An anti-icing system for a gas turbine system includes multiple nozzle assemblies. Each nozzle assembly of the multiple nozzle assemblies includes a nozzle having one or more outlets that are configured to inject a heated fluid in a radially outward direction and a cap having an annular wall that circumferentially surrounds at least a portion of the nozzle. The cap is configured to direct the heated fluid to flow in an upstream direction into an airflow to facilitate mixing of the heated fluid with the airflow.
Anti-icing for gas turbine system
18.10.2022
Patent
Elektronische Ressource
Englisch