Abstract: A turbine engine and method of operating includes an engine core with a compressor, a combustor, and a turbine in axial flow arrangement. A flow path extends through the engine core from the compressor to the turbine to define a flow direction for a working airflow through the engine core.

Abstract: A turbine engine and method of operating includes an engine core with a compressor, a combustor, and a turbine in axial flow arrangement. A flow path extends through the engine core from the compressor to the turbine to define a flow direction for a working airflow through the engine core.

Abstract: This technology relates to transferring state information between processes or active software programs in a computing environment where a new instance of a process or software program may receive such state information even after an original or old instance of the process or software program that owned the state information has terminated either naturally or unnaturally.

Abstract: This technology relates to transferring state information between processes or active software programs in a computing environment where a new instance of a process or software program may receive such state information even after an original or old instance of the process or software program that owned the state information has terminated either naturally or unnaturally.

Abstract: A turbine engine and method of operating includes an engine core with a compressor, a combustor, and a turbine in axial flow arrangement. A flow path extends through the engine core from the compressor to the turbine to define a flow direction for a working airflow through the engine core.

Abstract: Aspects of the disclosure generally relate to a turbine engine and method of operating a turbine engine having an engine core including a compressor, combustor, and turbine in axial flow arrangement, whereby a working airflow passes through the engine core from the compressor to the turbine to define a flow direction through the engine core. The method includes generating a shockwave in the working airflow that propagates in the flow direction, and at least partially attenuating the shockwave.

Abstract: Aspects of the disclosure generally relate to a turbine engine and method of operating a turbine engine having an engine core including a compressor, combustor, and turbine in axial flow arrangement, whereby a working airflow passes through the engine core from the compressor to the turbine to define a flow direction through the engine core. The method includes generating a shockwave in the working airflow that propagates in the flow direction, and at least partially attenuating the shockwave.

Abstract: This technology relates to transferring state information between processes or active software programs in a computing environment where a new instance of a process or software program may receive such state information even after an original or old instance of the process or software program that owned the state information has terminated either naturally or unnaturally.

Abstract: This technology relates to transferring state information between processes or active software programs in a computing environment where the a new instance of a process or software program may receive such state information even after an original or old instance of the process or software program that owned the state information has terminated either naturally or unnaturally.

Abstract: A user interface for interacting with multiple databases allows a user to lock or unlock access to their data in multiple databases simultaneously, each database being controlled by a different entity. A user interface server communicates with servers of the multiple databases to request that the consumer's data be locked or unlocked. The user interface server may also report to the consumer the lock status of the consumer's data in each of the multiple databases. To authenticate the user, the user interface for interacting with multiple databases may provide one or more authentication prompts prior to allowing the user to lock or unlock access to their data. The authentication prompts may be provided by one or more of the multiple entities.

Abstract: A user interface for interacting with multiple databases allows a user to lock or unlock access to their data in multiple databases simultaneously, each database being controlled by a different entity. A user interface server communicates with servers of the multiple databases to request that the consumer's data be locked or unlocked. The user interface server may also report to the consumer the lock status of the consumer's data in each of the multiple databases. To authenticate the user, the user interface for interacting with multiple databases may provide one or more authentication prompts prior to allowing the user to lock or unlock access to their data. The authentication prompts may be provided by one or more of the multiple entities.

Abstract: This technology relates to transferring state information between processes or active software programs in a computing environment where the a new instance of a process or software program may receive such state information even after an original or old instance of the process or software program that owned the state information has terminated either naturally or unnaturally.

Abstract: A user interface for interacting with multiple databases allows a user to lock or unlock access to their data in multiple databases simultaneously, each database being controlled by a different entity. A user interface server communicates with servers of the multiple databases to request that the consumer's data be locked or unlocked. The user interface server may also report to the consumer the lock status of the consumer's data in each of the multiple databases. To authenticate the user, the user interface for interacting with multiple databases may provide one or more authentication prompts prior to allowing the user to lock or unlock access to their data. The authentication prompts may be provided by one or more of the multiple entities.

Abstract: The present disclosure is directed to a variable area turbine nozzle. The variable area turbine nozzle includes a first vane segment, a second vane segment arranged with the first vane segment, and a trailing edge segment arranged with the first and second vane segments. The vane also includes a first actuating system for pivoting the second vane segment with respect to the first vane segment and a second actuating system for pivoting the trailing edge with respect to the first and second vane segments.

Abstract: The present disclosure is directed to a variable area turbine nozzle. The variable area turbine nozzle includes a first vane segment, a second vane segment arranged with the first vane segment, and a trailing edge segment arranged with the first and second vane segments. The vane also includes a first actuating system for pivoting the second vane segment with respect to the first vane segment and a second actuating system for pivoting the trailing edge with respect to the first and second vane segments.

Abstract: Turbine assemblies for gas turbine engines are provided. In one embodiment, a turbine assembly includes a row of circumferentially adjacent turbine rotor blades, each blade in the row of blades including an airfoil defining a chord extending axially between opposite leading and trailing edges of the airfoil. The chords in a mid-span region of each blade are shorter than the chords in span regions adjacent to the blade root and the blade tip. In another exemplary embodiment, a turbine assembly includes a row of circumferentially adjacent turbine stator vanes, each vane in the row of vanes including an airfoil defining a chord extending axially between opposite leading and trailing edges of the airfoil. The chords in a mid-span region of each vane are shorter than the chords in span regions adjacent to the vane root and the vane tip. A turbine rotor blade for a gas turbine engine also is provided.

Abstract: A turbine shroud apparatus for a gas turbine engine includes: a plurality of arcuate shroud segments arranged as an annular shroud, each of the shroud segments comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces, wherein an open channel is formed through the outer wall of each shroud segment; an annular stationary structure surrounding the shroud segments; and a hanger received in the open channel of each shroud segment and mechanically coupled to the stationary structure, each of the hangers passing through the respective open channel and including an enlarged portion having greater cross-sectional area than the open channel, the enlarged portion engaging the outer wall of the respective shroud segment, so as to retain the shroud segment radially relative to the stationary structure.

Abstract: A turbine shroud apparatus for a gas turbine engine having a central axis includes: an arcuate shroud segment comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces and collectively defining a shroud cavity; and an annular stationary structure surrounding the shroud segment, where the shroud segment is mechanically coupled to the stationary structure. The stationary structure includes at least one axially-facing bearing surface which is in direct contact with the shroud segment, and the shroud segment is disposed so as to absorb at least one axially-aligned force and transfer the axially-aligned force to the bearing surface.

Abstract: A turbine shroud apparatus for a gas turbine engine includes an arcuate turbine shroud segment of low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces. At least a portion of each of the forward and aft walls is oriented at an acute angle to the outer wall. Radially inner ends of the forward and aft walls are substantially closer together than radially outer ends thereof.

Abstract: A turbine shroud apparatus for a gas turbine engine having a central axis includes: an arcuate shroud segment comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces and collectively defining a shroud cavity; an annular stationary structure surrounding the shroud segment; and a load spreader received in the shroud cavity of the shroud segment and mechanically coupled to the stationary structure. The load spreader includes: a laterally-extending plate with opposed inner and outer faces; and a boss which protrudes radially from the outer face and extends through a mounting hole in the outer wall of one of the shroud segments. A fastener engages the boss and the stationary structure, so as to clamp the boss against the stationary structure in a radial direction.