Abstract: A method of forming a stator assembly which adapts the stator assembly to receive a roller assembly in a rotary machine is disclosed. Various details of the method are developed which may be used for the manufacture, the modification, and the repair of the stator assembly. The method includes forming a liner for the stator assembly independently of the stator assembly; and, disposing the liner in the stator assembly to adapt the stator assembly to receive the roller assembly.

Abstract: A rotary machine (10) having rotor elements (54-66), (114) and seal lands (86, 112) is disclosed. Various construction details are developed for facilitating assembly of the machine. In one embodiment clearances are established between rotor blades (66) and the seal land (86) which enable assembly of the components and provide for acceptable clearances at a steady-state operative condition of the engine.

Abstract: A method for assembling a rotary machine, such as a gas turbine engine, having rotor elements and associated seal lands. Various details of the method are developed for facilitating assembly of the rotary machine that are, in one embodiment, applicable to installing fan blades to a fan rotor disk while rotating the rotor disk by hand. In one embodiment, a lubricant is applied to a seal land to reduce friction between the rotor element and the seal land during assembly.

Abstract: A housing assembly for a turbine engine has a housing which is adapted to cooperate with an adjacent valve ring assembly. The housing has a plurality of passages for working medium gases which extend radially through the housing and are circumferentially spaced in the housing. The valve ring modulates the flow through the passages. A plurality of flanges extend axially and circumferentially from the housing. Each flange has a track opening which receives a liner and a roller assembly having a bearing surface. The roller assembly in combination with the liner guides the valve ring assembly. The liner and the housing have different physical characteristics, such as a different rate of thermal expansion and different spring rate characteristics which accommodate differences in thermal growth between the liner and the housing.

Abstract: A stator assembly of an axial flow rotary machine has a compressor bleed system. The compressor bleed system includes an axially translating valve ring. The valve ring is movable between an open and closed position and includes guide roller and guide track having guide walls which urge the valve ring axially against resilient seal members. The track is contoured to provide a mechanical advantage when the valve ring is moved to the closed position. A liner is adapted to engage the stator assembly to form the track.

Abstract: An actuator assembly for imparting non-proportional tangential displacement (22b) to a plurality of unison rings (16b, 16c) disposed about the exterior of a compressor case (10b) is provided. The assembly includes a linear drive component (26b) mounted on trunnions (74, 76) and supported by a frame 48. The drive component (26b) imparts a rotating motion to a crankshaft 70 which in turn drives the unison rings (16b, 16c) via the respective crank arms (42b, 42c) and pushrod (30b, 30c) linkages. Radial loading of the compressor case (10b) is avoided by aligning both the pushrod (30b) and the elongated frame first end (50) tangential to the compressor case (10b).

Abstract: The bore of the compressor of a gas turbine engine is selectively heated by mid-stage compressor bleed air and a higher stage compressor bleed air utilizing a two position valve integral with the engine case and manifold with provision for fail-safe in the lower temperature bleed air position.

Abstract: The bore of the compressor for a gas turbine engine is heated by selectively bleeding compressor air from downstream stages so that heating only occurs at discreet times during the engine operating envelope. The bled air is admitted into the bore at the mid-stage station of the compressor wherein the compressor disks are scrubbed so as to expand and close the gap between the outer air seal and tips of the compressor blades during cruise of the aircraft and prevented from heating the disks during the high powered operations of the engine.