Method and apparatus for aircraft anti-icing

Patent metadata

Field	Value
Publication number	US-11465758-B2
Application number	US-201916399639-A
Country	US
Kind code	B2
Filing date	Apr 30, 2019
Priority date	Apr 30, 2019
Publication date	Oct 11, 2022
Grant date	Oct 11, 2022

Abstract

An apparatus for aircraft anti-icing includes a nozzle body, at least one nozzle extending from the nozzle body, and at least one vane disposed in at least one of the nozzle(s), the at least one vane configured to impart rotational movement of a hot gas moving through the nozzle(s).

First claim

What is claimed is:

1. An apparatus for aircraft anti-icing, the apparatus comprising:
a nozzle body;
a first nozzle extending from the nozzle body, wherein the first nozzle is configured to be fluidly connected with only a single fluid source comprising a source of hot gas such that a gas exiting the first nozzle is comprised entirely of a hot gas received from the single fluid source; and
a first vane disposed in the first nozzle, the first vane configured to impart rotational movement of the hot gas moving through the first nozzle, wherein the first vane comprises helical geometry.

2. The apparatus of claim 1 , wherein the first nozzle comprises an annular flange extending from the nozzle body.

3. The apparatus of claim 1 , further comprising a second vane disposed in the first nozzle, the second vane configured to impart rotational movement of the hot gas moving through the first nozzle.

4. The apparatus of claim 1 , further comprising a first beam disposed at an exit plane of the first nozzle, the first beam bifurcating the first nozzle, and the first vane extending from the first beam.

5. The apparatus of claim 4 , further comprising a second beam disposed at an entrance plane of the first nozzle, the second beam bifurcating the first nozzle, and the first vane extending from the second beam.

6. The apparatus of claim 1 , wherein the first nozzle is tapered.

7. The apparatus of claim 1 , wherein a centerline axis of the nozzle body is orthogonal with respect to a centerline axis of the first nozzle.

8. The apparatus of claim 1 , further comprising a second nozzle extending from the nozzle body.

9. The apparatus of claim 1 , wherein the nozzle body is configured to receive the flow of hot gas from a compression stage of an engine.

10. The apparatus of claim 1 , wherein the apparatus is configured to provide at least a portion of the flow of hot gas to a leading edge housing of an aircraft component.

11. The apparatus of claim 1 , wherein the first vane divides a first flow path through the first nozzle from a second flow path through the first nozzle.

12. The apparatus of claim 1 , wherein the first vane is disposed internal to the first nozzle, and the first vane is configured to impart rotational movement of a hot gas ejected from the first nozzle.

13. The apparatus of claim 1 , wherein the first vane is disposed in a flow path of the hot gas.

14. An aircraft anti-icing system comprising:
a source of a hot gas;
a housing;
a conduit configured to carry the hot gas from the source to the housing; an outlet nozzle coupled to the conduit, the outlet nozzle comprising:
a nozzle body;
a first nozzle extending from the nozzle body, wherein the first nozzle is fluidly connected with only a single fluid source comprising the source of the hot gas such that a gas exiting the first nozzle is comprised entirely of a hot gas received from the single fluid source; and
a first vane disposed in the first nozzle, the first vane configured to impart rotational movement of the hot gas moving through the first nozzle, wherein the first vane comprises helical geometry.

15. The aircraft anti-icing system of claim 14 , further comprising a port for exhausting air from the housing, wherein the outlet nozzle is configured to increase a speed of the hot gas exiting the first nozzle, and the hot gas mixes with air from the housing after the hot gas exits the first nozzle.

16. The aircraft anti-icing system of claim 14 , wherein the first nozzle comprises an annular flange extending from the nozzle body.

17. The aircraft anti-icing system of claim 16 , wherein the annular flange is tapered.

18. The aircraft anti-icing system of claim 16 , further comprising:
a first beam disposed at an exit plane of the first nozzle, the first beam bifurcating the first nozzle, and the first vane extending from the first beam; and
a second beam disposed at an inlet plane of the first nozzle, the second beam bifurcating the first nozzle, and the first vane extending from the second beam.

19. The aircraft anti-icing system of claim 16 , wherein the first vane comprises at least one of a clockwise helix geometry or a counter clockwise helix geometry.

Assignees

• Rohr Inc

Inventors

• Lohman Sarah
• Kestler Steven M
• Muñoz Manuel
• Francisco Jay
• Pujar Vijay V

Classifications

• B64D2033/0233

  comprising de-icing means · CPC title

• B64D15/04 Primary

  Hot gas application · CPC title

• F15D1/08

  of jets leaving an orifice · CPC title

• B64D33/02

  of combustion air intakes · CPC title

• F02C7/047

  Heating to prevent icing · CPC title