Hot gas path duct for a combustor of a gas turbine
AssigneeGeneral Electric Company
InventorsRichard Martin DiCintio, Wei Chen
Life of this patent
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Abstract
A hot gas path duct or unibody liner for a gas turbine includes a main body having a forward end and an aft end. The main body defines a cross-sectional flow area and an axial flow length that extends between the forward end and the aft end. The main body further defines a fuel injection portion disposed downstream from the forward end and upstream from the aft end. The cross-sectional flow area decreases along the axial flow length between the forward end and the fuel injection portion and increases along at least a portion of the axial flow length downstream from the fuel injection portion.
Claims15
A unibody liner, comprising:
- a. a main body having a forward end and an aft end, the main body defining a cross-sectional flow area and an axial flow length that is defined between the forward end and the aft end, the main body further defining a fuel injection portion disposed downstream from the forward end and upstream from the aft end;
- and
- b. wherein the cross-sectional flow area decreases along the axial flow length between the forward end and the fuel injection portion and increases along at least a portion of the axial flow length downstream from the fuel injection portion and wherein the cross-sectional flow area increases continuously along the axial flow length downstream from the fuel injection portion to the aft end.
A combustor for a gas turbine, comprising:
- a. an end cover coupled to an outer casing;
- b. a fuel nozzle that extends downstream from the end cover;
- c. a cap assembly that at least partially surrounds the fuel nozzle;
- and
- d. a unibody liner that extends downstream from the cap assembly, the unibody liner comprising:
- i. a main body having a forward end and an aft end, the main body defining a cross-sectional flow area and an axial flow length that is defined between the forward end and the aft end, the main body further defining a fuel injection portion disposed downstream from the forward end and upstream from the aft end;
- and
- ii. wherein the cross-sectional flow area decreases along the axial flow length between the forward end and the fuel injection portion and increases along at least a portion of the axial flow length downstream from the fuel injection portion and wherein the cross-sectional flow area increases continuously along the axial flow length downstream from the fuel injection portion to the aft end.
A gas turbine comprising:
- a. a compressor;
- b. a combustor downstream from the compressor;
- c. a turbine having an inlet disposed downstream from the combustor;
- and
- d. wherein the combustor includes an end cover, a fuel nozzle that extends downstream from the end cover and a unibody liner that defines a flow path between the combustor and the inlet of the turbine, the unibody liner comprising:
- i. a main body having an upstream end and a downstream end, the main body defining a cross-sectional flow area;
- ii. an axial flow length that extends between the upstream end and the downstream end along an axial centerline of the unibody liner;
- iii. a conical portion that extends downstream from the forward end, a fuel injection portion that extends downstream from the conical portion and a transitional portion that extends downstream from the fuel injection portion;
- and
- iv. wherein the cross-sectional flow area decreases along the axial flow length from the upstream end to the fuel injection portion and increases along at least a portion of the axial flow length downstream from the fuel injection portion and wherein the cross-sectional flow area increases continuously along the axial flow length between the fuel injection portion and the downstream end of the main body.
Dependencies are inferred from the claim text.