Anti-icing and bleed heat system for a gas turbine system
AssigneeGE Infrastructure Technology LLC
InventorsLaxmikant Merchant, Senthilkumar Jeyaraj
Life of this patent
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Abstract
An anti-icing system for a gas turbine system includes a plurality of nozzles and a bypass conduit. Each nozzle of the plurality of nozzles includes one or more outlets that are configured to inject a first portion of a heated fluid into an airflow within an air intake conduit of the gas turbine system upstream of a filter. The bypass conduit is configured to direct a second portion of the heated fluid into the airflow within the air intake conduit downstream of the filter.
Claims18
An anti-icing system for a gas turbine system, the anti-icing system comprising:
- a plurality of nozzles, wherein each nozzle of the plurality of nozzles comprises one or more outlets that are configured to inject a first portion of a heated fluid into an airflow within an air intake conduit of the gas turbine system upstream of a filter;
- and
- a bypass conduit configured to direct a second portion of the heated fluid into the airflow within the air intake conduit downstream of the filter.
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 nozzles, wherein each nozzle of the plurality of nozzles comprises one or more outlets that are configured to inject a first portion of a heated fluid into an airflow within the air intake conduit upstream of the filter system;
- and
- a bypass conduit configured to direct a second portion of the heated fluid into the airflow within the air intake conduit downstream of the filter 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;
- injecting, via a plurality of nozzles, a first portion of the heated fluid into an airflow within an air intake conduit of the gas turbine system upstream of a filter;
- and
- injecting, from a bypass conduit, a second portion of the heated fluid into the airflow within the air intake conduit of the gas turbine system downstream of the filter.
Dependencies are inferred from the claim text.