outer portion having an outer surface aligned with outer surfaces of the first and second skin panels, wherein the outer portion includes micro apertures open to the outer surface of the outer portion and open to an interior chamber of the joint strap;
a support portion supporting the outer portion, wherein the support portion includes a base portion opposite the outer portion, and support members within the interior chamber, wherein the support members span between the base portion and the outer portion;
a fastener receiving aperture in each of a plurality of the support members;
a fastener in each of the fastener receiving apertures, wherein each fastener secures the base portion to the first skin panel or the second skin panel; and

an outlet in the support portion and configured to be coupled to a suction source, wherein air is drawn through the micro-apertures, into the interior chamber and through the outlet by the suction source.

13. The system according to claim 12 , wherein the first skin panel comprises a first recess in which a first portion of the body of the apparatus is received, and the second skin panel comprises a second recess in which a second portion of the apparatus is received.

14. The system according to claim 12 , wherein an outer surface of the outer portion of the body of the apparatus is aligned with an outer surface of the first or second skin panel.

15. The system according to claim 12 , wherein the first or second skin panel is one of a leading-edge skin panel for an aircraft wing and a wing box skin panel of an aircraft wing.

16. A laminar flow control apparatus comprising:
a joint strap configured to cover a gap between a first skin panel and a second skin panel of an aircraft, wherein the joint strap includes:
an internal cavity;
an outer portion including micro apertures providing fluid communication between the internal cavity and an outer surface of the joint strap, wherein the outer surface is aligned with an outer surface of the first and an outer surface of the second skin panel;

a support portion including a base portion opposite the outer portion, wherein the internal cavity is between the base portion and the outer portion,
support members spanning between the base portion and the outer portion, and the support members are within the internal cavity,
a fastener receiving aperture in each of a plurality of the support members;
fasteners each in a respective one of the fastener receiving apertures, wherein a first fastener of the fasteners secures the joint strap to the first skin panel and a second fastener of the fasteners secures the joint strap to the second skin panel; and
at least one outlet extending through the base portion, in fluid communication with the internal cavity, and configured to be connected to a suction source;
wherein, the suction source, while connected to the at least one outlet, draws air from the internal cavity causing air to be drawn in to the internal cavity from the exterior of the joint strap via the at least one micro aperture.

17. A skin panel assembly for an aerodynamic structure of an aircraft, the skin panel assembly including:
a first skin panel including a first outer surface, a first recess in the first outer surface, and a first edge adjacent the first recess;
a second skin panel including a second outer surface, a second recess in the second outer surface, and a second edge adjacent the second recess and adjacent the first recess of the first skin panel;
a joint strap spanning a gap between the first and second edges of the first and second skin panels, wherein the joint strap is seated in the first and second recesses and the joint strap includes:
a third outer skin surface aligned with the first and second outer surfaces;
micro-apertures in the third outer skin surface;
an internal chamber within the joint strap, wherein the micro-apertures are in fluid communication with the internal chamber, wherein the internal chamber overlaps at least partially the first and second reces

Assignees

• Airbus Operations Ltd

Inventors

• Holmes Vernon
• Evans Rodney

Classifications

• B64C1/0009 Primary

  Aerodynamic aspects · CPC title

• B64C2230/06

  by explicitly adjusting fluid flow, e.g. by using valves, variable aperture or slot areas, variable pump action or variable fluid pressure · CPC title

• B64C2230/04

  by actively generating fluid flow · CPC title

• B64C2230/20

  by passively inducing fluid flow, e.g. by means of a pressure difference between both ends of a slot or duct · CPC title

• B64C3/36

  Structures adapted to reduce effects of aerodynamic or other external heating · CPC title