Aircraft anti-icing system

Patent metadata

Field	Value
Publication number	US-11708166-B2
Application number	US-202117196803-A
Country	US
Kind code	B2
Filing date	Mar 9, 2021
Priority date	Apr 7, 2020
Publication date	Jul 25, 2023
Grant date	Jul 25, 2023

Abstract

An aircraft anti-icing system is disclosed. A tube having a plurality of outlet ports is disposed within an interior of an outer housing in spaced relation to a closed end of this outer housing. The exterior of the outer housing includes a leading edge at its closed end. The tube is anchored relative to the outer housing by one or more brackets that extend from the tube to the outer housing. An open end of the outer housing may be closed by an aft wall that encloses the tube within an interior compartment of the outer housing.

First claim

What is claimed is:

1. An aircraft anti-icing system comprising:
an outer housing comprising a leading edge on a closed end of said outer housing, wherein said outer housing further comprises a first wall extending from a first edge of said closed end of said outer housing and a second wall extending from a second edge of said closed end of said outer housing, wherein said first and second walls are disposed in opposing, spaced relation to one another;
an aft wall attached to said outer housing in spaced relation to said closed end;
an interior compartment collectively defined by said outer housing and said aft wall;
a bracket attached to and extending from said outer housing into said interior compartment; and
a tube comprising an outer perimeter and a plurality of outlet ports extending through the outer perimeter of the tube, wherein said tube is engaged by said bracket within said interior compartment at a location that is spaced from said closed end of said outer housing, and wherein said bracket is attached to only one of said first wall and said second wall at a location that is between said aft wall and said tube in a dimension that said aft wall and said closed end of said outer housing are spaced from one another.

2. The aircraft anti-icing system of claim 1 , wherein said outer housing is selected from the group consisting of an aircraft wing and an aircraft engine nacelle.

3. The aircraft anti-icing system of claim 1 , wherein said leading edge is on an exterior surface of said closed end of said outer housing and is a leading surface of said outer housing when directed through air in an installed configuration.

4. The aircraft anti-icing system of claim 1 , wherein said closed end of said outer housing is convex relative to an exterior of said outer housing.

5. The aircraft anti-icing system of claim 4 , wherein said closed end of said outer housing comprises a concave interior surface, and wherein said tube is disposed in spaced relation to said concave interior surface at said closed end.

6. The aircraft anti-icing system of claim 1 , wherein said plurality of outlet ports each project at least generally in a direction of said closed end of said outer housing.

7. The aircraft anti-icing system of claim 1 , wherein said bracket cantilevers from said outer housing.

8. The aircraft anti-icing system of claim 1 , wherein said bracket extends from said outer housing both inwardly and in a direction of said closed end of said outer housing for engagement with said tube.

9. The aircraft anti-icing system of claim 1 , wherein each exposed outlet port of said plurality of outlet ports fluidly interfaces with a single common space that both extends from each said exposed outlet port to said closed end of said outer housing and extends between each adjacent pair of said exposed outlet ports.

10. The aircraft anti-icing system of claim 1 , wherein a first length segment of said tube extends from said bracket, wherein multiple outlet ports of said plurality of outlet ports are incorporated by said first length segment of said tube, wherein an open space is disposed about an outer perimeter of said first length segment of said tube and said open space also extends from said first length segment of said tube to said closed end of said outer housing.

11. An aircraft comprising a fuselage, a first wing, a first engine, a second wing, a second engine, and the aircraft anti-icing system of claim 1 .

12. The aircraft of claim 11 , wherein said first engine comprises a nacelle, and wherein said outer housing comprises said nacelle.

13. The aircraft of claim 11 , wherein said outer housing comprises said first wing.

Assignees

• Rohr Inc

Inventors

• Shetzer Daniel J

Classifications

• B64D15/04 Primary

  Hot gas application · CPC title

• B64D29/00

  Power-plant nacelles, fairings or cowlings · CPC title