Leading edge struction for a flow control system of an aircraft
US-2019202566-A1 · Jul 4, 2019 · US
US11524770B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-11524770-B2 |
| Application number | US-201816147145-A |
| Country | US |
| Kind code | B2 |
| Filing date | Sep 28, 2018 |
| Priority date | Sep 28, 2018 |
| Publication date | Dec 13, 2022 |
| Grant date | Dec 13, 2022 |
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A panel for an active laminar flow control arrangement may comprise a longitudinal wall and one or more division walls extending from the longitudinal wall and extending between the first end and the second end. The panel may be coupled to a nacelle outer skin via a plurality of adhesive fasteners pre-installed onto an inner surface of the outer skin and onto stiffeners and/or stringers associated with the outer skin.
Opening claim text (preview).
What is claimed is: 1. A panel for an active laminar flow control arrangement, comprising: a longitudinal wall extending between a first end and a second end of the panel and extending between a first side and a second side of the panel; a division wall extending from the longitudinal wall and extending between the first end and the second end; a first plurality of apertures disposed along the division wall; and a second plurality of apertures disposed along a perimeter of the panel, wherein the panel is a single, monolithic piece. 2. The panel for an active laminar flow control arrangement of claim 1 , further comprising a sealant disposed on an end of the division wall. 3. The panel for an active laminar flow control arrangement of claim 1 , wherein the division wall is T-shaped. 4. The panel for an active laminar flow control arrangement of claim 1 , further comprising a second division wall extending from the longitudinal wall and oriented parallel with respect to the division wall. 5. The panel for an active laminar flow control arrangement of claim 1 , further comprising a third plurality of apertures disposed in the longitudinal wall between the division wall and the second division wall. 6. The panel for an active laminar flow control arrangement of claim 1 , wherein the panel is made from a composite material. 7. The panel for an active laminar flow control arrangement of claim 1 , further comprising a plurality of indentations formed into the panel and disposed along the division wall, wherein each indentation extends from the longitudinal wall and intersects the division wall. 8. The panel for an active laminar flow control arrangement of claim 7 , wherein each aperture of the first plurality of apertures is located in a bottom wall of each of the indentations, each aperture of the first plurality of apertures is sized to receive a fastener for coupling the panel to an adjacent structure. 9. An active laminar flow control arrangement, comprising: an outer skin having an inner surface, an outer surface, and a perforated area; a panel coupled to the inner surface; and a first plurality of adhesive fasteners adhered to the inner surface of the outer skin and extending through the panel; wherein the panel comprises: a longitudinal wall extending between a first end and a second end of the panel and extending between a first side and a second side of the panel; and a division wall extending from the longitudinal wall and extending between the first end and the second end. 10. The active laminar flow control arrangement of claim 9 , wherein the inner surface is in fluid communication with the outer surface via the perforated area. 11. The active laminar flow control arrangement of claim 10 , further comprising a sealant disposed on an end of the division wall and the inner surface. 12. The active laminar flow control arrangement of claim 10 , wherein the longitudinal wall is oriented substantially parallel with the outer skin. 13. The active laminar flow control arrangement of claim 10 , further comprising an indentation formed into the panel and extending from the longitudinal wall and intersecting the division wall. 14. The active laminar flow control arrangement of claim 9 , further comprising: a structural support arrangement comprising a stiffener disposed at the inner surface of the outer skin; and a second plurality of adhesive fasteners adhered to the stiffener and extending through the panel. 15. The active laminar flow control arrangement of claim 9 , further comprising a first plenum and a second plenum, the first plenum is divided from the second plenum via the division wall. 16. A method of installing a laminar flow control arrangement onto a nacelle inlet, comprising: disposing a sealant over an end of a division wall of a panel; coupling a first plurality of adhesive fasteners onto an inner surface of an outer skin; coupling a second plurality of adhesive fasteners onto a stiffener; and disposing the panel over the first plurality of fasteners and the second plurality of fasteners. 17. The method of claim 16 , further comprising compressing the sealant between the outer skin and the division wall, wherein the division wall divides a cavity to at least partially define a first plenum and a second plenum.
by using a surface having multiple apertures of relatively small openings other than slots · CPC title
Power-plant nacelles, fairings or cowlings · CPC title
of combustion air intakes · CPC title
Construction or attachment of skin panels · CPC title
Nacelles · CPC title
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