Abstract: An assembly for a turbine engine comprising a plurality of circumferentially arranged segments having first and second confronting end faces. The first and second confronting end faces include a multi-channel spline seal assembly. The multi-channel spline seal assembly includes at least a first and second channel wherein confronting first or second channels can receive at least one spline seal.

Abstract: A vehicle is provided including a structure including a skin defining an outside surface exposed to ambient cooling flow and an inside surface. The structure includes a first structural member extending from the inside surface of the skin and a second structural member extending from the inside surface of the skin; and a thermal management system including a heat exchanger assembly positioned adjacent to, and in thermal communication with, the inside surface of the skin, the heat exchanger assembly positioned at least partially between the first and second structural members of the structure.

Abstract: A patient temperature control system for automated temperature control according to a programmed protocol. In one aspect, at least one programmed protocol may be established for each of a plurality of patient thermal therapy phases. In turn, the temperature of a thermal exchange medium may be controlled upon the programmed protocol during each of the phases. A plurality of programmed protocols may be established, wherein a selected protocol may be utilized for automated temperature control during patient thermal therapy. The protocol may include a target patient temperature and/or a set duration for one or more of the phase of thermal therapy. The protocol may be user-definable and modifiable during therapy. In a multiphase configuration, automatic termination and initiation of successive phases may be selectively established by a user, based on target patient temperature data and/or set duration data on a phase-specific basis.

Abstract: A seal assembly to seal a gas turbine hot gas path flow at an interface of a combustor liner and a downstream component, such as a stage one turbine nozzle, in a gas turbine. The seal assembly including a piston ring seal housing, defining a cavity, and a piston ring disposed within the cavity. The piston ring disposed circumferentially about the combustor liner. The piston ring is responsive to a regulated pressure to secure sealing engagement of the piston ring and outer surface of the combustor liner. The seal assembly includes at least one of one or more sectional through-slots, bumps or channel features to provide for a flow therethrough of a high-pressure (Phigh) bypass airflow exiting a compressor to the cavity. The high-pressure (Phigh) bypass airflow exerting a radial force on the piston ring.

Abstract: A scavenge tube for conveying oil within an engine. The scavenge tube includes an outer tube and an inner tube. The outer tube defines a first surface and the inner tube defines a second surface. The inner tube is configured to be fluidly connected to a source for oil. A space that is defined between the outer tube and the inner tube such that the first surface opposes the second surface. A plurality of bumps is positioned within the space such that each bump extends from one of the first surface and the second surface and extends toward the opposing surface.

Abstract: A turbine engine includes an engine core defining a higher pressure region and a lower pressure region. A seal can fluidly separate the higher pressure region from the lower pressure region and be movably mounted to a component within the turbine engine, where a side of the seal can confront the component.

Abstract: A patient temperature control system and method are provided for automated temperature control according to a programmed protocol. In one aspect, at least one programmed protocol may be established for each of a plurality of patient thermal therapy phases. In turn, the temperature of a thermal exchange medium may be controlled, based at least in part, upon the programmed protocol, during each of the phases. In another aspect, a plurality of programmed protocols may be established, wherein a selected one of the protocols (e.g. selected by a user at a user interface) may be utilized for automated temperature control during patient thermal therapy. The protocol(s) may include a target patient temperature and/or a set duration for one or more of the phase of thermal therapy. Further, the protocol(s) may be user-definable and modifiable during therapy.

Abstract: Gas turbine engine components are provided which utilize an insert to provide cooling air along a cooled surface of an engine component. The insert provides cooling holes or apertures which face the cool side surface of the engine component and direct cooling air onto that cool side surface. The apertures may be formed in arrays and directed at an oblique or a non-orthogonal angle to the surface of the insert and may be at an angle to the surface of the engine component being cooled. An engine component assembly is provided with counterflow impingement cooling, comprising an engine component cooling surface having a cooling fluid flow path on one side and a second component adjacent to the first component. The second component may have a plurality of openings forming an array wherein the openings extend through the second component at a non-orthogonal angle to the surface of the second component.

Abstract: An apparatus for a turbine engine comprising an outer casing, an engine core provided within outer casing and having a at least one set of blades, and through which gasses flow in a forward to aft direction, an outer drum located within the outer casing to define an annular cavity. A set of seals extending between the first surface and the second surface to define at least one cooled cavity within the annular cavity.

Abstract: An apparatus and method of cooling a hot portion of a gas turbine engine, such as a multi-stage compressor of a gas turbine engine, by reducing an operating air temperature in a space between a seal and a blade post of adjacent stages by routing cooling air through an inlet in the vane, passing the routed cooling air through the vane, and emitting the routed cooling air into the space.

Abstract: A method of making a shroud assembly by: forming a shroud frame consisting of a one-piece hook and rail assembly which includes a first rail and a second rail disposed at lateral edges and a first support and a second support connected to the first rail and the second rail, the first and second rails and the first and second supports being integrally joined to one another and defining a central aperture therebetween; joining a metallic backsheet to the shroud frame covering the central aperture; and attaching a honeycomb rubs strip to the metallic backsheet via an upper edge of the honeycomb seal structure.

Abstract: An apparatus and method for cooling a portion of a turbine engine comprising an outer casing defining an axial centerline, a turbine section through which a flow of combustion gasses flows in a forward to aft direction, an outer drum located between the outer casing and the turbine section defining an annular cavity therebetween. A set of seals extends between the outer casing and outer drum to define at least one cooled cavity.

Abstract: An apparatus and method of cooling a hot portion of a gas turbine engine, such as a multi-stage compressor of a gas turbine engine, by reducing an operating air temperature in a space between a seal and a blade post of adjacent stages by routing cooling air through an inlet in the vane, passing the routed cooling air through the vane, and emitting the routed cooling air into the space.

Abstract: An apparatus and method for cooling a portion of a turbine engine comprising an outer casing defining an axial centerline, a turbine section through which a flow of combustion gasses flows in a forward to aft direction, an outer drum located between the outer casing and the turbine section defining an annular cavity therebetween. A set of seals extends between the outer casing and outer drum to define at least one cooled cavity.

Abstract: A turbine engine includes an engine core defining a higher pressure region and a lower pressure region. A seal can fluidly separate the higher pressure region from the lower pressure region and be movably mounted to a component within the turbine engine, where a side of the seal can confront the component.

Abstract: A patient temperature control system and method are provided for automated temperature control according to a programmed protocol. In one aspect, at least one programmed protocol may be established for each of a plurality of patient thermal therapy phases. In turn, the temperature of a thermal exchange medium may be controlled, based at least in part, upon the programmed protocol, during each of the phases. In another aspect, a plurality of programmed protocols may be established, wherein a selected one of the protocols (e.g. selected by a user at a user interface) may be utilized for automated temperature control during patient thermal therapy. The protocol(s) may include a target patient temperature and/or a set duration for one or more of the phase of thermal therapy. Further, the protocol(s) may be user-definable and modifiable during therapy.

Abstract: A compressor for a gas turbine engine includes a stator and a rotor. The stator includes first and second stator vanes attached to first and second vane platforms, respectively. The rotor includes a plurality of rotor blades that rotate with respect to the stator. An inner stator casing supports the first and second vane platforms and encloses the stator and the rotor. An outer stator casing encloses the inner stator casing, and a bleed cavity is disposed therebetween. At least one diffuser is disposed between the first vane platform and the second vane platform, and is configured to allow air communication between the inner stator casing and the bleed cavity. An exit opening of the diffuser is disposed within the bleed cavity at a location separate from the inner stator casing and the outer stator casing.

Abstract: A patient temperature control system and method are provided for automated temperature control according to a programmed protocol. In one aspect, at least one programmed protocol may be established for each of a plurality of patient thermal therapy phases. In turn, the temperature of a thermal exchange medium may be controlled, based at least in part, upon the programmed protocol, during each of the phases. In another aspect, a plurality of programmed protocols may be established, wherein a selected one of the protocols (e.g. selected by a user at a user interface) may be utilized for automated temperature control during patient thermal therapy. The protocol(s) may include a target patient temperature and/or a set duration for one or more of the phase of thermal therapy. Further, the protocol(s) may be user-definable and modifiable during therapy.

Abstract: A seal assembly to seal a gas turbine hot gas path flow at an interface of a combustor liner and a downstream component, such as a stage one turbine nozzle, in a gas turbine. The seal assembly including a piston ring seal housing, defining a cavity, and a piston ring disposed within the cavity. The piston ring disposed circumferentially about the combustor liner. The piston ring is responsive to a regulated pressure to secure sealing engagement of the piston ring and outer surface of the combustor liner. The seal assembly includes at least one of one or more sectional through-slots, bumps or channel features to provide for a flow therethrough of a high-pressure (Phigh) bypass airflow exiting a compressor to the cavity. The high-pressure (Phigh) bypass airflow exerting a radial force on the piston ring.

Abstract: A scavenge tube for conveying oil within an engine. The scavenge tube includes an outer tube and an inner tube. The outer tube defines a first surface and the inner tube defines a second surface. The inner tube is configured to be fluidly connected to a source for oil. A space that is defined between the outer tube and the inner tube such that the first surface opposes the second surface. A plurality of bumps is positioned within the space such that each bump extends from one of the first surface and the second surface and extends toward the opposing surface.