Combustor mixing assembly

Patent metadata

Field	Value
Publication number	US-11754288-B2
Application number	US-202017115877-A
Country	US
Kind code	B2
Filing date	Dec 9, 2020
Priority date	Dec 9, 2020
Publication date	Sep 12, 2023
Grant date	Sep 12, 2023

Abstract

A mixing assembly for a combustor, including: a pilot mixer and a pilot fuel nozzle; a main mixer including: a main housing surrounding the pilot mixer; a fuel manifold positioned between the pilot housing and the main housing; a mixer foot extending outward from a forward end of the main housing; a main swirler body surrounding the main housing such that an annular mixing channel is defined between the main housing and the main swirler body, and coupled to the mixer foot; and a main fuel ring in the mixing channel downstream of the mixer foot connected to the main housing by main fuel vanes, at least one of the main fuel ring and the main fuel vanes including fuel injection ports positioned to discharge fuel into a central portion of the mixing channel, wherein the mixer foot extends farther from the main housing than the main fuel ring.

First claim

What is claimed is:

1. A mixing assembly for a combustor, comprising:
a pilot mixer including an annular pilot housing having a hollow interior extending along a mixer centerline and a pilot fuel nozzle mounted in the annular pilot housing;
a main mixer including:
a main housing surrounding the annular pilot housing, the main housing having a forward end and an aft end;
a fuel manifold positioned between the annular pilot housing and the main housing;
a mixer foot extending outward from the forward end of the main housing;
a main swirler body including a plurality of swirl vanes, the main swirler body surrounding the main housing such that an annular mixing channel is defined between the main housing and the main swirler body, and the main swirler body being coupled to the mixer foot to define a forward end of the annular mixing channel; and
a main fuel ring disposed in the annular mixing channel downstream of the mixer foot and connected to the main housing by a plurality of main fuel vanes arranged in a circumferential array about the mixer centerline, each main fuel vane of the plurality of main fuel vanes extending outward from the main housing into the annular mixing channel, the main fuel ring including a first plurality of fuel injection ports positioned to discharge fuel into a central portion of the annular mixing channel, wherein the mixer foot extends outward farther from the main housing than the main fuel ring;
wherein the main fuel ring is positioned in the central portion of the mixing channel, the central portion being defined radially from the mixer centerline and extending circumferentially about the mixer centerline,
wherein the fuel manifold is radially inward of the plurality of main fuel vanes and supplies the fuel to the plurality of main fuel vanes and the main fuel ring, and
wherein an aft portion of the main fuel ring includes a plurality of corrugations forming a lobed mixer.

2. The mixing assembly of claim 1 , wherein the plurality of main fuel vanes include a second plurality of fuel injection ports.

3. The mixing assembly of claim 1 , wherein the plurality of main fuel vanes are oriented to produce swirl in a flow of air passing therethrough.

4. The mixing assembly of claim 1 , wherein the mixer foot includes a plurality of slats passing therethrough.

5. The mixing assembly of claim 1 , wherein the main swirler body includes an upstream first main swirler and a downstream second main swirler.

6. A combustor for ag turbine, comprising:
an annular inner liner having an upstream end and a downstream end;
an annular outer liner having an upstream end and a downstream end; and
a mixer assembly, comprising:
a pilot mixer inducing an annular allot housing having a hollow interior extending along a mixer centerline and a pilot fuel nozzle mounted in the annular pilot housing;
a main mixer including:
a main housing surrounding the annular pilot housing, the main housing having a forward end and an aft end:
a fuel manifold positioned between the annular pilot housing and the main housing;
a mixer foot extending outward from the forward end of the main housing;
a main swirler body including a plurality of swirl vanes, the main swirler body surrounding the main housing such that an annular mixing channel is defined between the main housing and the main swirler body, and the main swirler body being coupled to the mixer foot to define a forward end of the annular mixing channel; and
a main fuel ring disposed in the annular mixing channel downstream of the mixer foot and connected to the main housing by a plurality of main fuel vanes arranged in a circumferential array about the mixer centerline, each main fuel vane of the plurality of main fuel vanes extending outward from the main housing into the annular mixing channel, the main fuel ring including a first plurality of fuel injection ports positioned to discharge fuel into a central portion of the annular mixing channel, wherein the mixer foot extends outward farther from the main housing than the main fuel ring;
wherein the main fuel ring is positioned in the central portion of the mixing channel, the central portion being defined radially from the mixer centerline and extending circumferentially about the mixer centerline,
wherein the fuel manifold is radially inward of the plurality of main fuel vanes and supplies the fuel to the plurality of main fuel vanes and the main fuel ring, and
wherein an aft portion of the main fuel ring includes a plurality of corrugations forming a lobed mixer;

wherein the mixer assembly is disposed at the upstream end of the annular inner liner and at the upstream end of the annular outer liner.

Assignees

• Gen Electric

Inventors

• Chandra Hari Ravi
• Rao Arvind Kumar
• Birmaher Shai
• Sekar Jayanth
• Gandikota Gurunath
• Benjamin Michael A

Classifications

• F23R3/286 Primary

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

• F23R3/343 Primary

  Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion (ignition in gas-turbine plants F02C7/264; pilot flame igniters F23Q9/00) · CPC title

• F23R3/38

  comprising rotary fuel injection means · CPC title

• F23R3/04

  Air inlet arrangements · CPC title

• F23R3/14

  by using swirl vanes · CPC title