Fuel swirler with anti-rotation features

Patent metadata

Field	Value
Publication number	US-10253976-B2
Application number	US-201715495043-A
Country	US
Kind code	B2
Filing date	Apr 24, 2017
Priority date	Apr 24, 2017
Publication date	Apr 9, 2019
Grant date	Apr 9, 2019

Abstract

A fuel swirler with anti-rotation features is provided. A swirler assembly may comprise a swirler, a guide plate, and a retaining ring. The swirler, the guide plate, and/or the retaining ring may comprise recessions configured to receive a retaining element. The retaining element may be configured to interface with the recessions to create an interference in the swirler assembly. The interference may at least partially resist rotation of the guide plate with respect to the swirler.

First claim

What is claimed is:

1. A swirler assembly defining a longitudinal axis, the swirler assembly comprising:
a swirler having a forward swirler surface, the forward swirler surface defining a guide plate recession and an annular wall portion circumferentially surrounding the guide plate recession, and a first axial void being defined axially, with respect to the longitudinal axis, into the guide plate recession, the swirler further including a swirler opening, the guide plate recession circumferentially surrounding the swirler opening;
a guide plate coupled within the guide plate recession of the swirler and circumferentially surrounded by the annular wall portion of the forward swirler surface;
a retaining ring coupled to the guide plate and comprising a second axial void defined axially, with respect to the longitudinal axis, through a portion of the retaining ring; and
a retaining element defining a first axial protrusion extending forward from a forward guide surface of the guide plate and a second axial protrusion extending aft from an aft guide surface of the guide plate,
wherein the first axial protrusion is coupled within the second axial void,
wherein the second axial protrusion is coupled within the first axial void, and
wherein the retaining element is configured to at least partially resist rotation of the guide plate with respect to the swirler.

2. The swirler assembly of claim 1 , wherein at least one of the guide plate, the retaining ring, or the swirler are formed using investment casting.

3. The swirler assembly of claim 1 , wherein at least one of the first axial protrusion or the second axial protrusion of the retaining element comprises an angular shape, a circular shape, or a pin shape.

4. The swirler assembly of claim 1 , wherein the guide plate comprises an aft sealing protrusion extending axially, with respect to the longitudinal axis, from the aft guide surface, wherein the aft sealing protrusion is configured to provide radial sealing against a radially inner swirler surface of the swirler.

5. The swirler assembly of claim 1 , wherein the guide plate comprises a forward sealing protrusion extending axially, with respect to the longitudinal axis, from the forward guide surface, wherein the forward sealing protrusion is configured to provide radial sealing against a radially inner surface of the retaining ring.

6. A gas turbine engine comprising:
a combustor;
a fuel nozzle configured to deliver fuel into the combustor; and
a swirler assembly defining a longitudinal axis and coupled around a distal end of the fuel nozzle, the swirler assembly comprising:
a swirler having a forward swirler surface, the forward swirler surface defining a guide plate recession and an annular wall portion circumferentially surrounding the guide plate recession, and a first axial void being defined axially, with respect to the longitudinal axis, into the guide plate recession, the swirler further including a swirler opening, the guide plate recession circumferentially surrounding the swirler opening;
a guide plate coupled within the guide plate recession of the swirler and circumferentially surrounded by the annular wall portion of the forward swirler surface;
a retaining ring coupled to the guide plate and comprising a second axial void defined axially, with respect to the longitudinal access, through a portion of the retaining ring; and
a retaining element defining a first axial protrusion extending forward from a forward guide surface of the guide plate and a second axial protrusion extending aft from an aft guide surface of the guide plate,
wherein the first axial protrusion is coupled within the second axial void,
wherein the second axial protrusion is coupled within the first axial void, and
wherein the retaining element is configured to at least partially resist rotation of the guide plate with respect to the swirler.

7. The gas turbine engine of claim 6 , wherein at least one of the guide plate, the retaining ring, or the swirler are formed using investment casting.

8. The gas turbine engine of claim 6 , wherein at least one of the first axial protrusion or the second axial protrusion of the retaining element comprises an angular shape, a circular shape, or a pin shape.

9. The gas turbine engine of claim 6 , wherein the guide plate comprises an aft sealing protrusion extending axially, with respect to the longitudinal axis, from the aft guide surface, wherein the aft sealing protrusion is configured to provide radial sealing against a radially inner swirler surface of the swirler.

10. The gas turbine engine of claim 6 , wherein the guide plate comprises a forward sealing protrusion extending axially, with respect to the longitudinal axis, from the forward guide surface, wherein the forward sealing protrusion is configured to provide radial sealing against a radially inner surface of the retaining ring.

Assignees

• United Technologies Corp

Inventors

• Gunderson Peter E

Classifications

• F23R3/14

  by using swirl vanes · CPC title

• F23R2900/00017

  Assembling combustion chamber liners or subparts · CPC title

• F23R3/12

  inducing a vortex · CPC title

• F05D2260/30

  Retaining components in desired mutual position · CPC title

• F23D2900/14021

  Premixing burners with swirling or vortices creating means for fuel or air · CPC title