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 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;
- a first valve configured to control a first flow rate of the first portion of the heated fluid into the plurality of nozzles;
- 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 and upstream of a compressor of the gas turbine system;
- a second valve configured to control a second flow rate of the second portion of the heated fluid through the bypass conduit;
- and
- a controller configured to adjust the first valve and the second valve to adjust a ratio of the first flow rate to the second flow rate.
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;
- 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 and upstream of the compressor of the gas turbine system;
- a first valve configured to control a first flow rate of the first portion of the heated fluid through the bypass conduit;
- a second valve configured to control a second flow rate of the second portion of the heated fluid to the plurality of nozzles;
- and
- a controller configured to adjust the first valve and the second valve to adjust a ratio of the first flow rate to the second flow rate.
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;
- 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 and upstream of the compressor of the gas turbine system;
- and
- controlling operation of a first valve configured to control a first flow rate of the first portion of the heated fluid to the plurality of nozzles and a second valve configured to control a second flow rate of the second portion of the heated fluid through the bypass conduit to adjust a ratio of the first flow rate to the second flow rate.
Dependencies are inferred from the claim text.