Anti-icing apparatus and system

Patent metadata

Field	Value
Publication number	US-9815558-B2
Application number	US-201514963708-A
Country	US
Kind code	B2
Filing date	Dec 9, 2015
Priority date	Dec 9, 2015
Publication date	Nov 14, 2017
Grant date	Nov 14, 2017

Abstract

An anti-icing apparatus includes an anti-icing piccolo tube for an aircraft component with a plurality of self rotating elements. Each self rotating element of the plurality of self rotating elements includes a first inlet to receive a working fluid, a second inlet to receive the working fluid, a peripheral layer that connects the first inlet and the second inlet, and a plurality of outlets placed on the peripheral layer that expulses the working fluid through jets. The jets rotate each self rotating element and dynamically impinges the working fluid on an internal surface of the aircraft component.

First claim

What is claimed is:

1. An anti-icing piccolo tube for an aircraft component with a plurality of self rotating elements, each self rotating element of the plurality of self rotating elements comprising:
a first inlet to receive a working fluid;
a second inlet to receive the working fluid;
a peripheral layer that connects the first inlet and the second inlet; and
a plurality of outlets placed on the peripheral layer that expulses the working fluid through jets,
wherein the jets rotate each self rotating element and dynamically impinges the working fluid on an internal surface of the aircraft component.

2. The anti-icing piccolo tube as claimed in claim 1 , wherein each outlet of the plurality of outlets is configured to expulse the working fluid on a tangent plane of an outer surface of the peripheral layer.

3. The anti-icing piccolo tube as claimed in claim 2 , wherein each outlet is further configured to expulse the working fluid with a direction to directly impinge an area of the internal surface of the aircraft component.

4. The anti-icing piccolo tube as claimed in claim 1 , wherein each outlet further includes an elbow fitting that connects the first inlet and the second inlet to a nozzle with an orifice.

5. The anti-icing piccolo tube as claimed in claim 4 , wherein the orifice is configured to expulse the working fluid on a tangent plane of an outer surface of the peripheral layer.

6. The anti-icing piccolo tube as claimed in claim 4 , wherein the orifice is configured to expulse the working fluid with a direction to directly impinge an area of the internal surface of the aircraft component.

7. The anti-icing piccolo tube as claimed in claim 1 , wherein each self rotating element includes a rotating connector that reduces rotational friction.

8. The anti-icing piccolo tube as claimed in claim 1 , wherein the plurality of self rotating elements includes at least two self rotating elements affixed side by side that rotate together around a common axis at a common angular velocity.

9. The anti-icing piccolo tube as claimed in claim 1 , wherein the plurality of self rotating elements includes at least two self rotating elements affixed side by side that rotate together around a common axis at different angular velocity.

10. The anti-icing piccolo tube as claimed in claim 1 , wherein the plurality of self rotating elements includes at least two self rotating elements separated by an inter-distance to follow a curve of the piccolo tube.

11. An anti-icing system to prevent ice accumulation on a component of an aircraft comprising:
a chamber that heats the component through a working fluid from an engine of the aircraft;
a bleed duct placed behind the chamber that bleeds the working fluid;
a piccolo tube routed inside the chamber that receives the working fluid from the bleed duct; and
a plurality self rotating elements connected to the piccolo tube that dynamically distributes the working fluid into the chamber, each self rotating element of the plurality of self rotating elements including:
a first inlet to receive the working fluid from the piccolo tube;
a second inlet to receive the working fluid from the piccolo tube;
a peripheral layer that connects the first inlet and the second inlet, and
a plurality of outlets placed on the peripheral layer that expulses the working fluid through jets,
wherein the jets rotate each self rotating elements and dynamically impinges the working fluid on an internal surface of the chamber.

12. The anti-icing system as claimed in claim 11 , wherein the chamber further includes a baffle to direct the working fluid on an inner surface of the chamber.

13. The anti-icing system as claimed in claim 12 , wherein the chamber further includes discharge slots that discharge the working fluid from the chamber.

14. The anti-icing system as claimed in claim 11 , wherein each outlet of the plurality of outlets is configured to expulse the working fluid on a tangent plane of an outer surface of the peripheral layer.

15. The anti-icing system as claimed in claim 11 , wherein each outlet is further configured to expulse the working fluid with a direction to directly impinge an area of the internal surface of the component.

16. The anti-icing system as claimed in claim 11 , wherein each outlet further includes an elbow fitting that connects the first inlet and the second inlet to a nozzle with an orifice.

17. The anti-icing system as claimed in claim 16 , wherein the orifice is configured to expulse the working fluid on a tangent plane of an outer surface of the peripheral layer.

18. The anti-icing system as claimed in claim 16 , wherein the orifice is configured to expulse the working fluid with a direction to directly impinge an area of the internal surface of the aircraft component.

19. The anti-icing piccolo tube as claimed in claim 11 , wherein each self rotating element includes a rotating connector that reduces rotational friction.

20. The anti-icing system as claimed in claim 11 , wherein each self rotating element further includes a plurality of mixing plates that mixes the working fluid inside the chamber.

Assignees

• Univ King Fahd Pet & Minerals

Inventors

• Saeed Farooq

Classifications

• B64D15/16

  by mechanical means, e.g. pulsating mats or shoes attached to, or built into, surface · CPC title

• B64D15/04 Primary

  Hot gas application · CPC title

• B64D29/00

  Power-plant nacelles, fairings or cowlings · CPC title

• B64D2033/0233

  comprising de-icing means · CPC title

• B64D33/02

  of combustion air intakes · CPC title