Micromixer assembly for a turbine system and method of distributing an air-fuel mixture to a combustor chamber

Patent metadata

Field	Value
Publication number	US-9416973-B2
Application number	US-201313735448-A
Country	US
Kind code	B2
Filing date	Jan 7, 2013
Priority date	Jan 7, 2013
Publication date	Aug 16, 2016
Grant date	Aug 16, 2016

Abstract

A micromixer assembly for a turbine system includes a plurality of pipes each having an inlet for receiving an airflow from an annulus defined by an inwardly disposed liner and an outwardly disposed sleeve, each of the plurality of pipes also including an outlet for dispersing an air-fuel mixture into a combustor chamber. Also included is a first portion of each of the plurality of pipes. Further included is a second portion of each of the plurality of pipes, the second portion comprising the inlet for receiving the airflow. Yet further included is at least one fuel receiving path in communication with at least one of the first portion and the second portion.

First claim

The invention claimed is:

1. A micromixer assembly for a turbine system comprising:
a plurality of pipes, each pipe comprising an inlet section and an outlet section, the inlet section having an inlet in fluid communication with an annulus defined by an inwardly disposed liner and an outwardly disposed sleeve of a combustor, the inlet receiving an air-fuel mixture entering the inlet in a first direction from the annulus, wherein the inlet is directly coupled to the annulus, the outlet section including a straight portion terminating in an outlet for dispersing the air-fuel mixture into a combustor chamber; wherein the inlet section further defines a curved portion between the inlet and the straight portion of the outlet section, the curved portion redirecting the air-fuel mixture from a first flow direction to a second flow direction different from the first flow direction.

2. The micromixer assembly of claim 1 , wherein the air-fuel mixture is redirected from the inlet to the outlet at an angle of from 90° to 180°, wherein the angle is defined between a first line drawn parallel to a transverse through the inlet and a second line drawn parallel to a transverse through the outlet.

3. The micromixer assembly of claim 1 , further comprising a fuel injector arrangement disposed at least partially in the annulus, the fuel injector arrangement comprising at least one airfoil-shaped region with at least one hole for dispensing fuel.

4. The micromixer assembly of claim 1 , wherein at least a portion of the micromixer assembly is formed by a casting process.

5. A micromixer assembly for a turbine system comprising:
a fuel injector arrangement disposed at least partially in an annulus defined between an inwardly disposed liner and an outwardly disposed sleeve of a combustor, the fuel injector arrangement injecting a fuel into the annulus for mixing with an airflow to produce an air-fuel mixture;
a plurality of pipes, each pipe comprising an inlet section and an outlet section, the inlet section having an inlet in fluid communication with the annulus for receiving an air-fuel mixture in a first flow direction from the annulus, wherein the inlet is directly coupled to the annulus, the outlet section having a straight portion terminating in an outlet for dispersing the air-fuel mixture into a combustor chamber; wherein the inlet section further defines curved region between the inlet and the straight portion of the outlet section for redirecting the air-fuel mixture from a first flow direction to a second flow direction different from the first flow direction.

6. The micromixer assembly of claim 5 , wherein the fuel injector arrangement comprises at least one airfoil having at least one aperture for injecting the fuel into the airflow flowing throughout the annulus toward an endcover of a combustor assembly.

7. The micromixer assembly of claim 5 , wherein the air-fuel mixture is redirected from the inlet to the outlet at an angle of 180°, wherein the angle is defined between a first line drawn parallel to a transverse through the inlet and a second line drawn parallel to a transverse through the outlet.

8. The micromixer assembly of claim 5 , wherein at least a portion of the micromixer assembly is formed by a casting process or an additive metal process.

Assignees

• Gen Electric

Inventors

• Melton Patrick Benedict
• Boardman Gregory Allen

Classifications

• F23R3/286 Primary

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

• F23R3/46

  Combustion chambers comprising an annular arrangement of {several essentially tubular} flame tubes within a common annular casing or within individual casings · CPC title

• F23R2900/00018

  Manufacturing combustion chamber liners or subparts · CPC title