Fuel pre-mixer with planar and swirler vanes

Patent metadata

Field	Value
Publication number	US-9395084-B2
Application number	US-201213490061-A
Country	US
Kind code	B2
Filing date	Jun 6, 2012
Priority date	Jun 6, 2012
Publication date	Jul 19, 2016
Grant date	Jul 19, 2016

Abstract

A combustor assembly having a fuel pre-mixer including a duct for mixing an airflow and a fuel therein. Also included is a center body coaxially aligned within the duct for receiving the fuel from a fuel source and configured to distribute the fuel to at least one axial location within the duct. Further included is a planar vane section in communication with the airflow and the fuel to provide a first injection of fuel and a flow conditioning effect on the airflow. Yet further included is a swirler vane section disposed downstream of the planar vane section, wherein the swirler vane section is configured to provide a second injection of fuel and a mixing of the fuel and the airflow.

First claim

The invention claimed is:

1. A combustor assembly having a fuel pre-mixer comprising:
a duct for mixing an airflow and a fuel therein;
a center body coaxially aligned within the duct for receiving the fuel from a fuel source and configured to distribute the fuel to at least one axial location within the duct;
a planar vane section in communication with the airflow and the fuel source to provide a first injection of fuel and a flow conditioning effect on the airflow, the planar vane section comprising a plurality of relatively planar vanes, each planar vane having a leading edge axially spaced from a trailing edge, wherein the leading edge and the trailing edge of each planar vane are axially aligned, wherein the plurality of planar vanes is circumferentially spaced around the centerbody, each of the plurality of relatively planar vanes having a planar portion aligned in a longitudinal direction of the duct to straighten the airflow and each two circumferentially adjacent planar vanes form an airflow channel therebetween; and
a swirler vane section disposed downstream of the planar vane section, the swirler vane section comprising a plurality of circumferentially spaced swirler vanes, each of the plurality of swirler vanes having a leading edge positioned downstream from corresponding trailing edge of the two circumferentially adjacent planar vanes of the plurality of plurality of planar vanes, wherein the leading edge of each swirler vane is circumferentially offset from the two circumferentially adjacent planar vanes of the plurality of planar vanes, thereby forming a staggered formation between the planar vane section and the swirler vane section, wherein the swirler vane section is configured to provide a second injection of fuel and a mixing of the fuel and the airflow.

2. The combustor assembly of claim 1 , wherein each of the plurality of relatively planar vanes is operably connected to, and extends radially outward from, the center body, wherein the fuel is distributed through the plurality of relatively planar vanes and ejected at a plurality of radial locations to a flow path of the duct for mixing with the airflow.

3. The combustor assembly of claim 1 , wherein at least a portion of each of the plurality of swirler vanes is disposed at an angle to a longitudinal direction of the duct.

4. The combustor assembly of claim 3 , wherein each of the plurality of swirler vanes is operably connected to, and extends radially outward from, the center body, wherein the fuel is distributed through the plurality of swirler vanes and ejected at a plurality of radial locations to a flow path of the duct for mixing with the airflow.

5. The combustor assembly of claim 1 , wherein the airflow is received from a compressor, wherein the fuel source is a fuel manifold.

6. The combustor assembly of claim 1 , wherein the fuel is distributed to a flow path of the duct through the planar vane section and the swirler vane section, wherein a first fraction of the fuel is distributed through the planar vane section and a remaining fraction of the fuel is distributed through the swirler vane section.

7. A combustor having a fuel pre-mixer comprising:
a duct having a first end for receiving an airflow from a compressor disposed upstream of the combustor assembly, wherein the airflow is transferred through the duct along a longitudinal direction of the duct;
A center body disposed within and along the longitudinal direction of the duct and configured to receive a fuel from at least one fuel manifold proximate the first end of the duct;
a planar vane section comprising a plurality of relatively planar vanes circumferentially spaced from each other, wherein each planar vane of the plurality of relatively planar vanes includes a leading edge axially spaced from a trailing edge and aligned in the longitudinal direction of the duct to straighten the airflow, the plurality of relatively planar vanes disposed at a first axial location within the duct, wherein the planar vane section is in communication with the airflow and the fuel source and each two circumferentially adjacent planar vanes form an airflow channel therebetween; and
a swirler vane section comprising a plurality of swirler vanes circumferentially spaced from each other and disposed at a second axial location within the duct, each of the plurality of swirler vanes having a leading edge positioned downstream from corresponding trailing edges of the two circumferentially adjacent planar vanes of the plurality of planar vanes, wherein the leading edge of each swirler vane is circumferentially offset from the two circumferentially adjacent planar vanes of the plurality of planar vanes, thereby forming a staggered formation between the planar vane section and the swirler vane section, wherein the second axial location is downstream of the first axial location.

8. The combustor assembly of claim 7 , wherein each of the plurality of relatively planar vanes is operably connected to, and extends radially outward from, the center body, wherein the fuel is distributed through the plurality of relatively planar vanes and ejected at a plurality of radial locations to a flow path of the duct for mixing with the airflow.

9. The combustor assembly of claim 7 , wherein at least a portion of each of the plurality of swirler vanes is disposed at an angle to the longitudinal direction of the duct wherein each of the plurality of swirler vanes is operably connected to, and extends radially outward from, the center body, wherein the fuel is distributed through the plurality of relatively planar vanes and ejected at a plurality of radial locations to a flow path of the duct for mixing with the airflow.

10. A gas turbine system comprising;
a compressor for providing an airflow; and
a fuel pre-mixer comprising:
a duct for receiving the airflow, wherein the airflow is transferred through the duct in a first direction and mixed with a fuel;
a first vane section comprising a plurality of relatively planar vanes circumferentially spaced from each other and extending radially between a center body and an inner wall of the duct, wherein each planar vane of the plurality of relatively planar vanes includes a leading edge axially spaced from a trailing edge and aligned in a longitudinal direction of the duct to straighten the airflow and each two circumferentially adjacent planar vanes form an airflow channel there between; and
a second vane section comprising a plurality of swirler vanes circumferentially spaced from each other and extending radially between the center body and the inner wall of the duct, each of the plurality of swirler vanes having a leading edge positioned downstream from corresponding trailing edges of the two circumferentially adjacent planar vanes of the plurality of planar vanes, wherein the leading edge of each swirler vane is circumferentially offset from the two circumferentially adjacent planar vanes of the plurality of planar vanes, thereby forming a staggered formation between the planar vane section and the swirler vane section, wherein at least a portion of each of the plurality of swirler vanes is posed at an angle to the first direction.

11. The gas turbine system of claim 10 , wherein the fuel is distributed to a flow path of the duct through the first vane section and the second vane section, wherein a first fraction of the fuel is distributed through the first vane section and a remaining fraction of the fuel is distributed through the second vane section.

12. The gas turbine system of claim 10 , wherein the swirler vane leading edge of the plurality of swirler vanes is offset from an in-line plane of the plurality of relatively planar vane

Assignees

• Bobba Mohan Krishna
• Khan Abdul Rafey
• Gen Electric

Inventors

• Bobba Mohan Krishna
• Khan Abdul Rafey

Classifications

• F23R3/286

  having fuel-air premixing devices (F23R3/30 takes precedence) · CPC title

• F23D14/64

  with injectors · CPC title

• F23R3/14 Primary

  by using swirl vanes · CPC title

• F23D2900/14021

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