Leading-edge arrangement for an aircraft

Patent metadata

Field	Value
Publication number	US-11840337-B2
Application number	US-202017425264-A
Country	US
Kind code	B2
Filing date	Jun 24, 2020
Priority date	Jun 27, 2019
Publication date	Dec 12, 2023
Grant date	Dec 12, 2023

Abstract

A leading-edge arrangement for an aircraft is proposed, comprising a plurality of movable flow bodies, a supply duct, an air transfer duct, and at least one perforated tube. The movable flow bodies are arranged in a consecutive arrangement to form a row with a first end and a second end. The supply duct reaches into an interior of one of the flow bodies at the first end. The air transfer duct connects to the supply duct and extends at least through the interior of the respective flow body in the direction towards the second end. The at least one perforated tube is arranged inside at least one of the flow bodies that directly follows on. The at least one perforated tube is in fluid communication with the transfer duct. The transfer duct is configured to transfer air from the supply duct into the at least one perforated tube.

First claim

The invention claimed is:

1. A leading-edge arrangement for an aircraft, comprising:
a plurality of movable flow bodies,
a supply duct,
an air transfer duct, and
at least one perforated tube,
wherein the movable flow bodies are arranged in a consecutive arrangement to form a row with a first end and a second end,
wherein the supply duct reaches into an interior of a first flow body at the first end,
wherein the air transfer duct connects to the supply duct and extends at least through the interior of the first flow body in a direction towards the second end,
wherein the air transfer duct is unperforated within the first flow body,
wherein the at least one perforated tube is arranged inside at least one of the flow bodies that directly follows from the first flow body,
wherein the at least one perforated tube is in fluid communication with the air transfer duct, and
wherein the air transfer duct is configured to transfer air from the supply duct into the at least one perforated tube.

2. The leading-edge arrangement according to claim 1 , wherein the at least one perforated tube is a piccolo tube configured to eject air to form a thermal anti- or de-icing device.

3. The leading-edge arrangement according to claim 1 , wherein the supply duct is configured to route bleed air from an aircraft engine to the air transfer duct and the at least one piccolo tube.

4. The leading-edge arrangement according to claim 1 ,
wherein the flow bodies each comprise a forward end and a rear end, and
wherein the supply duct extends through the rear end of the first flow body at the first end.

5. The leading-edge arrangement according to claim 4 ,
wherein the supply duct comprises a telescopic duct section extending through the rear end of the first flow body that is arranged at the first end, and
wherein the telescopic duct section is in fluid communication with an angular connector, which connects to the air transfer duct.

6. The leading-edge arrangement according to claim 1 , wherein the air transfer duct extends into at least two flow bodies.

7. The leading-edge arrangement according to claim 1 , wherein the air transfer duct is coupled with the at least one piccolo tube in the interior of one of the flow bodies.

8. The leading-edge arrangement according to claim 1 , wherein the air transfer duct is coupled with the at least one piccolo tube between two adjacent flow bodies.

9. The leading-edge arrangement according to claim 1 , wherein a section of 10 to 75 percent of a length of the air transfer duct comprises perforations to eject air that is transferred by the air transfer duct.

10. The leading-edge arrangement according to claim 9 , wherein the section comprising perforations comprises 25 to 50 percent of the length of the air transfer duct.

11. The leading-edge arrangement according to claim 9 ,
wherein the perforations of the air transfer duct are arranged at a side of the respective flow body that faces away from the first end.

12. The leading-edge arrangement according to claim 1 , wherein a transition section in the interior of one of the flow bodies connects one of the at least one perforated tube and the air transfer duct.

13. The leading-edge arrangement according to claim 1 , wherein the flow bodies are leading-edge high lift devices.

14. A wing having a fixed wing component and a leading-edge arrangement according to claim 1 ,
wherein the flow bodies of the leading-edge arrangement are movably supported on the fixed wing component, and
wherein the supply duct extends through a section of the fixed wing component.

15. The wing according to claim 14 , wherein the flow bodies comprise at least one of a leading-edge slat and of a droop nose device.

16. An aircraft having two wings according to claim 14 , and engines attached to the wings, wherein the supply duct of each wing extends from an engine to the leading-edge arrangement.

Assignees

• Airbus Operations Gmbh

Inventors

• Bensmann Stefan
• Erban Marcus
• Fees Martin

Classifications

• B64C9/26 Primary

  by multiple flaps · CPC title

• B64C3/50

  by leading or trailing edge flaps · CPC title

• B64D15/04 Primary

  Hot gas application · CPC title

• B64C9/22 Primary

  at the front of the wing · CPC title

• Y02T50/40

  Weight reduction · CPC title