Abstract:
A shroud supports one of an inner and an outer trunnion on a variable vane. The shroud is provided by a first and a second axial half. Each of the axial halves is provided by a plurality of circumferentially spaced segments. Circumferential edges are defined on each of the plurality of circumferentially spaced segments. Edges between adjacent ones of the circumferentially spaced segments on the first half are circumferentially offset from the edges on adjacent ones of circumferentially spaced segments of the second half, such that no direct leakage path exists across an axial width of the shroud.
Abstract:
A spline assembly includes a shaft having an outer surface with a shaft spline extending along the outer surface. The spline assembly may further include a hub having an inner surface with a hub spline extending along the inner surface and configured to mate with the shaft spline of the shaft. The spline assembly may further include a spline engagement aid configured to be coupled to the shaft and having an aid spline configured to engage with the hub spline to facilitate alignment of the shaft spline relative to the hub spline.
Abstract:
A variable vane assembly includes a variable vane, a trunnion arranged on one end of the variable vane, an inner bushing configured to receive the trunnion in a press fit relationship, and an outer bushing configured to rotatably receive the inner bushing. A retention feature is configured to retain the trunnion axially with respect to the outer bushing. A gas turbine engine and a method of assembling a variable vane assembly are also disclosed.
Abstract:
A variable area vane arrangement includes a stator vane, a bushing and a vane platform with an aperture. The stator vane rotates about an axis, and includes a shaft that extends along the axis into the aperture. The bushing is connected to the shaft, and is arranged within the aperture between the vane platform and the shaft.
Abstract:
A shroud for a turbomachine stator includes a first portion and a second portion configured to sandwich around at least a portion of a stator vane assembly, a first pin hole defined in the first portion at an angle relative to an axial direction of the turbomachine, and a second pin hole defined in the second portion at the angle of the first portion, wherein the first pin hole is aligned and in communication with the second pin hole to accommodate a pin configured to be seated in the first and second pin holes.
Abstract:
A gas turbine engine includes a compressor section and a nosecone assembly. The compressor section includes an inlet guide vane assembly including an inner shroud, an outer shroud, and an inlet guide vane extending from the inner shroud to the outer shroud. The nosecone assembly is attached to the inner shroud.
Abstract:
A variable area vane arrangement includes a stator vane, a bushing and a vane platform with an aperture. The stator vane rotates about an axis, and includes a shaft that extends along the axis into the aperture. The bushing is connected to the shaft, and is arranged within the aperture between the vane platform and the shaft.