Abstract: A turbine system including a sealing component is presented. The sealing component is positioned in a gap between adjacent turbine components of the turbine system. The sealing component includes a metallic shim including a high-temperature-resistant alloy in a single crystal form. A turbine shroud assembly including the sealing component is also presented.

Abstract: A sealing system for a multi-stage turbine includes multiple first interstage seal subsystems disposed circumferentially about a rotor wheel shaft of the multi-stage turbine and extending axially between a first turbine stage and a second turbine stage of the multi-stage turbine. Each of the first interstage seal subsystems includes multiple near flow path seal segments. The first interstage seal subsystem also includes a forward coverplate disposed axially between a first turbine wheel of the first turbine stage and the near flow path seal segment and an aft coverplate disposed axially between the near flow path seal segment and a second turbine wheel of the second turbine stag. Further, each of the forward coverplate and the aft coverplate extends radially to a first stage bucket and a second stage bucket respectively.

Abstract: A turbomachine and a method of operating the turbomachine are disclosed. The turbomachine includes a stator, a rotor including a rotor bearing face, and a face seal assembly including a first segmented seal ring and a second segmented seal ring. The first segmented seal ring includes a plurality of joints and a first flat-contact surface and the second segmented seal ring includes a plurality of segment ends and a second flat-contact surface. One of the first and second segmented seal rings includes a seal bearing face. The second segmented seal ring is coupled to the first segmented seal ring such that the second flat-contact surface is in contact with the first flat-contact surface. The plurality of segment ends is circumferentially offset from the plurality of joints. The first segmented seal ring is slidably coupled to the stator and defines a face seal clearance between the rotor and seal bearing faces.

Abstract: A turbomachine and a method of operating the turbomachine are disclosed. The turbomachine includes a stator, a rotor including a rotor bearing face, a face seal assembly, a first pressure cavity, and a second pressure cavity. The face seal assembly includes a seal ring including a seal bearing face, a first pressure cavity, and a plurality of isolated hydrostatic ports extending from the first pressure cavity to the seal bearing face. The face seal assembly is slidably coupled to the stator and defines a face seal clearance between the rotor and seal bearing faces. The second and third pressure cavities are defined by the stator, the rotor, and the face seal assembly. The third pressure cavity is disposed downstream of the second pressure cavity with reference to flow of a process fluid along the stator and rotor. The first pressure cavity is isolated from the second and third pressure cavities.

Abstract: A sealing system for a multi-stage turbine includes multiple interstage seal segments disposed circumferentially about a turbine rotor wheel assembly and extending axially between a forward turbine stage and an aft turbine stage. Each of the interstage seal segments includes a forward end portion including an outer seal surface and an inner support face, an aft end portion, including an outer seal surface and an inner support face and a main body portion extending axially from the forward end portion to the aft end. The main body portion includes at least two support webs coupling the outer seal surfaces and the inner support faces. The outer seal surfaces are configured to be retained in a radial direction by a land support on each of a forward and aft stage turbine buckets, such that substantially all the centrifugal load from the multiple interstage seal segments is transferred to the forward and aft stage turbine buckets. A method of assembling the sealing system is disclosed.

Abstract: A turbine blisk is provided. The turbine blisk includes an inner rim, a plurality of adjacent rotor blades extending radially outward from said inner rim, a shroud segment integrally coupled to each of the plurality of adjacent rotor blades, thereby forming a plurality of adjacent shroud segments, and a gap defined between each of the adjacent shroud segments. The gap has a geometry that facilitates interlocking the plurality of adjacent shroud segments when a torsional force is applied to the plurality of adjacent rotor blades.

Abstract: A coated seal slot system for turbomachinery includes a first turbine component comprising a first groove having at least one first coating attached to at least a portion of the first groove of the first turbine component, a second turbine component comprising a second groove having at least one second coating attached to at least a portion of the second groove of the second turbine component. The first and the second turbine components are disposable adjacent to each other with the first groove having the first coating and the second groove having the second coating together forming a coated seal slot extending across a gap between the first turbine component and the second turbine component. A seal is disposable in the coated seal slot and extendable across the gap between the first and the second turbine components and engageable with the first coating and the second coating to inhibit leakage of gas through the gap.

Abstract: A turbine system including a sealing component is presented. The sealing component is positioned in a gap between adjacent turbine components of the turbine system. The sealing component includes a metallic shim including a high-temperature-resistant alloy in a single crystal form. A turbine shroud assembly including the sealing component is also presented.

Abstract: A turbomachine and a method of operating the turbomachine are disclosed. The turbomachine includes a stator, a rotor including a rotor bearing face, a face seal assembly, a first pressure cavity, and a second pressure cavity. The face seal assembly includes a seal ring including a seal bearing face, a first pressure cavity, and a plurality of isolated hydrostatic ports extending from the first pressure cavity to the seal bearing face. The face seal assembly is slidably coupled to the stator and defines a face seal clearance between the rotor and seal bearing faces. The second and third pressure cavities are defined by the stator, the rotor, and the face seal assembly. The third pressure cavity is disposed downstream of the second pressure cavity with reference to flow of a process fluid along the stator and rotor. The first pressure cavity is isolated from the second and third pressure cavities.

Abstract: A turbomachine and a method of operating the turbomachine are disclosed. The turbomachine includes a stator, a rotor including a rotor bearing face, and a face seal assembly including a first segmented seal ring and a second segmented seal ring. The first segmented seal ring includes a plurality of joints and a first flat-contact surface and the second segmented seal ring includes a plurality of segment ends and a second flat-contact surface. One of the first and second segmented seal rings includes a seal bearing face. The second segmented seal ring is coupled to the first segmented seal ring such that the second flat-contact surface is in contact with the first flat-contact surface. The plurality of segment ends is circumferentially offset from the plurality of joints. The first segmented seal ring is slidably coupled to the stator and defines a face seal clearance between the rotor and seal bearing faces.

Abstract: A turbine system including a sealing component is presented. The sealing component includes a ceramic material. The ceramic material includes grains having an average grain size of less than 10 microns. A turbine shroud assembly including the sealing component is also presented.

Abstract: Seal assemblies for reducing leakage between components of turbomachinery include a metallic shim, at least a pair of non-metallic end blocks, and ceramic fiber positioned between the shim and the end blocks. The shim may be mechanically coupled with the end blocks such that the metallic shim, end blocks and ceramic fiber are coupled. The end blocks account for misalignment of turbine components by ensuring sealing engagement of the seal to the components. The end blocks may be a ceramic or glass material, and the ceramic fiber may be a high temperature woven ceramic fiber. The ceramic fiber and/or the end blocks protect the metallic shim from reaching harmful temperatures during use of the seal, such as use in high temperature turbines including CMC components.

Abstract: Snap in annular spring seal including continuous or split full 360 degree ring having radially outer second seal end spaced outwardly of a radially inner first end of the ring and axial biasing means urging first and second seal ends apart. Biasing means may include an axially aftwardly opening conical section connecting first and second seal ends and second seal end having outer aftwardly opening V-shaped cross-sectional bend or circular cross-sectional bend. Spring seal may extend radially and circumferentially between and in sealing engagement with first and second annular turbine components. First end may be spring-loaded and removably secured in U-shaped or V-shaped slot of turbine component. Slot may include symmetrical inner U-shaped bent first seal end including annular substantially parallel or non-parallel forward and aft legs connected by semi-circular cross-sectional bend. Seal may include bowed section connecting circular seal ends.

Abstract: A coated seal slot system for turbomachinery includes a first turbine component comprising a first groove having at least one first coating attached to at least a portion of the first groove of the first turbine component, a second turbine component comprising a second groove having at least one second coating attached to at least a portion of the second groove of the second turbine component. The first and the second turbine components are disposable adjacent to each other with the first groove having the first coating and the second groove having the second coating together forming a coated seal slot extending across a gap between the first turbine component and the second turbine component. A seal is disposable in the coated seal slot and extendable across the gap between the first and the second turbine components and engageable with the first coating and the second coating to inhibit leakage of gas through the gap.

Abstract: The present application provides slot seals for reducing leakages between adjacent components of turbomachinery. The seals may include a metallic shim and a coating overlying the metallic shim. The coating may be a metallic coating, a glass coating, an enamel coating or a ceramic coating. The coating may form an outer surface of the seal for engagement with seal slot surfaces of a seal slot of a turbomachine. The coating may be operable to conform to surface irregularities of the seal slot surfaces and remain coupled to the metallic shim at a predefined operating temperature and a predefined operating pressure to reduce leakage past the seal and thereby between the components. The coating may be configured to flow into depressions formed by the surface irregularities of the seal slot surfaces and remain coupled to the metallic shim at the predefined operating temperature and the predefined operating pressure.

Abstract: The present application provides composite seals for reducing leakages between adjacent components of turbomachinery. The composite seals may include a metallic shim, a metallic support structure and a ceramic, glass or enamel coating. The shim and the support structure may be bonded or fused together. The support structure may include internal voids or gaps, and the coating may be applied to the shim and the support structure such that the coating is provided within the voids or gaps of the support structure, between portions of the support structure and the shim, and substantially over the outer surface of the support structure. The support structure may thereby provide a mechanical attachment between the shim and the coating. In use, the coating provides thermal and/or chemical insulation to the metallic shim and the support structure of the seal.

Abstract: Seal assemblies for reducing leakage between components of turbomachinery are provided. The seals may include a metallic shim, at least a pair of non-metallic end blocks, and ceramic fiber positioned between the shim and the end blocks. The shim may be mechanically coupled with the end blocks such that the metallic shim, non-metallic end blocks and ceramic fiber are coupled. The end blocks may be configured to account for misalignment of turbine components by ensuring sealing engagement of the seal to the components. The end blocks may be made from a ceramic or glass material, and the ceramic fiber may be a high temperature woven ceramic fiber. The ceramic fiber and/or the end blocks may protect the metallic shim from reaching potentially harmful temperatures during use of the seal, such as use in high temperature turbines including CMC components.

Abstract: A sealing system for a multi-stage turbine includes multiple interstage seal segments disposed circumferentially about a turbine rotor wheel assembly and extending axially between a forward turbine stage and an aft turbine stage. Each of the interstage seal segments includes a forward end portion including an outer seal surface and an inner support face, an aft end portion, including an outer seal surface and an inner support face and a main body portion extending axially from the forward end portion to the aft end. The main body portion includes at least two support webs coupling the outer seal surfaces and the inner support faces. The outer seal surfaces are configured to be retained in a radial direction by a land support on each of a forward and aft stage turbine buckets, such that substantially all the centrifugal load from the multiple interstage seal segments is transferred to the forward and aft stage turbine buckets. A method of assembling the sealing system is disclosed.

Abstract: A sealing system for a multi-stage turbine includes multiple first interstage seal subsystems disposed circumferentially about a rotor wheel shaft of the multi-stage turbine and extending axially between a first turbine stage and a second turbine stage of the multi-stage turbine. Each of the first interstage seal subsystems includes multiple near flow path seal segments. The first interstage seal subsystem also includes a forward coverplate disposed axially between a first turbine wheel of the first turbine stage and the near flow path seal segment and an aft coverplate disposed axially between the near flow path seal segment and a second turbine wheel of the second turbine stag. Further, each of the forward coverplate and the aft coverplate extends radially to a first stage bucket and a second stage bucket respectively.

Abstract: A rotor assembly is provided. The rotor assembly includes a rotor shaft and at least one blisk integrally formed with the rotor shaft. The at least one blisk includes an inner rim extending circumferentially about the rotor shaft, and a plurality of blades extending radially outward from the inner rim, wherein the rotor shaft and the at least one blisk are defined from a single billet of material.