Injector nozzle configuration for swirl anti-icing system

Patent metadata

Field	Value
Publication number	US-2017057643-A1
Application number	US-201514836015-A
Country	US
Kind code	A1
Filing date	Aug 26, 2015
Priority date	Aug 26, 2015
Publication date	Mar 2, 2017
Grant date	—

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

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.

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 , 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 at least partially within an outer perimeter of the nozzles.

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

6 . The system of claim 1 , wherein the one or more nozzles include an irregular shaped outer perimeter.

7 . 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.

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

9 . 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 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.

10 . The system of claim 9 , 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.

11 . The system of claim 9 , 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 at least partially within an outer perimeter of the nozzles.

12 . The system of claim 11 , further comprising:
one or more braces disposed within the at least one nozzle to support the central diffuser element.

13 . The system of claim 9 , wherein the one or more nozzles include an irregular shaped outer perimeter.

14 . The system of claim 9 , 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.

15 . The system of claim 9 , further comprising a turbine, wherein the turbine is the source of the high pressure hot gas.

16 . 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 in fluid contact with the injector and an exit, wherein an outer perimeter of at least one of the one or more nozzles is irregular shaped and surrounds at least a portion of a central diffuser element disposed in a flow path of the gas entering the nozzles.

17 . The system of claim 16 , 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.

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

19 . The system of claim 16 , 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.

20 . The system of claim 15 , 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

• B64D2033/0233

  comprising de-icing means · CPC title

• B64D15/04 Primary

  Hot gas application · CPC title

• B64D33/02

  of combustion air intakes · CPC title

• F02C7/047 Primary

  Heating to prevent icing · CPC title

• B64D27/16

  of jet type · CPC title