Abstract: A casing includes an inner shell and an outer shell that surrounds the inner shell and comprises a plurality of inflection points. An annular flange is between the inner shell and the outer shell, and a plurality of joints attach the inner shell to the annular flange. A connector is between the annular flange and the outer shell at each of the plurality of inflection points. A method for assembling a casing includes joining a plurality of curved sections to one another to generally define an arcuate inner shell and surrounding the arcuate inner shell with an outer shell. The method further includes attaching the arcuate inner shell to an annular flange at first attachment points and connecting the annular flange to the outer shell at second attachment points spaced approximately equidistantly from the first attachment points.

Abstract: A turbine diffuser is disclosed. The turbine diffuser includes a diffuser segment having a forward end and an aft end with a flange disposed at the aft end of the diffuser segment. The diffuser segment is joinable to an adjacent diffuser segment via the flange, which includes a seal retainer that is securedly connectable in a radial direction with a seal.

Abstract: A system is provided that includes a first turbine alignment component for a turbine engine; and a shim comprises a metal foam. The shim mounts between a first surface of the first turbine alignment component and a second surface of a second turbine alignment component.

Abstract: A turbomachine includes a rotor assembly including a wheel member. The wheel member includes a first portion that extends to a second portion through an intermediate portion. The intermediate portion partially defines a first wheel space and a second wheel space. The wheel member further includes a rotor inertia belt member arranged at the second portion. The rotor inertia belt member includes an extraction air cavity. The extraction air cavity includes an inlet, a first plurality of extraction air passages each including an inlet section and an outlet section, the outlet section leading into the first wheel space, and a second plurality of extraction air passages each including an inlet portion and an outlet portion, the outlet portion leading into the second wheel space.

Abstract: An apparatus to support a rotor of a turbine engine disposed upon a support surface is disclosed. The apparatus includes a housing, a rotor support bearing disposed within the housing, and a support leg in operable communication with the housing and in direct structural connection with the support surface.

Abstract: In a rotary machine such as a gas turbine, torque is transmitted between adjacent components of a rotor. To enable effective transmission of torsional and radial loads, a plurality of mating surfaces are distributed on an interfacing surface of a disk of the rotor. The mating surfaces include at least one first mating surface and at least one second mating surface. Each first mating surface is angularly offset relative to a radial line by a first angle, and each second mating surface is angularly offset relative to the radial line by a second angle. The second angle is opposite in direction from the first angle from the radial line.

Abstract: A method is disclosed for improving a turbine's thermal response during transient and steady state operating conditions in which the flow of cooling fluid in the turbine's casing is caused to be asymmetrical relative to the horizontal and vertical symmetry planes of the casing so that the turbine's cooling symmetry planes are rotated relative to its geometric symmetry planes and thereby the heat transfer at locations in the casing with increased mass is increased.

Abstract: A system to support a rotor and a stator of a rotating machine disposed upon a support base, the system including at least one support leg in operable communication with a bearing of the rotor and with the support base; and at least one strut in operable communication with the at least one support leg and with the stator.

Abstract: A turbomachine includes a rotor assembly including a wheel member. The wheel member includes a first portion that extends to a second portion through an intermediate portion. The intermediate portion partially defines a first wheel space and a second wheel space. The wheel member further includes a rotor inertia belt member arranged at the second portion. The rotor inertia belt member includes an extraction air cavity. The extraction air cavity includes an inlet, a first plurality of extraction air passages each including an inlet section and an outlet section, the outlet section leading into the first wheel space, and a second plurality of extraction air passages each including an inlet portion and an outlet portion, the outlet portion leading into the second wheel space.

Abstract: A retaining system is provided for circumferential entry rotor dovetails inserted into dovetail slot in a rotor. A plurality of rotor blade dovetails are circumferentially slidable into and along the dovetail slot, with each rotor blade dovetail having a neck and a pair of oppositely oriented lobes. A plurality of rail segments are circumferentially slid into channels in the dovetail slot between the dovetail lobes and the respective disk hoops. The rail segments define a first pressure face that engages against an outward pressure face of the dovetail lobes, and a second pressure face that engages against an inward pressure face of the respective disk hoop component.

Abstract: An apparatus to support a rotor of a turbine engine disposed upon a support surface is disclosed. The apparatus includes a housing, a rotor support bearing disposed within the housing, and a support leg in operable communication with the housing and in direct structural connection with the support surface.

Abstract: A method operates a gas turbine that includes a compressor section, a turbine section and an extraction cooling system. The method includes monitoring an operation of the gas turbine, directing a cooling air flow through the extraction cooling system from the compressor section to the turbine section in response to normal operation of the gas turbine, and directing a warming air flow through the extraction cooling system to the compressor section and the turbine section in response to shutdown of the gas turbine.

Abstract: A method is disclosed for improving a turbine's thermal response during transient and steady state operating conditions in which the flow of cooling fluid in the turbine's casing is caused to be asymmetrical relative to the horizontal and vertical symmetry planes of the casing so that the turbine's cooling symmetry planes are rotated relative to its geometric symmetry planes and thereby the heat transfer at locations in the casing with increased mass is increased.

Abstract: An inner shell for a rotating machine including at least one segment; and at least one complementary segment in operable communication with the at least one segment, the segments forming a support structure for a shroud ring; wherein the at least one segment and the at least one complementary segment are individually moved to change a set of dimensions defined by the at least one segment and the at least one complementary segment. A method for controlling a dimension of the shroud ring in a rotating machine is also disclosed.

Abstract: A gas turbine including a casing and a shroud ring, the gas turbine including an attachment device rigidly attached to the casing and at least one of the shroud ring and a duct attached to the shroud ring, wherein the device allows the shroud ring to expand and contract independent of the casing and provides limited net axial growth of the shroud ring.

Abstract: A turbine diffuser is disclosed. The turbine diffuser includes a diffuser segment having a forward end and an aft end with a flange disposed at the aft end of the diffuser segment. The diffuser segment is joinable to an adjacent diffuser segment via the flange, which includes a seal retainer that is securedly connectable in a radial direction with a seal.

Abstract: Disclosed herein is a rotor to stator alignment method. The alignment method includes, positioning a plurality of eccentric rings between the rotor and a stator, and rotating at least one of the plurality of eccentric rings relative to the stator thereby reducing eccentricity of the rotor with the stator.