Systems and apparatus relating to downstream fuel and air injection in gas turbines

Patent metadata

Field	Value
Publication number	US-9435541-B2
Application number	US-201313836938-A
Country	US
Kind code	B2
Filing date	Mar 15, 2013
Priority date	Mar 15, 2013
Publication date	Sep 6, 2016
Grant date	Sep 6, 2016

Abstract

A gas turbine that includes: a combustor coupled to a turbine that together define an interior flowpath, the interior flowpath extending aftward about a longitudinal axis from a primary air and fuel injection system that defines a forward end, through an interface at which the combustor connects to the turbine, and through a row of stator blades in the turbine that defines an aft end; and a downstream injection system that includes two injection stages, a first stage and a second stage, that are axially spaced along the longitudinal axis of the interior flowpath. The first stage and the second stage each includes multiple injectors configured to inject an air and fuel mixture into the interior flowpath.

First claim

We claim:

1. A gas turbine comprising:
a combustor coupled to a turbine that together define an interior flowpath, the interior flowpath extending aftward about a longitudinal axis from a forward end of the interior flowpath that connects to a primary air and fuel injection system, through an interface at which the combustor connects to the turbine, and through a row of stator blades in the turbine that defines an aft end of the interior flowpath; and
a downstream injection system that includes two injection stages, a first stage and a second stage, which are axially spaced along the longitudinal axis of the interior flowpath;
wherein the first stage and the second stage each includes multiple injectors configured to inject an air and fuel mixture into the interior flowpath;
wherein:
the first stage is positioned aft of an axial midpoint defined along the interior flowpath between the primary air and fuel injection system and the interface; and
the second stage is spaced aftward from the first stage;

wherein:
immediately aft of the primary air and fuel injection system, the interior flowpath includes a primary combustion zone defined by a surrounding liner and, immediately aft of the liner, the interior flowpath includes a transition zone defined by a surrounding transition piece;
the transition piece is configured to fluidly couple the primary combustion zone to the turbine, the transition piece having a shape that transitions from a cylindrical cross-sectional shape of the liner to an annular cross-sectional shape of the turbine;
the transition piece comprises an aft frame that forms the interface between the combustor and the turbine;
the first stage of the downstream injection system is positioned within the transition zone and the second stage of the downstream injection system is spaced aftward from the first stage;

wherein:
the injectors of the first stage are circumferentially arrayed about a common injection plane, the common injection plane being aligned approximately perpendicular relative to the longitudinal axis of the interior flowpath; and
the injectors of the second stage are circumferentially arrayed about a common injection plane, the common injection plane of the second stage being aligned approximately perpendicular relative to the longitudinal axis of the interior flowpath;

wherein:
the common injection plane of the first stage is spaced aftward from an upstream end of the transition piece;
the common injection plane of the second stage is spaced at or aftward from the aft frame.

2. The gas turbine of claim 1 , wherein the common injection plane of the second stage is positioned at the aft frame, and wherein the injectors of the second stage are integrated into the aft frame.

3. The gas turbine of claim 1 , wherein the common injection plane of the second stage is positioned at the row of stator blades in the turbine; and
wherein the injectors of the second stage are integrated into the row of stator blades.

4. The gas turbine of claim 1 , wherein the common injection plane of the first stage is positioned at the aft frame of the combustor and the common injection plane of the second stage is positioned at the row of stator blades in the turbine;
wherein the injectors of the first stage are integrated into the aft frame and the injectors of the second stage are integrated into the row of stator blades.

5. The gas turbine of claim 1 , wherein the downstream injection system comprises a third stage positioned within the interior flowpath, the third stage being configured to inject both air and fuel into the interior flowpath;
wherein the second stage and the third stage are each axially spaced from the other along the longitudinal axis of the interior flowpath, the third stage comprising an axial position that is aft of the second stage.

6. The gas turbine of claim 5 ,
wherein the first stage of the downstream injection system is positioned within the transition zone.

7. The gas turbine of claim 6 , wherein the second stage is positioned at the aft frame of the combustor and the third stage is positioned at the row of stator blades in the turbine, and wherein the second stage is integrated into the aft frame and the third stage is integrated into the row of stator blades.

8. A gas turbine comprising:
a combustor coupled to a turbine that together define an interior flowpath, the interior flowpath extending aftward about a longitudinal axis from a forward end of the interior flowpath that connects to a primary air and fuel injection system, through an interface at which the combustor connects to the turbine, and through a row of stator blades in the turbine that defines an aft end of the interior flowpath; and
a downstream injection system that includes three injection stages, a first stage, a second stage, and a third stage, which are axially spaced along the longitudinal axis of the interior flowpath;
wherein the first stage, the second stage, and the third stage each includes multiple injectors configured to inject an air and fuel mixture into the interior flowpath;
wherein the third stage being positioned aftward of the second stage; and
wherein the third stage is positioned at the row of stator blades in the turbine.

9. The gas turbine of claim 8 , wherein the injectors of the third stage are integrated into the row of stator blades.

Assignees

• Gen Electric

Inventors

• Davis Jr Lewis Berkley
• Venkataraman Krishna Kumar
• Graham Kaitlin Marie

Classifications

• F23R3/286

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

• F23R3/346 Primary

  for staged combustion · CPC title

• F23R3/20

  incorporating fuel injection means · CPC title