Leading edge member for an airfoil of an aircraft
US-2021024221-A1 · Jan 28, 2021 · US
Piccolo tube for de-icing an airfoil structure of an aircraft, de-icing system and airfoil structure
US11873107B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-11873107-B2 |
| Application number | US-202217718899-A |
| Country | US |
| Kind code | B2 |
| Filing date | Apr 12, 2022 |
| Priority date | Apr 13, 2021 |
| Publication date | Jan 16, 2024 |
| Grant date | Jan 16, 2024 |
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- Title
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Abstract
Official abstract text for this publication.
A piccolo tube for de-icing an airfoil structure of an aircraft is disclosed having a shape extending in a longitudinal direction and is configured for installation in an airfoil structure of an aircraft in the longitudinal direction of the airfoil structure. The piccolo tube includes a connector element for receiving heated air from a supply source, and a longitudinally extending air duct having a plurality of outlet openings arranged along the air duct, for supplying and distributing the heated air along the inner side of the airfoil structure. The piccolo tube is curved and its curvature is adapted to a curvature of the airfoil structure in its longitudinal direction. A de-icing system includes the piccolo tube and a supply source for supplying heated air to the piccolo tube. An airfoil structure includes the piccolo tube and/or the de-icing system.
First claim
Opening claim text (preview).
The invention claimed is: 1. A piccolo tube for an aircraft including an airfoil structure, the piccolo tube having a shape extending in a longitudinal direction and configured to be installed in the airfoil structure of the aircraft in the longitudinal direction of the airfoil structure, the piccolo tube comprising: a connector element for receiving heated air from a supply source, a longitudinally extending air duct having a plurality of outlet openings arranged along the air duct, for supplying and distributing the heated air along the inner side of the airfoil structure, wherein the airfoil structure has a curvature in a longitudinal direction along the entire length of the airfoil structure, wherein the piccolo tube is curved having a curvature along an entire length of the piccolo tube, and configured to the curvature of the airfoil structure in the longitudinal direction, and wherein at least a portion of the curvature of the airfoil structure is configured to contour an outer circumference of an engine of the aircraft. 2. The piccolo tube according to claim 1 , wherein at least a portion of the piccolo tube has a constant curvature radius. 3. The piccolo tube according to claim 1 , wherein at least a portion of the piccolo tube is bended vertically in the installed state. 4. The piccolo tube according to claim 1 , wherein the airfoil structure is a slat. 5. The piccolo tube according to claim 1 , further comprising one or more guiding elements integrally formed with the piccolo tube and configured for guiding the piccolo tube during assembly in the airfoil structure. 6. The piccolo tube according to claim 1 , further comprising a removable guiding tool for guiding the piccolo tube during assembly in the airfoil structure. 7. A de-icing system for an airfoil structure of an aircraft, comprising a piccolo tube according to claim 1 and a supply source for supplying heated air to the piccolo tube. 8. An airfoil structure for an aircraft, comprising a piccolo tube according to claim 1 . 9. The airfoil structure according to claim 8 , wherein at least a portion of the piccolo tube and the airfoil structure are bended vertically in the assembled state of the aircraft. 10. The airfoil structure according to claim 8 , wherein at least a portion of the curvature of the airfoil structure is adapted to an outer circumference of an engine of the aircraft. 11. The airfoil structure according to claim 8 , wherein the airfoil structure is a slat. 12. The airfoil structure according to claim 8 , further comprising one or more guiding elements integrally formed with the airfoil structure and configured for guiding the piccolo tube when it is installed in the airfoil structure. 13. The airfoil structure according to claim 8 , further comprising one or more ribs having a cut out for supporting the piccolo tube in the airfoil structure. 14. An aircraft, comprising a de-icing system according to claim 7 . 15. An airfoil structure for an aircraft, comprising a de-icing system according to claim 7 . 16. An aircraft, comprising an airfoil structure according to claim 8 .
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- What does patent US11873107B2 cover?
- A piccolo tube for de-icing an airfoil structure of an aircraft is disclosed having a shape extending in a longitudinal direction and is configured for installation in an airfoil structure of an aircraft in the longitudinal direction of the airfoil structure. The piccolo tube includes a connector element for receiving heated air from a supply source, and a longitudinally extending air duct havi…
- Who is the assignee on this patent?
- Airbus Operations Gmbh
- What technology area does this patent fall under?
- Primary CPC classification B64D15/04. Mapped technology areas include Operations & Transport.
- When was this patent published?
- Publication date Tue Jan 16 2024 00:00:00 GMT+0000 (Coordinated Universal Time) (B2). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 5 related publications on this page (citations in our corpus or others sharing the same primary CPC).