Abstract: A turbine shroud assembly includes a carrier segment, a blade track segment, and a locating feature. The carrier segment includes an outer wall, a first flange that extends radially inward from the outer wall, and a second flange axially spaced apart from the first flange and extending radially inward from the outer wall. The blade track segment includes a shroud wall and a first attachment flange that extends radially outward from the shroud wall. The locating feature extends axially forward from the second flange of the carrier segment to engage the first attachment flange of the blade track segment to axially locate the blade track segment relative to the carrier segment.

Abstract: A turbine shroud assembly includes a carrier segment, a blade track segment, and a mount assembly. The carrier segment includes an outer wall, a first flange that extends radially inward from the outer wall, and a second flange axially spaced apart from the first flange and extending radially inward from the outer wall. The blade track segment includes a shroud wall and an attachment feature that extends radially outward from the shroud wall. The mount assembly includes a pin that extends axially into the second flange, through the attachment feature, and into the first flange so as to couple the blade track segment to the carrier segment and a pin retention plug that is press fit into the second flange axially aft of the pin to block removal of the pin through the second flange.

Abstract: A turbine shroud assembly for use with a gas turbine engine includes a first shroud segment, a second shroud segment, and a damping strip seal assembly. The first shroud segment has a first carrier segment arranged circumferentially at least partway around a central axis and a first blade track segment supported by the first carrier segment. The second shroud segment is arranged circumferentially adjacent the first shroud segment. The damping strip seal assembly includes a body segment and a damping segment that extends along a curvilinear path.

Abstract: A turbine shroud assembly adapted for use with a gas turbine engine includes a shroud segment. The shroud segment includes a heat shield, an attachment flange, and a multi-layer coating. The heat shield extends circumferentially partway around the axis to define a portion of gas path for the gas turbine engine. The attachment feature extends radially outward from the heat shield. The multi-layer coating is applied to different surfaces of the heat shield and the attachment feature of the shroud segment.

Abstract: An assembly adapted for use in a gas turbine engine includes a blade track segment, a carrier segment, and a retainer. The blade track segment defines a portion of a gas path of the gas turbine engine. The carrier segment supports the blade track segment to locate the blade track segment radially outward of the axis. The retainer couples the blade track segment to the carrier segment. The carrier segment may include a plurality of impingement passageways to conduct cooling air to the blade track segment.

Abstract: A turbine assembly adapted for use with a gas turbine engine includes a turbine shroud assembly and a turbine vane. The turbine shroud assembly includes a blade track segment arranged circumferentially at least partway around an axis of the gas turbine engine, a carrier segment arranged circumferentially at least partway around the axis, and a mount assembly configured to couple the blade track segment to the carrier segment. The turbine vane is located axially aft of the turbine shroud assembly and helps retain the mount assembly in place.

Abstract: An assembly adapted for use in a gas turbine engine includes a blade track segment, a carrier segment, and a retainer. The blade track segment defines a portion of a gas path of the gas turbine engine. The carrier segment supports the blade track segment to locate the blade track segment radially outward of the axis. The retainer couples the blade track segment to the carrier segment. The carrier segment may include a plurality of impingement passageways to conduct cooling air to the blade track segment.

Abstract: A turbine shroud assembly adapted for use with a gas turbine engine includes a shroud segment. The shroud segment includes a heat shield, an attachment flange, and a multi-layer coating. The heat shield extends circumferentially partway around the axis to define a portion of gas path for the gas turbine engine. The attachment feature extends radially outward from the heat shield. The multi-layer coating is applied to different surfaces of the heat shield and the attachment feature of the shroud segment.

Abstract: A turbine assembly includes a turbine case, a vane assembly, and a locating plate. The vane assembly includes a first vane and an outer platform arranged on a radially outer end of the first vane, the outer platform including a first anti-rotation protrusion extending radially outwardly away from a radially outwardly-facing surface of the outer platform. The locating plate is radially outside of the vane assembly and includes a main wall and two anti-rotation extensions extending radially inwardly. The first anti-rotation protrusion of the vane assembly is arranged to engage with one of the anti-rotation extensions so as to block circumferential movement of the vane assembly relative to the locating plate.

Abstract: A turbine assembly adapted for use with a gas turbine engine includes a turbine shroud assembly and a turbine vane. The turbine shroud assembly includes a carrier segment arranged circumferentially at least partway around an axis and a blade track segment supported by the carrier segment to locate the blade track segment radially outward of the axis. The turbine vane is located axially forward of the turbine shroud assembly and cooperates with the turbine shroud assembly to form a tortuous flow path therebetween.

Abstract: A turbine assembly includes a turbine case, a turbine shroud assembly including a carrier segment, and a locating plate. The locating plate is coupled with the turbine case axially forward of the carrier segment to block axially forward movement of the carrier segment and prevent separation of the carrier segment from the turbine case. The locating plate includes a main wall, a raised portion extending upwardly a first radial distance, and two circumferentially spaced apart extensions extending upwardly a second radial distance. The second radial distance is greater than the first radial distance such that, in a first arrangement, only the extensions contact the turbine case and such that, in a second arrangement, the raised portion is pulled toward the turbine case via a fastener so as to contact the turbine case in addition to the extensions.

Abstract: A turbine shroud assembly adapted for use with a gas turbine engine includes a shroud segment. The shroud segment includes a heat shield, an attachment flange, and a multi-layer coating. The heat shield extends circumferentially partway around the axis to define a portion of gas path for the gas turbine engine. The attachment feature extends radially outward from the heat shield. The multi-layer coating is applied to different surfaces of the heat shield and the attachment feature of the shroud segment.

Abstract: A turbine shroud assembly includes a first shroud segment, a second shroud segment, and a damping strip seal. The first shroud segment has a first carrier segment arranged circumferentially at least partway around a central axis and a first blade track segment supported by the first carrier segment. The second shroud segment is arranged circumferentially adjacent the first shroud segment about the central axis. The damping strip seal extends circumferentially into the first shroud segment and the second shroud segment to block gases from passing between the first shroud segment and the second shroud segment.

Abstract: A turbine shroud assembly for use with a gas turbine engine includes a first shroud segment, a second shroud segment, and a damping strip seal assembly. The first shroud segment has a first carrier segment arranged circumferentially at least partway around a central axis and a first blade track segment supported by the first carrier segment. The second shroud segment is arranged circumferentially adjacent the first shroud segment. The damping strip seal assembly includes an axial seal member, a forward seal, and an aft seal member.

Abstract: To eliminate the adverse effects of power swings in a large scale computing system during the life cycle of an application or job, control of several operating characteristics for the collective group of processors is provided. By providing certain levels of coordination for the many processors utilized in large scale computing systems, significant and abrupt changes in power needs can be avoided. In certain circumstances, this may involve limiting the transition between several C-States of the processors involved and the overall power transitions for a large scale system are not detrimental and do not create issues for the data center or local power utility. Some cases will require stepped transitions between C-States, while other cases will include both stepped and modulated transitions. Other cases will incorporate random wait times at the various transitions in order to spread the power consumption involved.

Abstract: To eliminate the adverse effects of power swings in a large scale computing system during the life cycle of an application or job, control of several operating characteristics for the collective group of processors is provided. By providing certain levels of coordination for the many processors utilized in large scale computing systems, significant and abrupt changes in power needs can be avoided. In certain circumstances, this may involve limiting the transition between several C-States of the processors involved and the overall power transitions for a large scale system are not detrimental and do not create issues for the data center or local power utility. Some cases will require stepped transitions between C-States, while other cases will include both stepped and modulated transitions. Other cases will incorporate random wait times at the various transitions in order to spread the power consumption involved.

Abstract: To eliminate the adverse effects of power swings in a large scale computing system during the life cycle of an application or job, control of several operating characteristics for the collective group of processors is provided. By providing certain levels of coordination for the many processors utilized in large scale computing systems, significant and abrupt changes in power needs can be avoided. In certain circumstances, this may involve limiting the transition between several C-States of the processors involved and the overall power transitions for a large scale system are not detrimental and do not create issues for the data center or local power utility. Some cases will require stepped transitions between C-States, while other cases will include both stepped and modulated transitions. Other cases will incorporate random wait times at the various transitions in order to spread the power consumption involved.

Abstract: To eliminate the adverse effects of power swings in a large scale computing system during the life cycle of an application or job, control of several operating characteristics for the collective group of processors is provided. By providing certain levels of coordination for the many processors utilized in large scale computing systems, significant and abrupt changes in power needs can be avoided. In certain circumstances, this may involve limiting the transition between several C-States of the processors involved and the overall power transitions for a large scale system are not detrimental and do not create issues for the data center or local power utility. Some cases will require stepped transitions between C-States, while other cases will include both stepped and modulated transitions. Other cases will incorporate random wait times at the various transitions in order to spread the power consumption involved.