Abstract: A compressor rotor includes a rim having airfoils extending radially outwardly therefrom, and a corresponding web and hub extending radially inwardly. A row of curvic coupling teeth extends axially away from one end of the rim. An imperforate support ring extends radially inwardly from the rim end for carrying hoop loads. And, a balance ring extends radially inwardly from the support ring, and includes a balance notch circumferentially splitting the balance ring.

Abstract: A gas turbine nozzle includes a plurality of nozzle segments having a pair of nozzle vanes supported by inner and outer shroud segments. Each inner shroud segment includes a circumferential retention slot and a radial retention slot in generally circumferential alignment and an interlocking tab and slot arrangement at the respective ends to provide engagement between adjacent flange segments. A 360 degree retention ring includes a plurality of circumferential retention tabs and radial retention tabs to engage respective ones of the plurality of flange segments to secure the nozzle segments in a circumferential ring about the outlet of a gas turbine combustor.

Abstract: A gas turbine engine combustor dome assembly includes a dome having a dome eyelet, a mounting ring fixedly joined to the dome around the eyelet, a baffle fixedly joined to the mounting ring, and a carburetor fixedly joined to the mounting ring. The carburetor is joined to the mounting ring for providing a fuel/air mixture through the mounting ring with a predetermined relationship to the baffle for controlling pattern factor. The mounting ring allows for assembly with reduced stackup clearances, and easy disassembly for servicing.