Abstract: A system includes a casing alignment system configured to align an inner wall with an outer wall of a multi-wall casing of a turbomachine having a rotor. The casing alignment system includes a first alignment positioner configured to bias a first lip of the inner wall in a direction of rotation of the rotor disposed within the multi-wall casing. The alignment positioner may include a spring, a fluid-driven alignment positioner, an electric-driven alignment positioner, or a combination thereof. The alignment positioner may be configured to bias the first lip within a first recess adjacent a first flanged coupling between first and second wall sections of the outer wall.

Abstract: A gas turbomachine includes a compressor portion, a turbine portion operatively connected to the compressor portion, and a combustor assembly fluidically connected to each of the compressor portion and the turbine portion. A turbine casing includes a body having an outer surface and an inner surface. A clearance control system includes a plurality of fluidically connected fluid channels extending through the turbine casing. The plurality of fluidically connected fluid channels includes a first fluid channel configured to direct a fluid flow in a first axial direction, a circumferential fluid channel configured to direct the fluid flow in a circumferential direction, and a second fluid channel configured to direct the fluid flow in a second axial direction substantially opposite the first axial direction. The first fluid channel includes a first outlet passing through the inner surface, and the second fluid channel including a second outlet passing through the inner surface.

Abstract: Embodiments of the present disclosure include a bearing housing of a turbine, wherein the bearing housing is configured to support a shaft of the turbine, and the bearing housing comprises at least one bearing housing ear configured to transfer a load of the bearing housing to an inlet housing of the turbine through a horizontal center line of the bearing housing.

Abstract: A gas turbomachine includes a compressor portion, a turbine portion operatively connected to the compressor portion, and a combustor assembly fluidically connected to each of the compressor portion and the turbine portion. A turbine casing includes a body having an outer surface and an inner surface. A clearance control system includes a plurality of fluidically connected fluid channels extending through the turbine casing. The plurality of fluidically connected fluid channels includes a first fluid channel configured to direct a fluid flow in a first axial direction, a circumferential fluid channel configured to direct the fluid flow in a circumferential direction, and a second fluid channel configured to direct the fluid flow in a second axial direction substantially opposite the first axial direction. The first fluid channel includes a first outlet passing through the inner surface, and the second fluid channel including a second outlet passing through the inner surface.

Abstract: Embodiments of the present disclosure include a bearing housing of a turbine, wherein the bearing housing is configured to support a shaft of the turbine, and the bearing housing comprises at least one bearing housing ear configured to transfer a load of the bearing housing to an inlet housing of the turbine through a horizontal center line of the bearing housing.

Abstract: A method of operating a turbine engine including coupling a heating assembly to the turbine engine for selectively heating a compressor casing. A sensor transmits a first monitoring signal indicative of a speed of a rotor assembly to a controller. The controller determines whether the turbine engine is operating in a first operating mode based at least in part on the received first monitoring signal, wherein during the first operating mode a minimum clearance distance is defined between the rotor assembly and the compressor casing. The compressor casing of the turbine engine is heated to increase the clearance distance between the compressor casing and the rotor assembly, if the turbine engine is in the first operating mode.