Method and apparatus for aircraft anti-icing

Patent metadata

Field	Value
Publication number	US-2020346767-A1
Application number	US-201916399699-A
Country	US
Kind code	A1
Filing date	Apr 30, 2019
Priority date	Apr 30, 2019
Publication date	Nov 5, 2020
Grant date	—

Abstract

An apparatus for aircraft anti-icing includes a nozzle body, a nozzle extending from the nozzle body, an eductor shroud at least partially surrounding the nozzle, the eductor shroud configured to focus a first flow of ambient air towards a first flow of hot gas exiting the first nozzle.

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; and a first eductor shroud at least partially surrounding the first nozzle, the first eductor shroud configured to focus a first flow of ambient air towards a first flow of hot gas exiting the first nozzle.

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 , wherein an exit plane of the first eductor shroud is disposed downstream from an exit plane of the first nozzle.

4 . The apparatus of claim 1 , wherein a cross-sectional area of an inlet aperture of the first eductor shroud is greater than a cross-sectional area of an outlet aperture of the first eductor shroud.

5 . The apparatus of claim 1 , wherein the first eductor shroud is supported by at least one of the nozzle body and the first nozzle.

6 . The apparatus of claim 1 , further comprising a collar extending from the nozzle body, the collar configured to secure the apparatus to a leading edge housing, wherein the first eductor shroud extends from the collar.

7 . The apparatus of claim 1 , wherein a centerline axis of the nozzle body is at least one of:
orthogonal with respect to a centerline axis of the first nozzle; and oriented at a non-orthogonal angle with respect to the centerline axis of the first nozzle.

8 . The apparatus of claim 1 , further comprising a second nozzle extending from the nozzle body, wherein a centerline axis of the second nozzle is oriented at an angle with respect to a centerline axis of the first nozzle.

9 . The apparatus of claim 8 , further comprising a second eductor shroud configured to focus a second flow of ambient air towards a second flow of hot gas exiting the second nozzle.

10 . The apparatus of claim 8 , wherein the first eductor shroud is configured to focus the first flow of ambient air towards a second flow of hot gas exiting the second nozzle, and the first eductor shroud at least partially surrounds the second nozzle.

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

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

13 . 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; and an outlet nozzle coupled to the conduit, the outlet nozzle comprising:
a nozzle body;
a first nozzle extending from the nozzle body; and
a first eductor shroud at least partially surrounding the first nozzle, the first eductor shroud configured to focus a first flow of ambient air towards a first flow of hot gas exiting the first nozzle.

14 . The aircraft anti-icing system of claim 13 , 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.

15 . The aircraft anti-icing system of claim 13 , wherein an exit plane of the first eductor shroud is disposed downstream from an exit plane of the first nozzle.

16 . The aircraft anti-icing system of claim 15 , wherein a cross-sectional area of an inlet aperture of the first eductor shroud is greater than a cross-sectional area of an outlet aperture of the first eductor shroud.

17 . The aircraft anti-icing system of claim 15 , further comprising:
a second nozzle extending from the nozzle body; and a second eductor shroud configured to focus a second flow of ambient air towards a second flow of hot gas exiting the second nozzle.

18 . The aircraft anti-icing system of claim 15 , further comprising a second nozzle extending from the nozzle body, wherein the first eductor shroud is configured to focus the first flow of ambient air towards a second flow of hot gas exiting the second nozzle, and the first eductor shroud at least partially surrounds the second nozzle.

19 . A method for preventing formation of ice, the method comprising:
receiving, at an outlet nozzle, a hot gas from a compression stage of an engine; and conducting, via the outlet nozzle, the hot gas received from the compression stage to an internal volume of a leading edge housing, wherein the outlet nozzle conducts the hot gas based on a flow pattern, wherein the flow pattern is determined based, at least in part, on a geometry of the outlet nozzle that has a nozzle body, a first nozzle extending from the nozzle body, and a first eductor shroud at least partially surrounding the first nozzle, the first eductor shroud configured to focus a first flow of ambient air towards a first flow of hot gas exiting the first nozzle.

20 . The method of claim 19 , further comprising exhausting the hot gas from the leading edge housing.

Assignees

• Rohr Inc

Inventors

• Pujar Vijay V
• Kestler Steven M
• Lohman Sarah
• Francisco Jay
• Harasha Jeffrey

Classifications

• F02C7/047

  Heating to prevent icing · CPC title

• B64D15/04 Primary

  Hot gas application · CPC title

• B64D2033/0233

  comprising de-icing means · CPC title

• B64D29/00

  Power-plant nacelles, fairings or cowlings · CPC title

• B64D2033/0286

  for turbofan engines · CPC title