Abstract: In combination a wear indicator and a component of a gas turbine engine is provided. The wear indicator is secured to a surface of the component of the gas turbine engine. The wear indicator comprising: a first side delaminates when impacted by a blade of the gas turbine engine; a second side parallel to the first side, the second side being secured to a surface of the component of the gas turbine engine; a mid-section interposed between the first side and the second side; and a reference dimension remains constant when the first side delaminates.

Abstract: A low profile un-lensed non-intrusive stress measurement system probe may comprise a housing comprising a first channel and an optical face, a first hypotube disposed within the first channel and coupled at a sensing aperture in the optical face, and a plurality of optical fibers disposed within the first hypotube, wherein the first hypotube executes a bend between 45° and 90° within the housing.

Abstract: A variable alignment aerodynamic probe may comprise a probe body having a leading edge and extending radially into a vane case, a sensor element proximate the leading edge, and a bearing coupled to the probe body and the vane case. The probe body may be configured to rotate in response to a turned flow within the vane case. The rotation of the probe body may be configured to maintain an angle of attack of the leading edge with respect to the turned flow between 0° and 15°.

Abstract: A triaxial epoxy cap probe may comprise a probe body having a cavity disposed radially outward of a fan blade and comprising a first material, an outer insulator and an inner insulator disposed within the cavity and comprising a second material, a sensor element disposed within the inner insulator, a guard annulus about the sensor element and between the inner insulator and the outer insulator, a ground plane annulus about the outer insulator, wherein the sensor element, the guard annulus, and the ground plane annulus comprise a third material, and a triaxial lead in electronic communication with the sensor element, the guard annulus, and the ground plane annulus, wherein the second material and the third material are at least one of a resin, epoxy, or thermoset material.

Abstract: A low profile embedded BTC probe may comprise a housing having a cavity disposed radially outward of a blade, a lower insulator disposed within the cavity, a sensor element disposed within the cavity, an upper insulator disposed within the cavity, a cap wherein the cap fills a remainder of the cavity, and a hard lead in electronic communication with the sensor element and the housing.

Abstract: A BTC probe may comprise a housing having a body, a neck extending radially from the body coupled to a hard lead comprising a hard shield, a driven guard, and a lead wire, and a cap coupled at a top surface of the body enclosing an interior volume of the housing. A sensor element may be disposed within the housing an coupled to the lead wire. The sensor element may comprise a sensor head having a first vertex.

Abstract: A low profile triaxial BTC probe may comprise a housing having a first body, a first cavity within the first body, and a neck extending radially from the first body, an outer hat insulator disposed within the first cavity, an inner housing, disposed within the first cavity, having a second body and a second cavity within the second body, an inner hat insulator disposed within the second cavity, a sensor element disposed within the second cavity, an inner cap insulator disposed within the second cavity, an inner cap over the inner cap insulator, an outer cap insulator disposed within the first cavity, a cap over the outer cap insulator, and a hard lead comprising a hard shield, a driven guard, and a lead wire.

Abstract: A wear indication sensor comprising: a resistor strip configured to be operably attached to the surface of an engine component, the resistor strip including a first end and second end; a plurality of lead wires comprising: a first lead wire electrically connected to the first end proximate an aft end of the engine component; a second lead wire electrically connected to the first end proximate a forward end of the engine component; a third lead wire electrically connected to the second end proximate the aft end of the engine component; and a fourth lead wire electrically connected to the second end proximate the forward end of the engine component; and a measurement device electrically connected to each of the plurality of lead wires, wherein the measurement device is configured to measure a resistance of the resistor strip between each of the plurality of lead wires.

Abstract: A method for installing a probe assembly in a case of a gas turbine engine the method including installing a first portion of the probe assembly within a first section of the case, and installing a second portion of the probe assembly within a second section of the case. A case assembly within a gas turbine engine the case assembly including a case in at least one of a compressor and a turbine, and a probe assembly. The probe assembly including a first portion positioned within a bore of the case, and a second portion positioned within an inset of the case, the bore having a smaller diameter than the inset.

Abstract: An optical probe for a gas turbine engine includes a housing. Also included is a plurality of optical fibers, a portion of each of the optical fibers secured to fiber holders. Further included is an optical head disposed within the housing and having channels extending in a longitudinal direction of the optical head, the fiber holders disposed within the channels. Yet further included is a cap disposed within the housing and operatively coupled to the optical head, the plurality of optical fibers extending through the cap. Also included is an inner tube operatively coupled to the cap, the plurality of fibers extending through the inner tube.

Abstract: A fully integral epoxy cap probe may comprise a body having a cavity disposed radially outward of a fan blade and comprising a first material, a frame disposed within the cavity and comprising a second material, a first sensor element and a ground plane disposed within the frame, the first sensor element and the ground plane comprising a third material, and a first soft lead in electronic communication with the first sensor element and the ground plane.

Abstract: A wear indicator for detecting blade clearance in a gas turbine engine includes a capacitor connected to a first conductor and a second conductor. The capacitor includes a multiple of layers arranged transverse to a rub direction, each layer separated by an insulator and including a first plate, a second plate, and a dielectric between the first plate and the second plate. A method of detecting blade clearance in a gas turbine engine, includes determining a change in capacitance between the first and second capacitance and determining an amount of material removed from the wear indicator by the blade corresponding to the change in capacitance.

Abstract: A probe assembly for a gas turbine engine is disclosed. The probe assembly may include a probe, and a fastener to retain the probe within a case of the gas turbine engine, the fastener including a sealing arrangement with a heat shield of the gas turbine engine.

Abstract: An epoxy composition may comprise a bisphenolic resin composition comprising bisphenol AF and at least one of a filler, a fire resistant component, a chain extender, a conductivity modifier, and a dye. The bisphenolic resin composition may further comprise at least one of bisphenol A and bisphenol F.

Abstract: A fully integral epoxy cap probe may comprise a body having a cavity disposed radially outward of a fan blade and comprising a first material, a frame disposed within the cavity and comprising a second material, a first sensor element and a ground plane disposed within the frame, the first sensor element and the ground plane comprising a third material, and a first soft lead in electronic communication with the first sensor element and the ground plane.

Abstract: A low profile embedded BTC probe may comprise a housing having a cavity disposed radially outward of a blade, a lower insulator disposed within the cavity, a sensor element disposed within the cavity, an upper insulator disposed within the cavity, a cap wherein the cap fills a remainder of the cavity, and a hard lead in electronic communication with the sensor element and the housing.

Abstract: In combination a blade clearance sensor and a radial flow separation wall of a gas turbine engine is provided. The blade clearance sensor is embedded in the radial flow separation wall. The radial flow separation wall comprising: a splitter hoop located radially outward from blades in a first flow path of the gas turbine engine, the splitter hoop being about concentric to a blade path of the blades; and one or more guide vane bases attached to a guide vane located radially outward from the splitter hoop in a second flow path, each of the one or more guide vane bases being securely attached to a radially outward surface of the splitter hoop, wherein the blade clearance sensor is configured to detect a blade clearance between the blades and the splitter hoop.

Abstract: A wear indication sensor comprising: a resistor strip configured to be operably attached to the surface of an engine component, the resistor strip including a first end and second end; a plurality of lead wires comprising: a first lead wire electrically connected to the first end proximate an aft end of the engine component; a second lead wire electrically connected to the first end proximate a forward end of the engine component; a third lead wire electrically connected to the second end proximate the aft end of the engine component; and a fourth lead wire electrically connected to the second end proximate the forward end of the engine component; and a measurement device electrically connected to each of the plurality of lead wires, wherein the measurement device is configured to measure a resistance of the resistor strip between each of the plurality of lead wires.

Abstract: In combination a wear indicator and a component of a gas turbine engine is provided. The wear indicator is secured to a surface of the component of the gas turbine engine. The wear indicator comprising: a first component including: a first plate; a second plate opposite the first plate; a plurality of wires extending from first plate to the second plate, wherein the first plate is electrically connected to the second plate through the plurality of wires; and a potting material configured to partially fill the first component and fill voids between the plurality of wires, such that the plurality of wires are electrically insulated from each other by the potting material.

Abstract: An axial location of a time of arrival probe may be determined by attaching a wedge comprising a distal surface to a blade. A first edge of the distal surface and a second edge of the distal surface may form an angle. The axial location of the probe may be determined based on the angle and a distance extending from the first edge of the wedge to the blade.