Patent ID: 8449249

Claim:
A turbine nozzle segment, wherein a plurality of said turbine nozzle segments provide for forming an associated turbine nozzle when circumferentially disposed in cooperative relationship with one another about a central axis, said turbine nozzle segment comprising: a. an inner endwall portion; b. an outer endwall portion, wherein said inner and outer endwall portions are each generally curved about said central axis, and said outer endwall portion is generally outside said inner endwall portion relative to said central axis; c. a first portion of a first bounding nozzle vane, wherein said first portion of said first bounding nozzle vane extends between said inner and outer endwall portions at a first azimuthal boundary of said turbine nozzle segment; d. a second portion of a second bounding nozzle vane, wherein said second portion of said second bounding nozzle vane extends between said inner and outer endwall portions at a second azimuthal boundary of said turbine nozzle segment, and said first and second azimuthal boundaries are azimuthally displaced from one another relative to said central axis; e. at least one annular-segment passage, wherein said at least one annular-segment passage is bounded by said inner and outer endwall portions, one said at least one annular-segment passage is bounded by said first portion of said first bounding nozzle vane and one said at least one annular-segment passage is bounded by said second portion of said second bounding nozzle vane, a first external boundary of said first portion of said first bounding nozzle vane is shaped so as to provide for mating with a second external boundary of said second portion of said second bounding nozzle vane when said first portion of said first bounding nozzle vane is part of said turbine nozzle segment and said second portion of said second bounding nozzle vane is part of a first other turbine nozzle segment, or when said second portion of said second bounding nozzle vane is part of said turbine nozzle segment and said first portion of said first bounding nozzle vane is part of a second other turbine nozzle segment, and said first portion of said first bounding nozzle vane, said second portion of said second bounding nozzle vane and said first and second external boundaries are shaped so that said second portion of said second bounding nozzle vane of said first other turbine nozzle segment and said first portion of said first bounding nozzle vane of said turbine nozzle segment when azimuthally abutted against one another constitute said first bounding nozzle vane, and said first portion of said first bounding nozzle vane of said second other turbine nozzle segment and said second portion of said second bounding nozzle vane of said turbine nozzle segment when azimuthally abutted against one another constitute said second bounding nozzle vane, wherein each said first and second other turbine nozzle segment is shaped substantially the same as said turbine nozzle segment.