Axial fuel staging system for gas turbine combustors

Patent metadata

Field	Value
Publication number	US-11137144-B2
Application number	US-201715838149-A
Country	US
Kind code	B2
Filing date	Dec 11, 2017
Priority date	Dec 11, 2017
Publication date	Oct 5, 2021
Grant date	Oct 5, 2021

Abstract

A gas turbine combustor includes: a head end comprising a primary fuel nozzle; a liner defining a primary combustion zone proximate the head end and a downstream secondary combustion zone; a forward casing radially outward of and surrounding at least a portion of the liner; and an axial fuel staging system. The axial fuel staging system includes a plurality of fuel injection assemblies. Each fuel injection assembly includes a thimble assembly mounted to the liner, and an injector unit attached to the forward casing. A thimble of the thimble assembly extends through a thimble aperture in the liner. The injector unit extends through the forward casing, such that a portion of the injector unit is disposed within the thimble, and a fuel line fitting is disposed outward of the forward casing. The injector unit introduces fuel into air flowing through the thimble for injection into the secondary combustion zone.

First claim

What is claimed is:

1. A combustor comprising:
a head end comprising a primary fuel nozzle;
a liner coupled to the head end, the liner defining a primary combustion zone proximate the head end and a secondary combustion zone downstream of the primary combustion zone;
a forward casing radially outward of and surrounding at least a portion of the liner;
an outer sleeve disposed radially between the liner and the forward casing, the outer sleeve circumscribing at least a portion of the liner such that a first annulus is defined between the liner and the outer sleeve and a second annulus is defined between the outer sleeve and the forward casing;
an axial fuel staging system including a first fuel injection assembly, the first fuel injection assembly comprising:
a first thimble assembly mounted to the liner and including a first thimble extending through a first thimble aperture in the liner, such that an outlet portion of the first thimble is disposed in the secondary combustion zone inboard of the liner, the first thimble having an inlet portion in fluid communication with the second annulus; and
a first injector unit attached to the forward casing and extending radially through an injector port in the forward casing, such that a portion of the first injector unit is disposed within the first thimble and a main fuel inlet of the first injector unit is disposed radially outward of the forward casing, wherein the first injector unit, the injector port, the first thimble, and the first thimble aperture are disposed along an injection axis extending inwardly toward the secondary combustion zone;
wherein the first annulus between the liner and the outer sleeve conveys a first flow of air in a first direction toward the head end, and the second annulus between the outer sleeve and the forward casing conveys a second flow of air in a second, opposite direction away from the head end to the first thimble, the second flow of air from the second annulus being directed into the first thimble; and
wherein the first fuel injection assembly introduces a flow of fuel into the second flow of air flowing through the first thimble, such that fuel and air are injected into the secondary combustion zone in a direction transverse to a flow of combustion products from the primary combustion zone.

2. The combustor of claim 1 , wherein the axial fuel staging system comprises a plurality of axial fuel injection assemblies, each axial fuel injection assembly comprising:
a respective thimble assembly mounted to the liner;
a respective thimble extending through a respective thimble aperture in the liner, such that an inlet portion of the respective thimble is in fluid communication with the second annulus and an outlet portion of the respective thimble extends into the secondary combustion zone; and
a respective injector unit attached to the forward casing and extending radially through a respective injector port in the forward casing, such that a portion of each respective injector unit is disposed within the corresponding respective thimble and a respective fuel line fitting of the respective injector unit is disposed radially outward of the forward casing.

3. The combustor of claim 1 , wherein the axial fuel staging system includes a second fuel injection assembly disposed in a first circumferential direction from the first fuel injection assembly and a third fuel injection assembly disposed in a second, opposite circumferential direction from the first fuel injection assembly; and
wherein a first fuel supply line fluidly connects the first fuel injection assembly to the second fuel injection assembly, and a second fuel supply line fluidly connects the first fuel injection assembly to the third fuel injection assembly, the first fuel supply line and the second fuel supply line being disposed radially outward of the forward casing.

4. The combustor of claim 3 , wherein the axial fuel staging system includes a fourth fuel injection assembly disposed in the second circumferential direction from the third fuel injection assembly; and
wherein a third fuel supply line fluidly connects the third fuel injection assembly to the fourth fuel injection assembly, the third fuel supply line being disposed radially outward of the forward casing.

5. The combustor of claim 3 , wherein the first fuel injection assembly comprises a first fuel line fitting to which the first fuel supply line is secured and a second fuel line fitting to which the second fuel supply line is secured.

6. The combustor of claim 1 , further wherein the outer sleeve defines an injector opening aligned with the first thimble aperture in the liner and through which the first injector unit projects and through which the second flow of air is directed into the first thimble.

7. The combustor of claim 1 , wherein during installation, when the first injector unit and the first thimble are cold, the first injector unit and the first thimble have longitudinal axes that are offset from one another, wherein during engine operation, when the first injector unit and the first thimble are hot, the longitudinal axes of the of the first injector unit and the first thimble align with one another.

8. The combustor of claim 1 , wherein, along the injection axis, the first injector unit is elongated in an axial direction along a central axis of the combustor, wherein, along the injection axis, the first thimble is elongated in the axial direction along the central axis of the combustor.

9. The combustor of claim 8 , further comprising a transition piece disposed axially downstream of the liner and sealingly connected to the liner; and a compressor discharge case (CDC) circumferentially surrounding the transition piece and an aft end of the liner, the compressor discharge case comprising a CDC flange;
wherein a downstream portion of the forward casing comprises a first flange, the first flange being positioned adjacent to and being coupled to the CDC flange;
wherein the forward casing comprises an upstream casing portion and a downstream casing portion separate from the upstream casing portion, the downstream casing portion including the first flange and a second flange spaced axially apart from the first flange; and
wherein the first injector unit is mounted to the downstream casing portion between the first flange and the second flange.

10. The combustor of claim 9 , wherein the upstream casing portion comprises a third flange, the third flange being coupled to the second flange of the downstream casing portion.

11. The combustor of claim 1 , wherein the first flow of air through the first annulus splits into the second flow of air through the second annulus and a third flow of air through the head end.

12. A combustor comprising:
a head end comprising a primary fuel nozzle;
a liner coupled to the head end, the liner defining a primary combustion zone proximate the head end and a secondary combustion zone downstream of the primary combustion zone;
a forward casing radially outward of and surrounding at least a portion of the liner;
an outer sleeve disposed radially between the liner and the forward casing, the outer sleeve circumscribing at least a portion of the liner and defining a first annulus between the liner and the outer sleeve and a second annulus between the outer sleeve and the forward casing;
an axial fuel staging system including a plurality of fuel injection assemblies, the plurality of fuel injection assemblies including a first fuel injection assembly and a second fuel injection assembly, each fuel injection assembly of the plurality of fuel injection assemblies comprising:
a thimble assembly mounted to the liner and including a t

Assignees

• Gen Electric

Inventors

• Wilson Matthew Bernard
• Harper James
• Chong Yon Han
• Jones Charlie Edmond

Classifications

• F23R3/045

  using pipes · CPC title

• F23R3/346 Primary

  for staged combustion · CPC title

• F23R3/286

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

• F23R3/002

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• F23R2900/03341

  Sequential combustion chambers or burners · CPC title