Aerodynamic swept vanes for fuel injectors

Patent metadata

Field	Value
Publication number	US-9429074-B2
Application number	US-50064909-A
Country	US
Kind code	B2
Filing date	Jul 10, 2009
Priority date	Jul 10, 2009
Publication date	Aug 30, 2016
Grant date	Aug 30, 2016

Abstract

A fuel nozzle for a gas turbine engine includes a nozzle body having a longitudinal axis. An elongated annular air passage is defined within the nozzle body. A plurality of circumferentially spaced apart axially extending swirl vanes is disposed within the annular air passage. Each swirl vane has an axially swept cross-sectional profile along the radial extent thereof.

First claim

What is claimed is:

1. A fuel nozzle for a gas turbine engine comprising:
a) a nozzle body having a longitudinal axis;
b) an annular air passage defined within the nozzle body; and
c) a plurality of circumferentially spaced apart axially extending aerodynamic swirl vanes disposed within the annular air passage, each of the swirl vane having an axially swept cross-sectional profile along the radial extent thereof,
wherein the cross-sectional profile of each of the swirl vane has proportions that vary along the radial extent of the swirl vane.

2. A fuel nozzle as recited in claim 1 , wherein each of the swirl vane has a trailing edge on a downstream portion thereof, a leading edge on an upstream portion thereof, wherein the leading edge and the trailing each have a tip portion on a radially outer extent thereof, and a base portion on a radially inner extent thereof, and wherein at least one of the leading edge and the trailing edge is axially swept.

3. A fuel nozzle as recited in claim 2 , wherein at least one of the leading edge and the trailing edge is swept with the tip portion thereof axially downstream relative to the base portion thereof.

4. A fuel nozzle as recited in claim 2 , wherein at least one of the leading edge and the trailing edge is swept with the tip portion thereof axially upstream relative to the base portion thereof.

5. A fuel nozzle as recited in claim 2 , wherein the trailing edge and the leading edge of each of the swirl vane are swept in opposite relative directions axially.

6. A fuel nozzle as recited in claim 2 , wherein the trailing edge and the leading edge of each of the swirl vane are swept in a common relative direction axially.

7. A fuel nozzle as recited in claim 2 , wherein the at least one swept edge of each of the swirl vane is straight.

8. A fuel nozzle as recited in claim 2 , wherein the at least one swept edge of each of the swirl vane is curved.

9. A fuel nozzle as recited in claim 2 , wherein the leading edge is substantially perpendicular to the longitudinal axis, and wherein the trailing edge is swept with the tip portion thereof axially downstream relative to the base portion thereof.

10. A fuel nozzle as recited in claim 2 , wherein the trailing edge is parallel to the leading edge.

11. A fuel nozzle as recited in claim 1 , wherein the cross-sectional profile of each of the swirl vane has a variable thickness along an axial length thereof.

12. A fuel nozzle as recited in claim 1 , wherein the cross-sectional profile of each of the swirl vane is airfoil shaped and has a chord that varies in length along the radial extent of the swirl vane.

Assignees

• Williams Brandon Phillip
• Thompson Kevin Eugene
• Rolls Royce Plc

Inventors

• Williams Brandon Phillip
• Thompson Kevin Eugene

Classifications

• F23R3/14

  by using swirl vanes · CPC title

• F05D2240/128

  Nozzles · CPC title

• F23C7/004

  using vanes · CPC title

• F05D2250/70

  Shape · CPC title

• F02C7/22 Primary

  Fuel supply systems · CPC title