Shielded swirl gas turbine engine inlet anti-icing system

Patent metadata

Field	Value
Publication number	US-12410750-B1
Application number	US-202418958264-A
Country	US
Kind code	B1
Filing date	Nov 25, 2024
Priority date	Nov 25, 2024
Publication date	Sep 9, 2025
Grant date	Sep 9, 2025

Abstract

A gas turbine engine inlet anti-ice system includes a nacelle having an inlet lip, an anti-ice air supply duct, and a flow deflector. The inlet lip has an annular anti-icing chamber formed therein that is defined by an inner surface of the inlet lip and an aft wall that has an aft wall opening formed therein. The anti-ice air supply duct is configured to direct a flow of pressurized air into the aft wall opening. The flow deflector is coupled to the aft wall and extends over the aft wall opening. The flow deflector has an inner surface, an outer surface, a closed end, and an open end. The flow deflector and aft wall define a flow channel that extends between the closed end and the open end and in a direction that is tangential to the aft wall opening.

First claim

What is claimed is:

1. A gas turbine engine inlet anti-ice system, comprising:
a nacelle having an inlet lip, the inlet lip having an annular anti-icing chamber formed therein, the annular anti-icing chamber defined by an inner surface of the inlet lip and an aft wall coupled to the inner surface, the aft wall having an aft wall opening formed therein;
an anti-ice air supply duct coupled to the aft wall opening, the anti-ice air supply duct configured to receive a flow of pressurized air and direct the flow of pressurized air into the aft wall opening;
a flow deflector coupled to the aft wall and extending over the aft wall opening, the flow deflector having an inner surface, an outer surface, a closed end, and an open end, at least a portion of the inner surface spaced apart from the aft wall opening and, together with the aft wall, defining a flow channel that extends between the closed end and the open end and in a direction that is tangential to the aft wall opening;
an annular shield disposed within the annular anti-icing chamber and at least partially surrounding the flow deflector, the annular shield having a first end and a second end, the first end spaced a first predetermined distance from the aft wall, the second end spaced a second predetermined distance from the aft wall; and
a plurality of flexible brackets, each flexible bracket spaced radially apart from two other flexible brackets and coupled between the first end of the annular shield and the aft wall,
wherein:
the second predetermined distance is greater than the first predetermined distance,
the annular shield divides the annular anti-icing chamber into a first chamber portion and a second chamber portion, and

the first chamber portion and the second chamber portion are fluidly coupled together by a passage formed between the second end and the inner surface of the inlet lip.

2. The system of claim 1 , wherein:
the annular shield further includes an inner surface and an outer surface,
the first chamber portion is defined between at least the inner surface and the aft wall; and
the second chamber portion is defined between the outer surface and the inner surface of the inlet lip.

3. The system of claim 1 , wherein:
the first end of the annular shield being spaced the first predetermined distance from the aft wall defines a gap, having the first predetermined distance, between the annular shield and the aft wall at positions where the flexible brackets are not coupled to the annular shield and the aft wall.

4. The system of claim 3 , wherein the first chamber portion and the second chamber portion are also fluidly coupled together via the gap.

5. The system of claim 1 , further comprising:
a metering orifice disposed within the anti-ice air supply duct and configured to meter the flow of pressurized air directed into the aft wall opening.

6. The system of claim 1 , further comprising:
a flow deflector coupled to the aft wall and extending over the aft wall opening, the flow deflector disposed within the first chamber portion and having an inner surface, an outer surface, a closed end, and an open end, at least a portion of the inner surface spaced apart from the aft wall opening and, together with the aft wall, defining a flow channel that extends between the closed end and the open end and in a direction that is tangential to the aft wall opening.

7. A gas turbine engine system, comprising:
a gas turbine engine;
a nacelle housing the gas turbine engine and having an inlet lip, the inlet lip having an annular anti-icing chamber formed therein, the annular anti-icing chamber defined by an inner surface of the inlet lip and an aft wall coupled to the inner surface, the aft wall having an aft wall opening formed therein;
an anti-ice air supply duct coupled to the aft wall opening, the anti-ice air supply duct coupled to receive a flow of pressurized air from the gas turbine engine and direct the flow of pressurized air into the aft wall opening;
a flow deflector coupled to the aft wall and extending over the aft wall opening, the flow deflector having an inner surface, an outer surface, a closed end, and an open end, at least a portion of the inner surface spaced apart from the aft wall opening and, together with the aft wall, defining a flow channel that extends between the closed end and the open end and in a direction that is tangential to the aft wall opening;
an annular shield disposed within the annular anti-icing chamber and at least partially surrounding the flow deflector, the annular shield having a first end and a second end, the first end spaced a first predetermined distance from the aft wall, the second end spaced a second predetermined distance from the aft wall; and
a plurality of flexible brackets, each flexible bracket spaced radially apart from two other flexible brackets and coupled between the first end of the annular shield and the aft wall,
wherein:
the second predetermined distance is greater than the first predetermined distance,
the annular shield divides the annular anti-icing chamber into a first chamber portion and a second chamber portion, and

the first chamber portion and the second chamber portion are fluidly coupled together by a passage formed between the second end and the inner surface of the inlet lip.

8. The system of claim 7 , wherein:
the annular shield further includes an inner surface and an outer surface,
the first chamber portion is defined between at least the inner surface and the aft wall; and
the second chamber portion is defined between the outer surface and the inner surface of the inlet lip.

9. The system of claim 7 , wherein:
the first end of the annular shield being spaced the first predetermined distance from the aft wall defines a gap, having the first predetermined distance, between the annular shield and the aft wall at positions where the flexible brackets are not coupled to the annular shield and the aft wall.

10. The system of claim 9 , wherein the first chamber portion and the second chamber portion are also fluidly coupled together via the gap.

11. The system of claim 7 , further comprising:
a metering orifice disposed within the anti-ice air supply duct and configured to meter the flow of pressurized air directed into the aft wall opening.

12. A gas turbine engine inlet anti-ice system, comprising:
a nacelle having an inlet lip, the inlet lip having an annular anti-icing chamber formed therein, the annular anti-icing chamber defined by an inner surface of the inlet lip and an aft wall coupled to the inner surface, the aft wall having an aft wall opening formed therein;
an anti-ice air supply duct coupled to the aft wall opening, the anti-ice air supply duct configured to receive a flow of pressurized air and direct the flow of pressurized air into the aft wall opening; and
an annular shield disposed within the annular anti-icing chamber and having a first end and a second end, the first end spaced a first predetermined distance from the aft wall, the second end spaced a second predetermined distance from the aft wall; and
a plurality of flexible brackets, each flexible bracket spaced radially apart from two other flexible brackets and coupled between the first end of the annular shield and the aft wall,
wherein:
the second predetermined distance is greater than the first predetermined distance,
the annular shield divides the annular anti-icing chamber into a first chamber portion and a second chamber portion, and
the first chamber portion and the second chamber portion are fluidly coupled together by a passage formed between the second end and the inner surface of the inlet lip.

Assignees

• Honeywell Int Inc

Inventors

• Anderson Morris G
• Dunn Matthew

Classifications

• B64D33/02

  of combustion air intakes · CPC title

• B64D15/04

  Hot gas application · CPC title

• B64D2033/0233

  comprising de-icing means · CPC title

• F02C7/047 Primary

  Heating to prevent icing · CPC title