Fuel nozzle having aerodynamically shaped helical turning vanes

Patent metadata

Field	Value
Publication number	US-10295187-B2
Application number	US-201615332096-A
Country	US
Kind code	B2
Filing date	Oct 24, 2016
Priority date	Feb 18, 2009
Publication date	May 21, 2019
Grant date	May 21, 2019

Abstract

A fuel nozzle for a gas turbine engine is disclosed which includes a nozzle body having a longitudinal axis, an elongated annular air passage defined within the nozzle body, and a plurality of circumferentially spaced apart axially extending swirl vanes disposed within the annular air passage, wherein each swirl vane has multiple joined leads and a variable thickness along the axial extent thereof.

First claim

What is claimed is:

1. An air swirler for a fuel nozzle comprising:
a) a central hub defining a longitudinal axis;
b) a plurality of circumferentially spaced apart axially extending helically pitched swirl vanes extending radially outwardly from the hub, each of the swirl vanes having multiple joined helical leads and a variable thickness along the axial extent thereof.

2. An air swirler as recited in claim 1 , wherein each of the swirl vanes includes an upstream vane section having a leading edge surface and a downstream vane section having a trailing edge surface.

3. An air swirler as recited in claim 2 , wherein the leading edge surface of the upstream vane section of each of the swirl vanes is disposed at an angle relative to the longitudinal axis of the central hub, defining an initial pitch along the axial extent of the upstream vane section.

4. An air swirler as recited in claim 2 , wherein the downstream vane section has a continuously varying pitch along the axial extent thereof.

5. A fuel nozzle as recited in claim 2 , wherein the downstream vane section has a constant pitch along an axial extent thereof.

6. An air swirler as recited in claim 2 , wherein each of the swirl vanes includes a transitional vane section that blends the upstream vane section into the downstream vane section.

7. An air swirler as recited in claim 6 , wherein each of the swirl vanes has a maximum normal thickness associated with the transitional vane section.

8. An air swirler as recited in claim 7 , wherein the normal thickness varies from the transitional vane section to the trailing edge surface of each of the swirl vanes.

9. An air swirler as recited in claim 7 , wherein the normal thickness remains constant for at a least an axial segment from the transitional vane section to the trailing edge surface of each of the swirl vanes.

10. An air swirler as recited in claim 7 , wherein the normal thickness varies from the transitional vane section to the leading edge surface of each of the swirl vanes.

Assignees

• Rolls Royce Plc

Inventors

• Williams Brandon P
• Thompson Kevin E
• Fogarty Robert R

Classifications

• F23D11/107

  at least one of both being subjected to a swirling motion · CPC title

• F23R3/28

  characterised by the fuel supply (burners F23D) · CPC title

• F23R3/14 Primary

  by using swirl vanes · CPC title