Abstract: The present disclosure is directed to a gas turbine engine that includes a hot gas path component having an inner surface and defining a hot gas path component cavity. An impingement insert is positioned within the hot gas path component cavity. The impingement insert includes an inner surface and an outer surface and defines an impingement insert cavity and a plurality of impingement apertures fluidly coupling the impingement insert cavity and the hot gas path component cavity. A plurality of pins extends from the outer surface of the impingement insert to the inner surface of the hot gas path component.

Abstract: A turbine airfoil for a rotating blade or stationary nozzle vane includes an airfoil body including a leading edge and a trailing edge. A coolant supply passage extends within the airfoil body, and a coolant return passage extends within the airfoil body. A first trench is in an external surface of the airfoil body, the first trench extending to the trailing edge and being in fluid communication with the coolant supply passage. A second trench is in the external surface of the airfoil body, the second trench extending to the trailing edge and being in fluid communication with the coolant return passage and the first trench. A cover seats in the airfoil body and encloses the trenches to form coolant passages with the airfoil body. In embodiments, two coolant passages to and back from the trailing edge may be used to allow for a recycling flow.

Abstract: A turbine airfoil for a rotating blade or stationary nozzle vane includes an airfoil body including a leading edge and a trailing edge. A coolant supply passage extends within the airfoil body and a coolant return passage extends within the airfoil body, with each passage having respective a supply and return connection passage to an exterior surface of the airfoil body. A seat in the exterior surface of the airfoil body receives a cover that includes a trench on an interior surface thereof to fluidly connect the return connection passage and the supply connection passage and form a coolant passage for the airfoil body. Various arrangements of cooling circuits may be created with the cover that allow for reuse of the coolant.

Abstract: A system for attaching a probe to a casing of a gas turbine engine is disclosed. The system may include a probe receptacle attachable to the casing. The probe receptacle may include an internal bore, a bayonet slot, a spring disposed within the internal bore adjacent to the bayonet slot, and a sealing surface within the internal bore. The system also may include a probe attachment assembly disposed about the probe and configured to engage the probe receptacle. The probe attachment assembly may include at least one bayonet positionable within the bayonet slot and a seal positionable adjacent to the sealing surface within the internal bore.

Abstract: A system for packaging electronic components in a rotatable shaft includes an annular carrier shaft having a first end that is axially spaced from a second end and an inner surface that is radially spaced from an outer surface, and a plurality of transmitter assemblies annularly arranged within the carrier shaft. Each transmitter assembly includes a transmitter housing radially supported within the carrier shaft via a pair of circumferentially spaced rail members. Each transmitter assembly comprises a daughter board that extends laterally and longitudinally across a bottom portion of the transmitter housing and at least one electronic component electrically coupled to the daughter board. The electronic component extends substantially perpendicular to the daughter board within the transmitter housing.

Abstract: The present disclosure is directed to a system for attaching an instrument lead to a gas turbine engine component. The system includes a gas turbine engine component that includes a surface. A first sleeve couples to the surface of the gas turbine engine component. The first sleeve defines a first sleeve passageway extending therethrough. An instrument lead extends through the first sleeve passageway. A first potting material couples the instrument lead to the first sleeve to prevent the instrument lead from moving longitudinally relative to the first sleeve.

Abstract: A system for routing rotatable wire bundles which extend from a rotor shaft of a turbomachine includes a plurality of wire bundles which extend outwardly from an inner passage of the rotor shaft of the turbomachine. An annular wire barrel is coupled to an end of the rotor shaft. A plurality of thru-holes is defined within and/or by the wire barrel. The plurality of thru-holes is annularly arranged therein. Each thru-hole extends through an aft wall of the wire barrel and is circumferentially spaced from adjacent thru-holes. Each wire bundle extends individually through a corresponding thru-hole of the plurality of thru-holes.

Abstract: A system for attaching a probe to a casing of a gas turbine engine is disclosed. The system may include a probe receptacle attachable to the casing. The probe receptacle may include an internal bore, a bayonet slot, a spring disposed within the internal bore adjacent to the bayonet slot, and a sealing surface within the internal bore. The system also may include a probe attachment assembly disposed about the probe and configured to engage the probe receptacle. The probe attachment assembly may include at least one bayonet positionable within the bayonet slot and a seal positionable adjacent to the sealing surface within the internal bore.

Abstract: An apparatus is disclosed including a first article, a second article, and a third article disposed adjacent to one another, with the first article and the second article disposed between the third article and a gas path. The first article includes at least one first ceramic matrix composite ply defining a first cooperating feature. The second article includes at least one second ceramic matrix composite ply defining a second cooperating feature. The first cooperating feature and the second cooperating feature define a restricted flow path from the gas path to the third article, which includes a reduced volumetric flow rate of a gas from the gas path to the third article relative to a non-restricted flow path of a non-cooperating interface. A method for forming the apparatus includes forming and aligning the first cooperating feature and the second cooperating feature.

Abstract: A fitting for positioning a probe in a hot gas path within a casing of a gas turbine engine is disclosed herein. The fitting includes a main body attachable to the casing opposite the hot gas path. The main body includes an internal bore and one or more cooling holes in communication with the internal bore. A compliant seal is positionable within the internal bore. In addition, a follower is positionable within the internal bore adjacent to the compliant seal. Moreover, the fitting includes a fastener configured to mate with the main body. In this manner, the follower deforms the compliant seal about the probe within the main body to secure and seal the probe within the main body.

Abstract: A method for routing wires from a rotor shaft of a turbomachine includes routing a plurality of wire bundles through an end portion of the rotor shaft and into an annular extension shaft which is coupled to the end portion of the rotor shaft, threading each wire bundle through a corresponding thru-hole of a plurality of thru-holes defined in an annular wire barrel, inserting the wire barrel into the extension shaft and fixedly connecting the wire barrel to the extension shaft.

Abstract: A damping system for a turbomachine slip ring includes a slip ring assembly. The slip ring assembly includes a rotating component which is coupled at one end to a rotor shaft of the turbomachine and a stator component which circumferentially surrounds a rotatable center core portion of the rotating component. The system further includes a static structure which defines a carrier sleeve where the carrier sleeve circumferentially surrounds a portion of the stator component. The system also includes a damping material which extends radially between an inner surface of the carrier sleeve and an outer surface of the stator component so as to dissipate vibrational energy of the slip ring assembly during rotation of the rotor shaft.

Abstract: A system for packaging electronic components in a rotatable shaft includes an annular carrier shaft having a first end that is axially spaced from a second end and an inner surface that is radially spaced from an outer surface, and a plurality of transmitter assemblies annularly arranged within the carrier shaft. Each transmitter assembly includes a transmitter housing radially supported within the carrier shaft via a pair of circumferentially spaced rail members. Each transmitter assembly comprises a daughter board that extends laterally and longitudinally across a bottom portion of the transmitter housing and at least one electronic component electrically coupled to the daughter board. The electronic component extends substantially perpendicular to the daughter board within the transmitter housing.

Abstract: A system for packaging electronic components in a rotatable shaft includes an annular carrier shaft having a first end that is axially spaced from a second end and an inner surface that is radially spaced from an outer surface, and a plurality of transmitter assemblies annularly arranged within the carrier shaft. Each transmitter assembly includes a transmitter housing radially supported within the carrier shaft via a pair of circumferentially spaced rail members. Each transmitter assembly comprises a daughter board that extends laterally and longitudinally across a bottom portion of the transmitter housing and at least one electronic component electrically coupled to the daughter board. The electronic component extends substantially perpendicular to the daughter board within the transmitter housing.

Abstract: A sensor simulator and a system for testing rotatable sensor signal transmitters using the sensor simulator is disclosed herein. The sensor simulator includes a first and a second pin. The first pin includes a first end portion and a second end portion where the first end portion is configured to electronically couple to a positive terminal of a sensor circuit of the sensor signal transmitter. The second pin includes a first end portion and a second end portion where the first end portion is configured to electronically couple to a negative terminal of the same sensor circuit. The sensor simulator further includes an electronic component having a first wire lead electronically coupled to the second end portion of the first pin and a second wire lead electronically coupled the second end portion of the second pin.

Abstract: A system for packaging electronic components in a rotatable shaft includes an annular carrier shaft having a first end that is axially spaced from a second end and an inner surface that is radially spaced from an outer surface, and a plurality of transmitter assemblies annularly arranged within the carrier shaft. Each transmitter assembly includes a transmitter housing radially supported within the carrier shaft via a pair of circumferentially spaced rail members. Each transmitter assembly comprises a daughter board that extends laterally and longitudinally across a bottom portion of the transmitter housing and at least one electronic component electrically coupled to the daughter board. The electronic component extends substantially perpendicular to the daughter board within the transmitter housing.

Abstract: A method for routing wires from a rotor shaft of a turbomachine includes routing a plurality of wire bundles through an end portion of the rotor shaft and into an annular extension shaft which is coupled to the end portion of the rotor shaft, threading each wire bundle through a corresponding thru-hole of a plurality of thru-holes defined in an annular wire barrel, inserting the wire barrel into the extension shaft and fixedly connecting the wire barrel to the extension shaft.

Abstract: A system for routing rotatable wire bundles which extend from a rotor shaft of a turbomachine includes a plurality of wire bundles which extend outwardly from an inner passage of the rotor shaft of the turbomachine. An annular wire barrel is coupled to an end of the rotor shaft. A plurality of thru-holes is defined within and/or by the wire barrel. The plurality of thru-holes is annularly arranged therein. Each thru-hole extends through an aft wall of the wire barrel and is circumferentially spaced from adjacent thru-holes. Each wire bundle extends individually through a corresponding thru-hole of the plurality of thru-holes.

Abstract: A system for dissipating thermal energy from electronic components disposed within a rotatable shaft includes an annular carrier shaft having one end formed to couple to an end of a rotor shaft. The system also includes a transmitter assembly. The transmitter includes an outer casing, a daughter board and a circuit board electronically coupled to the daughter board within an inner pocket of the transmitter housing. The circuit board comprises a strip of thermally conductive material. The transmitter assembly further includes a lid that at least partially seals the inner pocket. A contact surface of the lid is in thermal communication with the thermally conductive material of the circuit board and at least a portion of a top surface of the lid is thermally coupled to an inner surface of the carrier shaft during rotation thereof. A method for dissipating thermal energy away from the circuit board is also provided.

Abstract: A damping system for a turbomachine slip ring includes a slip ring assembly. The slip ring assembly includes a rotating component which is coupled at one end to a rotor shaft of the turbomachine and a stator component which circumferentially surrounds a rotatable center core portion of the rotating component. The system further includes a static structure which defines a carrier sleeve where the carrier sleeve circumferentially surrounds a portion of the stator component. The system also includes a damping material which extends radially between an inner surface of the carrier sleeve and an outer surface of the stator component so as to dissipate vibrational energy of the slip ring assembly during rotation of the rotor shaft.