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.


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    Title :

    Anti-icing for gas turbine system


    Contributors:

    Publication date :

    2022-10-18


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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