A turbine engine has: a compressor (30); a combustor (32); a turbine (34), a gas flowpath (52) passing consecutively through the compressor (30), combustor (32), and turbine (34); and inlet member (140) along the gas flowpath (502) upstream of the compressor (30). The inlet member (140) includes the unitarily-formed single piece combination of: a three dimensional (3D) lattice portion (260); and a nose cap body (202) surrounding the lattice portion (260).


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    Titel :

    ATTRITABLE ENGINE ADDITIVELY MANUFACTURED INLET CAP


    Weitere Titelangaben:

    GENERATIV GEFERTIGTE EINLASSKAPPE EINER GASTURBINE
    CAPUCHON D'ADMISSION DE TURBINE À GAZ FABRIQUÉ DE MANIÈRE ADDITIVE


    Beteiligte:
    BINEK LAWRENCE A (Autor:in) / BOYER JESSE R (Autor:in) / BUTCHER EVAN J (Autor:in) / WINTER MICHAEL (Autor:in) / GARCIA JESUS A (Autor:in) / JACKSON SEAN R (Autor:in)

    Erscheinungsdatum :

    2023-01-04


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B33Y ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING , Additive (generative) Fertigung, d. h. die Herstellung von dreidimensionalen [3D] Bauteilen durch additive Abscheidung, additive Agglomeration oder additive Schichtung, z. B. durch 3D- Drucken, Stereolithografie oder selektives Lasersintern / B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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