Abstract: A system for passively varying an axial position of an inner casing of a gas turbine pursuant to changing pressure in a flowpath during transient engine operation. The system may include: a connection assembly slidably connecting the inner casing to the outer casing for axial movement of the inner casing between a first position and a second position; means for pressurizing the annulus relative to a flowpath pressure; biasing means for axially preloading the inner casing toward the first position; and an inner casing receiving surface configured to receive a pressure in the annulus for axially loading the inner casing in opposition to the axial preload of the biasing means.

Abstract: A gas turbine engine that includes: a flowpath defined through one of a compressor and a turbine; an inner casing defining an axially tilted outboard boundary of the flowpath, which, relative to the axial tilt, defines a converging direction in which the flowpath converges and a diverging direction in which the flowpath diverges; a row of rotor blades having outer tips that oppose the outboard boundary across a gap clearance defined therebetween; an outer casing concentrically arranged about the inner casing so to form an annulus therebetween; and a connection assembly that slidably connects the inner casing to the outer casing and includes a biasing means for axially preloading the inner casing in the converging direction.

Abstract: A piping assembly and a method for connecting an inner shell and an outer shell in a turbine system are disclosed. The piping assembly includes an inner fitting for connection to the inner shell and an outer fitting for connection to the outer shell. The piping assembly further includes an attenuation member extending between the inner fitting and the outer fitting and comprising an attenuation curve. The attenuation curve permits movement of the attenuation member in at least one of a longitudinal direction, a radial direction, or a tangential direction.

Abstract: A system for supporting a turbine nozzle includes an inner barrel having a forward end, an aft end and an outer surface that extends between the forward end and the aft end. A first fitting that extends through the outer surface is defined within the inner barrel. The system further includes a nozzle support ring that defines a second fitting that is complementary to the first fitting defined within the inner barrel.

Abstract: A turbine assembly is provided. The turbine assembly includes an inner turbine casing and an outer turbine casing radially outward from the inner turbine casing, the outer turbine casing including an aperture extending therethrough and a support assembly extending through the aperture, the support assembly externally adjustable outside of the outer turbine casing to adjust the inner turbine casing relative to the outer turbine casing.

Abstract: An alignment assembly for mounting and aligning an inner shell within an outer shell is disclosed. The alignment assembly generally includes a first bushing and a second bushing configured to be received within at least one of an arm extending radially between the inner and outer shells and a boss of the outer shell. The first bushing may generally have an eccentric configuration and the second bushing may include an eccentric portion extending within the first bushing. Additionally, the alignment assembly may include a connection member extending within at least one of said first bushing and said second bushing.

Abstract: In certain embodiments of the present disclosure, a turbine casing assembly is described. The turbine casing assembly includes an inner casing and an outer casing surrounding the inner casing. The outer casing has a first outer casing section and a second outer casing section that join together along a flange. A bolt extends through the flange and joins together the first outer casing section and the second outer casing section. The turbine casing assembly further includes a pin. The pin has a segment defining an opening therethrough. The pin extends through the inner casing and the outer casing and supports the inner casing relative to the outer casing. The bolt passes through the opening defined by the pin.

Abstract: A counter weight for installing and removing a lower portion of an inner casing of a turbine section generally includes a semi-annular main body having a first radially extending mating surface and a second radially extending mating surface. A radial gear rack extends radially outward from the main body. The radial gear rack includes a primary segment that extends a first angular distance between the first radially extending mating surface and the second radially extending mating surface of the main body. A secondary segment of the radial gear rack extends a second angular distance from the second radially extending mating surface of the main body. The secondary segment defines an at least partially linear inner surface and an outer arcuate surface.

Abstract: A counter weight for installing and removing a lower portion of an inner casing of a turbine section generally includes a semi-annular main body having a first radially extending mating surface and a second radially extending mating surface. A radial gear rack extends radially outward from the main body. The radial gear rack includes a primary segment that extends a first angular distance between the first radially extending mating surface and the second radially extending mating surface of the main body. A secondary segment of the radial gear rack extends a second angular distance from the second radially extending mating surface of the main body. The secondary segment defines an at least partially linear inner surface and an outer arcuate surface.

Abstract: A deformable fastener assembly for use with a gas turbine engine. The deformable fastener may be used to fasten a component of the gas turbine that is subjected to high temperatures and thermal deformation, such as an impingement sleeve assembly, to a rigid portion, such as the inner turbine shell of the gas turbine engine. The deformable fastener assemblies may permit components to be fastened to a rigid portion of the gas turbine with a consistent load input to permit frictional transient sliding of the component relative to the rigid portion of the gas turbine engine.

Abstract: Thermal control is provided for a gas turbine casing by supplying thermal control gas from a compressor to a space between an outer casing and an inner casing, and transferring the thermal control gas from the space through the opening in the inner casing via a plurality of holes defined through a plate attached to an outer surface of the inner casing. The holes are arranged with a predetermined non-uniform distribution corresponding to a desired preferential impingement pattern for providing non-uniform heat transfer. A gas turbine thermal control assembly includes structure providing preferential heat transfer from the inner casing during operation of the gas turbine via a thermal control gas flow path from radially outside of the inner casing into the interior of the gas turbine.

Abstract: A device for directing gas impingement to an inner casing of a gas turbine may include a plate configured for attachment to the outer surface of the inner casing. The plate has a first surface opposing the inner casing when the plate is attached to an area of the inner casing and a second surface opposite the first surface. The plate defines a plurality of holes through the plate from the first surface to the second surface. The holes are arranged with a predetermined non-uniform distribution in the plate corresponding to a desired preferential impingement pattern for providing non-uniform heat transfer from the area during operation of the gas turbine so as to control temperature of the inner casing across the area. Various options and modifications are possible. Related gas turbine assemblies are also disclosed.

Abstract: A first adjustable stop on a jack member selectively adjusts an incline stop gap while a second adjustable stop on a support element selectively adjusts a decline stop gap. Stop surfaces on the first adjustable stop and the support element may define the incline stop gap, while stop surfaces on the second adjustable stop and the first adjustable stop may define the decline stop gap. A number of turns of a stop needed to effect a desired of adjustment may be determined using a pitch, lead, and/or number of starts of threads used to mount the stops.

Abstract: A floating seal assembly for sealing two static parts is disclosed. Each static part has an opposing groove, and the opposing grooves define a seal cavity. Floating seal assembly includes a floating circumferential seal having a middle portion and opposing end portions, each opposing end portion is positioned within a groove in one of the static parts, wherein each end portion has a curved side facing a low pressure side of the seal cavity. The floating seal assembly according to embodiments of the invention is pressure driven in that each curved side of the end portions is configured to engage a low pressure side of the seal cavity in response to a pressure differential across the sealing cavity reaching a threshold value.

Abstract: A method and system adapted for removing one or more shells from an assembly of multiple annular shells, for example, turbine shells of a gas turbine engine. The method includes removing an upper shell positioned in an upper position relative to a lower shell of the assembly of multiple annular shells, and then positioning and securing a counterweight in the upper position and securing the counterweight to the lower shell as a replacement for the upper shell in the upper position. The counterweight and the lower shell are then rotated in unison until the lower shell is in the upper position and the counterweight is in a lower position previously occupied by the lower shell. Thereafter, the lower shell can be removed from the assembly.

Abstract: A method and apparatus for rolling and aligning a casing of a gas turbine is disclosed. At least one jack having a roller at one end is positioned at a location to couple the roller to the casing. The casing is rolled within the turbine by rolling over the roller of the at least one jack. The roller is moved relative to the at least one jack to align the casing within the turbine.

Abstract: The present application describes a locking spacer assembly for use with a groove in a rotating disk. The locking spacer assembly may include a locking spacer with a leg and a wedge tool in contact with the leg so as to pull the leg inward and into the groove.

Abstract: A seal for a turbine casing is provided. The turbine casing includes a plurality of sections joined at flanges provided on each section. Each flange includes a bore and a counterbore. The seal comprises a compression sleeve seal having a length that is greater than a counterbore-to-counterbore length of two flanges; a fastener configured to extend through the compression sleeve seal; and a nut threadable on each end of the fastener. The compression sleeve seal is compressible between each flange and each nut to create a first seal and is radially extensible to create a second seal against each bore.

Abstract: A turbine casing includes a plurality of arc-shaped segments having a flange at each side end to connect to a flange of an adjacent arc-shaped segment. The flange extends outward from an outer surface of each arc-shaped segment and extends along the outer surface in a front-to-rear direction. Each arc-shaped segment has a portion of the outer surface that is co-linear with the flange in a front-to-rear direction that does not include the flange.

Abstract: A turbomachine includes an inner casing component having a first end that extends to a second end and a seal member. An outer casing component is coupled to the inner casing component. The annular outer casing component includes a first end portion that extends to a second end portion and a seal element that aligns with the seal member of the annular inner casing component to form a seal passage. A seal is arranged in the seal passage. The seal includes a first end section that extends to a second end section through an intermediate zone. The first end section includes a recessed portion and the second end section includes a connecting portion. The connecting portion is configured and disposed to nest within the recessed portion to form a substantially continuous seal.