Abstract: The present application provide a seal for use between components engine facing a high pressure cooling air flow and a hot gas path in a gas turbine. The seal may include a first shim, a second shim with an air exit hole, one or more middle layers positioned between the first shim and the second shim, and one or more cooling pathways extending through the middle layers for the high pressure cooling air flow to pass therethrough and exit via the air exit hole into the hot gas path.

Abstract: Components are disclosed which include a CMC substrate having a first surface and a second surface. The first surface is in fluid communication with a compressed, dry fluid, and the second surface is in fluid communication with a wet fluid stream and includes a hermetic coating. The components further include at least one opening extending from the first surface through a portion of the CMC substrate, wherein, upon removal of a fragment of one or both of the hermetic coating and the CMC substrate, the at least one opening selectively permits a flow of the compressed, dry fluid to the second surface. In one embodiment, the component is a gas turbine component, the wet fluid stream is a hot combustion stream, the hermetic coating is an environmental barrier coating, and the flow reduces or eliminates volatilization of the CMC substrate. Methods for forming the components are also disclosed.

Abstract: A process of producing a ceramic matrix composite gas turbine component and a ceramic matrix composite gas turbine component are provided. The process includes modifying a surface of the ceramic matrix composite gas turbine component to produce a modified surface with a surface roughness of less than 6 micrometers. The modifying is selected from the group of techniques consisting of applying unreinforced matrix plies to the surface, vapor depositing silicon on the surface, honing the surface, applying braze paste to the surface, and combinations thereof. The component includes a modified surface including a surface roughness of less than 6 micrometers. The modified surface being selected from the group consisting of unreinforced matrix plies applied to a surface of the ceramic matrix composite gas turbine component, silicon vapor deposited on the surface, a honed surface, a braze paste applied to the surface, and combinations thereof.

Abstract: A turbine component is disclosed. The turbine component includes an outer shroud and an inner shroud having a first hook region extending over a first portion of the outer shroud and a second hook region extending over a second portion of the outer shroud. A first hook gap, a second hook gap, a first radial gap, and a second radial gap are arranged and disposed to permit the inner shroud to deflect from the outer shroud under thermal loading. Additionally or alternatively, the inner shroud includes ceramic matrix composite fibers having a thermal conductivity of less than 200 W/m·k and greater than 10 W/m·k.

Abstract: A pressure probe includes an elongated cable provided with a sensing tip, a portion of the elongated cable and sensing tip enclosed within a ceramic shroud, the ceramic shroud at least partially formed of a metalized ceramic material.

Abstract: A turbine component patch delivery system can include a compressed gas source fluidly connected to a delivery line comprising a dispensing end. The turbine component patch delivery system can further include one or more turbine component patch carriers that can be projected out of the dispensing end of the delivery line by the compressed gas source, wherein each of the one or more turbine component patch carriers comprise a turbine component patch material housed within a breakaway shell.

Abstract: A turbine component patch delivery system can include a support arm and a deposition tool supported by the support arm. The deposition tool can include a reservoir configured to house a turbine component patch material and a dispenser configured to dispense the turbine component patch material from the reservoir onto a surface of a turbine component.

Abstract: A method for assembling a sensor assembly includes providing a sensing device configured to measure at least one variable. The method also includes at least partially enclosing a magnetic material within an enclosure. At least a portion of the enclosure is manufactured from a material having a permeability that facilitates forming a magnetic field therein. The method also includes coupling the sensing device to a first portion of the enclosure. The enclosure includes at least one second portion that is movable with respect to the first portion of the enclosure such that a magnetic coupling force is induced external to the enclosure to facilitate coupling the sensor assembly to a magnetic surface.

Abstract: A method for assembling a sensor assembly includes providing a sensing device configured to measure at least one variable. The method also includes at least partially enclosing a magnetic material within an enclosure. At least a portion of the enclosure is manufactured from a material having a permeability that facilitates forming a magnetic field therein. The method also includes coupling the sensing device to a first portion of the enclosure. The enclosure includes at least one second portion that is movable with respect to the first portion of the enclosure such that a magnetic coupling force is induced external to the enclosure to facilitate coupling the sensor assembly to a magnetic surface.

Abstract: A system for use in monitoring operation of a rotor assembly is provided. The system includes a plurality of clearance sensors including at least a first clearance sensor configured to measure a distance between the first sensor and a surface of a lockwire tab, and a monitoring unit coupled to the plurality of clearance sensors, the monitoring unit configured to receive measurements from the plurality of clearance sensors, and determine whether a crack exists in the rotor assembly based on the received measurements.

Abstract: A system for use in monitoring operation of a rotor assembly is provided. The system includes a plurality of clearance sensors including at least a first clearance sensor configured to measure a distance between the first sensor and a surface of a lockwire tab, and a monitoring unit coupled to the plurality of clearance sensors, the monitoring unit configured to receive measurements from the plurality of clearance sensors, and determine whether a crack exists in the rotor assembly based on the received measurements.

Abstract: A method for assembling a sensor assembly includes providing a sensing device configured to measure at least one variable. The method also includes at least partially enclosing a magnetic material within an enclosure. At least a portion of the enclosure is manufactured from a material having a permeability that facilitates forming a magnetic field therein. The method also includes coupling the sensing device to a first portion of the enclosure. The enclosure includes at least one second portion that is movable with respect to the first portion of the enclosure such that a magnetic coupling force is induced external to the enclosure to facilitate coupling the sensor assembly to a magnetic surface.