Staged fuel and air injection in combustion systems of gas turbines

Patent metadata

Field	Value
Publication number	US-2017191668-A1
Application number	US-201614988999-A
Country	US
Kind code	A1
Filing date	Jan 6, 2016
Priority date	Jan 6, 2016
Publication date	Jul 6, 2017
Grant date	—

Abstract

A gas turbine that includes: a combustor coupled to a turbine that together define a working fluid flowpath, the working fluid flowpath extending aftward along a longitudinal axis from a forward end defined by a forward injector in the combustor, through an interface at which the combustor ends and the turbine begins, and then through the turbine to an aftward end; a gap formed at the interface between the combustor and the turbine; and a fuel injector disposed near the gap for injecting a fuel into an airflow that passes through the gap. The gap may include a former leakage pathway occurring at the interface. The former leakage pathway may be expanded so to accommodate a desired level for the airflow passing therethrough.

First claim

That which is claimed:

1 . A gas turbine that comprises:
a combustor coupled to a turbine that together define a working fluid flowpath, the working fluid flowpath extending aftward along a longitudinal axis from a forward end defined by a forward injector in the combustor, through an interface at which the combustor ends and the turbine begins, and then through the turbine to an aftward end; a gap formed at the interface between the combustor and the turbine; and a fuel injector disposed near the gap for injecting a fuel into an airflow that passes through the gap.

2 . The gas turbine according to claim 1 , wherein the gap comprises a former leakage pathway occurring at the interface, the former leakage pathway being expanded so to accommodate a desired level for the airflow passing therethrough; and
wherein the gap comprises an axial gap defined to a forward side by structure rigidly attached to the combustor and to an aftward side by structure rigidly attached to the turbine.

3 . The gas turbine according to claim 1 , wherein the fuel injector comprises a staged injector, and wherein the forward injector and the fuel injector comprise a staged injection system;
further comprising:
a compressor discharge cavity formed about the working fluid flowpath for receiving a combustor air supply delivered thereto by a compressor;
circumferentially spaced stator blades positioned so to form a row of stator blades in the turbine, each of the stator blades comprising an airfoil extending across the working fluid flowpath;
fuel directing structure configured to apportion a combustor fuel supply between the forward injector and the fuel injector; and
air directing structure configured to apportion the combustor air supply between the forward injector and the gap;
wherein the combustor comprises an inner radial wall, which defines a combustion zone downstream of the forward injector, and an outer radial wall formed concentrically about the inner radial wall such that a flow annulus is formed therebetween.

4 . The gas turbine according to claim 3 , further comprising a flowpath wall that defines the working fluid flowpath through the combustor and the turbine;
wherein the gap comprises an axial gap defined between a forward most edge of the flowpath wall of the turbine and an aftward most edge of the flowpath wall of the combustor; wherein the gap fluidly communicates with the compressor discharge cavity such that the airflow flowing through the gap is derived therefrom; and wherein the combustor comprises one of an annular combustor and a can-annular combustor.

5 . The gas turbine according to claim 4 , further comprising a flowpath wall that defines the working fluid flowpath through each of the combustor and the turbine;
wherein, within the turbine:
the flowpath wall comprises an inboard flowpath wall that defines an inboard boundary of the working fluid flowpath and an outboard flowpath wall that defines an outboard boundary of the working fluid flowpath, the outboard flowpath wall concentrically formed about the inboard flowpath wall such that the working fluid flowpath through the turbine comprises an annular cross-sectional shape;
a forward edge of the inboard flowpath wall comprises a forward terminating point of the inboard flowpath wall; and
a forward edge of the outboard flowpath wall comprises a forward terminating point of the outboard flowpath wall.

6 . The gas turbine according to claim 5 , wherein the combustor comprises a can-annular combustor;
wherein the inner radial wall of the combustor comprises a cross-sectional shape that transitions axially between an approximate cylindrical shape at a forward end to a cross-sectional shape at an aftward end that corresponds to a cross-sectional shape of a segment of the annular shape of the working fluid flowpath turbine at the interface; wherein, within the combustor:
the flowpath wall comprises the inner radial wall; and
an aftward edge of the inner radial wall comprises an aftward terminating point of the inner radial wall; and
wherein the axial gap is defined between at least one of the forward edges of the inboard and outboard flowpath walls within the turbine and a corresponding opposing section of the aftward edge of the inner radial wall within the combustor.

7 . The gas turbine according to claim 5 , wherein the combustor comprises an annular combustor;
wherein, within the combustor:
the flowpath wall comprises an inboard flowpath wall that defines an inboard boundary of the working fluid flowpath and an outboard flowpath wall that defines an outboard boundary of the working fluid flowpath, the outboard flowpath wall concentrically formed about the inboard flowpath wall such that the working fluid flowpath through the combustor comprises an annular cross-sectional shape;
an aftward edge of the inboard flowpath wall comprises an aftward terminating point of the inboard flowpath wall; and
an aftward edge of the outboard flowpath wall comprises an aftward terminating point of the outboard flowpath wall; and
wherein the axial gap is defined between: i) at least one of the aftward edges of the inboard and outboard flowpath walls of the combustor; and ii) at least one of the forward edges of the inboard and outboard flowpath walls of the turbine.

8 . The gas turbine according to claim 4 , wherein:
the airfoils of the stator blades attach to inboard sidewalls and outboard sidewalls that define, respectively, axial sections of the inboard flowpath wall and the outboard flowpath wall of the turbine; and the combustor comprises an aft frame configured to support the flowpath wall of the combustor at an aftward end of the combustion zone; wherein:
at least one of the inboard and outboard sidewalls of the stator blades forms the forward most edge of the flowpath wall of the turbine; and
the aft frame forms the aftward most edge of the flowpath wall of the combustor.

9 . The gas turbine according to claim 8 , wherein, for each of the stator blades, the inboard sidewall, the outboard sidewall, and the airfoil comprises integrally formed components.

10 . The gas turbine according to claim 4 , wherein the gap comprises a gap width that signifies an axial distance between the forward most edge of the flowpath wall of the turbine and the aftward most edge of the flowpath wall of the combustor; and
wherein the forward most edge of the flowpath wall of the turbine and the aftward most edge of the flowpath wall of the combustor is configured such that the gap width is substantially constant.

11 . The gas turbine according to claim 4 , wherein the gap comprises a gap width that signifies an axial distance between the forward most edge of the flowpath wall of the turbine and the aftward most edge of the flowpath wall of the combustor; and
wherein the forward most edge of the flowpath wall of the turbine and the aftward most edge of the flowpath wall of the combustor comprises a contoured edge such that the gap width is variable.

12 . The gas turbine according to claim 11 , wherein the contoured edge profile comprises a repeating triangle.

13 . The gas turbine according to claim 11 , wherein the contoured edge profile comprises a sinusoidal wave.

14 . The gas turbine according to claim 11 , wherein both of the forward most edge of the flowpath wall of the turbine and the aftward most edge of the flowpath wall of the combustor comprises the contoured edge profile; and
wherein the contoured edge profiles are configured to complement each other such that a predetermined repeating pattern is formed.

15 . Th

Assignees

• Gen Electric

Inventors

• Hughes Michael John
• Berry Jonathan Dwight
• Flanagan James Scott

Classifications

• F23R3/002

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

• F05D2220/32

  in gas turbines · CPC title

• F02C7/222

  Fuel flow conduits, e.g. manifolds · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F23R3/346 Primary

  for staged combustion · CPC title