Anti-icing and bleed heat system for a gas turbine system
AssigneeGE Infrastructure Technology LLC
InventorsLaxmikant Merchant, Senthilkumar Jeyaraj
Life of this patent
Estimating the term…
Abstract
An anti-icing system for a gas turbine system has a finned conduit that includes a heated fluid conduit defining a flowpath extending along the heated fluid conduit, and a plurality of fins spaced along the conduit and extending radially outward from the conduit. The finned conduit is configured to be installed in an air intake conduit of the gas turbine system, to receive a heated fluid flowing along the flowpath, and to transfer heat from the heated fluid to air flowing through the air intake conduit of the gas turbine system.
Claims20
An anti-icing system for a gas turbine system, the anti-icing system comprising:
- a finned conduit comprising:
- a heated fluid conduit defining a flowpath extending in an axial direction along the heated fluid conduit;
- and
- a plurality of fins spaced along the heated fluid conduit and extending radially outward from the heated fluid conduit;
- wherein the finned conduit is configured to be installed in an air intake conduit of the gas turbine system, to receive a heated fluid flowing along the flowpath, and to transfer heat from the heated fluid to air flowing through the air intake conduit of the gas turbine system.
A gas turbine system, comprising:
- a compressor;
- and
- an air intake system comprising an air intake conduit, a filter system, and an anti-icing system, wherein the air intake system is configured to supply a heated airflow to the compressor and wherein the anti-icing system comprises:
- a plurality of finned conduits disposed within the air intake system, upstream of the filter system, wherein each of the plurality of finned conduits comprises:
- a heated fluid conduit defining a flowpath extending in an axial direction along the heated fluid conduit;
- and
- a plurality of fins spaced along the heated fluid conduit and extending radially outward from the heated fluid conduit;
- wherein each of the plurality of finned conduits is configured to receive a heated fluid extracted from the compressor and flowing along the flowpath and to transfer heat from the heated fluid to air flowing through the air intake conduit of the gas turbine system.
A method of operating an anti-icing system for a gas turbine system, comprising:
- extracting a heated fluid from a compressor of the gas turbine system;
- directing the heated fluid through a heated fluid conduit of a finned conduit, wherein the finned conduit is disposed within an air intake conduit of the gas turbine system upstream of a filter with respect to air flowing through the air intake conduit;
- wherein the finned conduit comprises a plurality of fins spaced in an axial direction along the heated fluid conduit and extending radially outward from the heated fluid conduit, wherein the finned conduit is configured to transfer heat from the heated fluid to the air flowing through the air intake conduit of the gas turbine system;
- and
- injecting the heated fluid into the air intake conduit at a location downstream of the filter.
Dependencies are inferred from the claim text.