Gas turbine engines include a compressor section having an impeller configured to compress a core flow. A combustor section having a combustor is arranged downstream from the compressor section along a path of the core flow. A turbine section is arranged downstream from the combustor section along the path of the core flow, with the turbine section having a plurality of first vanes arranged at an outlet of the combustor and at least one first vane of the plurality of first vanes includes an internal vane path. The path of the core flow, in a flow direction, passes through the impeller of the compressor section, the internal vane path internal to the first vane, the combustor, and then between external surfaces of the plurality of first vanes to enter the turbine section.


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    Title :

    Integrated centrifugal compressor diffuser and high pressure turbine vane assembly


    Contributors:

    Publication date :

    2024-11-12


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F04D Strömungsarbeitsmaschinen , NON-POSITIVE-DISPLACEMENT PUMPS