Anti-icing and bleed heat system for a gas turbine system
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.
1 . 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.
2 . The anti-icing system of claim 1 , wherein the plurality of nozzles is coupled to a manifold that is configured to distribute the heated fluid to the plurality of nozzles.
3 . The anti-icing system of claim 2 , wherein the plurality of nozzles is arranged as a two-dimensional grid and is positioned upstream of the manifold.
4 . The anti-icing system of claim 1 , wherein the plurality of nozzles is configured to heat the airflow within the air intake conduit of the gas turbine system to a first temperature greater than a threshold temperature above a dew point of the airflow through the air intake conduit of the gas turbine system at a location at or upstream of a face of the filter.
5 . The anti-icing system of claim 4 , wherein the plurality of nozzles is configured to heat the airflow within the air intake conduit of the gas turbine system to a temperature less than a second threshold temperature at the location at or upstream of the face of the filter.
6 . The anti-icing system of claim 2 , comprising one or more sensors configured to measure a temperature of the airflow at one or more locations within the air intake conduit.
7 . The anti-icing system of claim 6 , comprising a third valve configured to control a third flow rate of the heated fluid through a bleed conduit, wherein the bleed conduit is fluidly coupled to the manifold, the bypass conduit, and the compressor of the gas turbine system.
8 . The anti-icing system of claim 7 , wherein the heated fluid extracted from the compressor of the gas turbine system through the bleed conduit is equal to 6% of total compressor flow.
9 . The anti-icing system of claim 7 , wherein the controller is configured to control operation of the third valve.
10 . The anti-icing system of claim 9 , wherein the controller is configured to control operation of the first valve and second valve based on measurements by the one or more sensors.
11 . 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.
12 . The gas turbine system of claim 11 , wherein the heated fluid comprises compressed air bled from the compressor of the gas turbine system through a bleed conduit fluidly coupled to the anti-icing system.
13 . The gas turbine system of claim 11 , wherein the anti-icing system comprises
one or more sensors configured to measure a temperature of the airflow at one or more locations within the air intake conduit,
wherein the controller is configured to control operation of the first valve and the second valve based on measurements by the one or more sensors.
14 . 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.
15 . The method of claim 14 , comprising:
receiving, from one or more sensors disposed within the air intake conduit of the gas turbine system, one or more measurements representative of a measured temperature of the airflow at one or more locations within the air intake conduit; and
controlling operation of the first valve and the second valve based on the one or more measurements.
16 . The method of claim 15 , wherein injecting the first portion of the heated fluid is configured to heat the airflow within the air intake conduit of the gas turbine system to a first temperature greater than a first threshold temperature above a dew point of the airflow through the air intake conduit of the gas turbine system, but less than a second threshold temperature at a location at or upstream of a face of the filter.
17 . The anti-icing system of claim 1 , wherein the controller is configured to adjust the first valve to reduce the first flow rate and adjust the second valve to increase the second flow rate in response to a measured temperature in the air intake conduit, between the plurality of nozzles and the filter exceeding an upper threshold temperature.
18 . The anti-icing system of claim 1 , wherein the controller is configured to adjust the first valve to increase the first flow rate and adjust the second valve to decrease the second flow rate in response to a measured temperature in the air intake conduit, between the plurality of nozzles and the filter being below a lower threshold temperature.