A turbine rear structure for a gas turbine engine includes a central hub and a circumferential outer ring coaxial with the central hub. The turbine rear structure further includes a plurality of guide vanes extending radially between the central hub and the circumferential outer ring, and an intermediate guide vane located in a space defined between adjacent guide vanes. The intermediate guide vane is located closer to one of the guide vanes than the other guide vane.


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    Title :

    Splitter vane


    Publication date :

    2017-12-20


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English





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