Abstract: A gas turbine engine has a section, such as a compressor section, with at least two spaced apart stator assemblies and an asymmetrical rotor assembly positioned between the spaced apart stator assemblies. The asymmetrical rotor assembly has a rotor array which is asymmetric about at least one diameter of the rotor assembly.

Abstract: A seal assembly for a gas turbine engine includes an annular body and a flow-through tube that extends through the annular body. The flow-through tube includes an upstream orifice, a downstream orifice and a tube body that extends between the upstream orifice and the downstream orifice. The tube body establishes a gradually increasing cross-sectional area between the downstream orifice and the upstream orifice.

Abstract: A seal for a turbine blade in a gas turbine engine has a sealing portion with two subportions, where the subportions are longitudinally offset from one another, so that the seal may provide sealing for adjacent turbine blades having longitudinally offset inner platform surfaces. The offset between the sealing subportions should correspond generally to the offset between the platform surfaces.

Abstract: A damper for a turbine blade in a gas turbine engine includes a main body and may include at least one extended end which is adapted to clear radially inner surfaces of two adjacent blade platforms, to enhance the damping profile of the damper and radial support for a seal. An associated seal for the turbine blade includes supported and sealing portions and may further include a locator that interfaces with a catch structure on the blade to maintain the seal in the proper axial position with respect to the radially inner surfaces of the adjacent platforms. The seal may further include a projection adapted to provide interference with the blade in the event that the damper and seal are installed improperly with respect to each other to prevent such improper assembly.

Abstract: An integral damper and seal for a turbine blade in a gas turbine engine includes a damper portion which contacts the platform and at least one sealing portion, angled radially inward from the damper portion, which makes contact with and seals against the platform.

Abstract: An integrated damper and windage cover 52 has a windage cover portion 56 cantilevered at the upstream end, free of contact with the blade platform 24, 32. The contact portion 54 is rigid and bears against the underside of the blade platform 24, spanning blade platform clearance 50.

Abstract: A rotor blade having axially spaced gussets disposed between a root portion and a platform is disclosed. Various construction details are developed which provide a gusset providing both platform support and damper positioning means. In one particular embodiment, a rotor blade assembly includes a plurality of circumferentially spaced rotor blades having dampers disposed between adjacent blades, wherein each blade includes an axially spaced pair of gussets extending laterally from the rotor blade. The gussets extend from a root portion of the rotor blade to a platform and provide radial support of the platform during rotation of the rotor assembly. The gussets include a curved lateral edge which, during rotation of the rotor assembly, urges the damper away from the root portion of the blade.