Injector nozzle configuration for swirl anti-icing system

Patent metadata

Field	Value
Publication number	US-10393020-B2
Application number	US-201514836035-A
Country	US
Kind code	B2
Filing date	Aug 26, 2015
Priority date	Aug 26, 2015
Publication date	Aug 27, 2019
Grant date	Aug 27, 2019

Abstract

An anti-icing system for annular gas turbine engine inlet housings includes a substantially closed annular housing at a leading edge of the gas turbine engine inlet housing, the annular housing containing a quantity of air and a conduit extending from a source of high-pressure hot bleed air to the annular housing. The system also includes 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. The system may include one or both of an airfoil on an upstream side of the injector and an air direction element disposed one the injector that causes the quantity of air to be directed toward an outlet of the one or more nozzles.

First claim

The invention claimed is:

1. An anti-icing system for annular gas turbine engine housings comprising:
a substantially closed annular housing at a leading edge of the gas turbine engine inlet housing, the substantially closed annular housing containing a quantity of air;
a conduit extending from a source of high-pressure hot bleed air to the substantially closed annular housing;
an injector connected to an end of the conduit and extending into the substantially closed annular housing;
a first air directional element extending outwardly from a a distal end of the injector in a first direction that causes the quantity of high-pressure hot bleed air to be directed toward an outlet of the one or more nozzles, the first air directional element including at least two deflector vanes; and
one or more nozzles extending outwardly from the injector in a second direction that the quantity of air circulates in the annular housing, the second direction being different than the first direction;
wherein the first air directional element is outside of the one or more nozzles.

2. The system of claim 1 , wherein the injector includes an airfoil on an upstream side.

3. The system of claim 1 , further comprising a gas turbine engine compressor, wherein the gas turbine engine compressor is the source of the high-pressure hot bleed air.

4. 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 a nozzle length as the one of the one or more nozzles extends away from the injector.

5. The system of claim 4 , wherein the one of the one or more nozzles curves at a similar rate as the annular housing.

6. An anti-icing system for annular gas turbine engine inlet housings comprising:
a substantially closed annular housing at a leading edge of the gas turbine engine inlet housing, the substantially closed annular housing containing a quantity of air;
a conduit extending from a source of high-pressure hot bleed air to the substantially colosed annular housing;
an injector connected to the end of the conduit and extending into the substantially closed annular housing;
one or more nozzles extending outwardly in a first direction from the injector in a direction that the quantity of air circulates in the annular housing; and
a first air directional element extending outwardly from either a top or a bottom of the injector in a second direction that causes the quantity of air to be directed toward an outlet of the one or more nozzles, the first air directional element including at least two deflector vanes, the second direction being different than the first direction;
wherein the first air directional element is outside of the one or more nozzles.

7. The system of claim 6 , wherein the injector includes an airfoil on an upstream side.

8. The system of claim 6 , further comprising a gas turbine engine compressor, wherein the gas turbine engine compressor is the source of the high-pressure hot bleed air.

9. The system of claim 6 , further comprising:
a second air direction element disposed an a distal end of the injector that causes the quantity of air to be directed toward an outlet of the one or more nozzles.

10. The system of claim 9 , wherein the second air direction element imparts a side turning deflection angle from between 1 to 8 degrees.

11. The system of claim 9 , wherein the first air direction element imparts a downward deflection angle from between 1 to 15 degrees.

Assignees

• Rohr Inc

Inventors

• Frank Joel H
• Ribarov Lubomir A

Classifications

• F01D25/02

  De-icing means for engines having icing phenomena · CPC title

• F02C7/047 Primary

  Heating to prevent icing · CPC title

• B64D33/02

  of combustion air intakes · CPC title

• F05D2260/2212

  by creating turbulence · CPC title

• F02C6/08

  the gas being bled from the gas-turbine compressor · CPC title