Injector nozzle configuration for swirl anti-icing system

Patent metadata

Field	Value
Publication number	US-10723464-B2
Application number	US-201514836015-A
Country	US
Kind code	B2
Filing date	Aug 26, 2015
Priority date	Aug 26, 2015
Publication date	Jul 28, 2020
Grant date	Jul 28, 2020

Abstract

An anti-icing system for annular turbofan engine housings what include a substantially closed annular housing at a leading edge of the turbofan engine housing, the annular housing containing a quantity of air and a conduit extending from a source of high pressure hot gas to the annular housing. The system also includes an injector connected to the end of the conduit and extending into the annular housing; one or more nozzles extending outwardly from the injector in a direction that the quantity of air circulates in the annular housing while the turbofan engine is operating. The nozzles have an entrance in fluid contact with the injector and an exit, wherein a cross-sectional area of the entrance is less than a cross-sectional area of the exit such that gas leaving the nozzles is travelling slower than gas entering the nozzles.

First claim

The invention claimed is:

1. An anti-icing system for annular turbofan engine housings comprising:
a substantially closed annular housing at a leading edge of the turbofan engine housing, the annular housing containing a quantity of air;
a conduit extending from a source of high pressure hot gas to the annular housing;
an injector connected to the end of the conduit and extending into the annular housing; and
one or more nozzles extending outwardly from the injector in a direction that the quantity of air circulates in the annular housing while the turbofan engine is operating, the nozzles having an entrance in fluid contact with the injector and an exit, wherein a cross-sectional area of the entrance is less than a cross-sectional area of the exit such that gas leaving the nozzles is travelling slower than gas entering the nozzles
wherein at least one of the one or more nozzles includes a central diffuser element disposed in a flow path of the gas entering the nozzles and supported by at least two braces that center the central diffuser element within an outer periphery of the at least one nozzle.

2. The system of claim 1 , further comprising a turbofan jet engine compressor, wherein the turbofan jet engine compressor is the source of the high pressure hot gas.

3. The system of claim 1 , wherein the one or more nozzles includes at least three nozzles.

4. The system of claim 1 , further comprising:
one or more braces disposed within the at least one nozzle to support the central diffuser element.

5. The system of claim 1 , wherein the one or more nozzles include a non-uniform shaped outer perimeter.

6. The system of claim 1 , wherein one of the one or more nozzles has a length, L, and wherein the one of the one or more nozzles curves along its length as it extends away from the injector.

7. The system of claim 6 , wherein the one of the one or more nozzles curves at a similar rate as the annular housing.

8. An anti-icing system for annular turbofan engine housings comprising:
a substantially closed annular housing at a leading edge of the turbofan engine housing, the annular housing containing a quantity of air;
a conduit extending from a source of high pressure hot gas to the annular housing;
an injector connected to the end of the conduit and extending into the annular housing; and
one or more nozzles extending outwardly from the injector in a direction that the quantity of air circulates in the annular housing while the turbofan engine is operating, the nozzles having an entrance end in fluid contact with the injector and an exit end, wherein one of the one or more nozzles has a length, L, between the entrance end and the exit end and wherein the one of the one or more nozzles curves along its length as it extends away from the injector;
wherein at least one of the one or more nozzles includes a central diffuser element disposed in a flow path of the gas entering the nozzles that divides the flow path of the gas and is supported by braces within an interior of the nozzles.

9. The system of claim 8 , wherein the annular housing and the nozzle each have a radius of curvature, and wherein the radius of curvature of the annular housing and the radius of curvature of the one of the one or more nozzles have a same center point.

10. The system of claim 8 , further comprising:
one or more braces disposed within the at least one nozzle to support the central diffuser element.

11. The system of claim 8 , wherein the one or more nozzles include a non-uniform outer perimeter.

12. The system of claim 8 , wherein a cross-sectional area of the entrance is less than a cross-sectional area of the exit such that gas leaving the nozzles is travelling slower than gas entering the nozzles.

13. The system of claim 8 , further comprising a turbine, wherein the turbine is the source of the high pressure hot gas.

14. An anti-icing system for annular turbofan engine housings comprising:
a substantially closed annular housing at a leading edge of the turbofan engine housing, the annular housing containing a quantity of air and a conduit extending from a source of high pressure hot gas to the annular housing, the system comprising:
an injector connected to the end of the conduit and extending into the annular housing; and
one or more nozzles extending outwardly from the injector in a direction that the quantity of air circulates in the annular housing while the turbofan engine is operating, the nozzles having an entrance end in fluid contact with the injector and an exit end, wherein the nozzle has a length L between the entrance end and the exit end, wherein the one or more nozzles surrounds at least a portion of a central diffuser element disposed in a flow path of the gas entering the nozzles and in supported by braces within the nozzles.

15. The system of claim 14 , wherein one of the one or more nozzles has a length, L, and wherein the one of the one or more nozzles curves along its length as it extends away from the injector.

16. The system of claim 14 , further comprising:
one or more braces disposed within the at least one nozzle to support the central diffuser element.

17. The system of claim 14 , wherein a cross-sectional area of the entrance is less than a cross-sectional area of the exit such that gas leaving the nozzles is travelling slower than gas entering the nozzles.

18. The system of claim 14 , wherein the central diffuser element has a cross-sectional area and wherein a ratio of the cross sectional of the central diffuser element to a cross-sectional area of the entrance is between 0.25 and 0.75.

Assignees

• Rohr Inc

Inventors

• Frank Joel H
• Ribarov Lubomir A

Classifications

• F02C7/047 Primary

  Heating to prevent icing · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• B64D33/02

  of combustion air intakes · CPC title

• B64D2033/0233

  comprising de-icing means · CPC title

• B64D15/04 Primary

  Hot gas application · CPC title