Patent ID: 6942453

Claim:
A turbine nozzle segment of a turbine nozzle assembly to be installed onto a back of a turbine case of an aircraft engine, comprising: a plurality of stator vanes; an arc-like inner band being integrally molded at the inner end of a plurality of the stator vanes; an arc-like outer band being integrally molded at the outer end of a plurality of the stator vanes; an inner platform being formed in the inner band, the inner platform having a flange portion protruding inward at a back end thereof and an inner flow-path face on the outer side thereof; an inner leg being formed on the inner side of the inner platform of the inner band, the inner leg having an arc-like seal support at the inner end thereof; an outer platform being formed in the outer band, the outer platform having an outer flow-path face on the inner side thereof; a forward outer leg being formed on the outer side of the outer platform of the outer band, the forward outer leg having a forward hook being able to fit into an nozzle support hook of the turbine case at the inner end of the forward outer leg; a aft outer leg being formed at the back of the forward outer leg on the outer side of the outer platform; and a hook member being formed at the circumferentially central portion of the back end of the outer platform, wherein an outer lock piece of a assembly fixture for installing the turbine nozzle assembly onto the turbine case can be hooked onto the hook member.