Abstract: A tip clearance probe includes at least one anti-rotation feature within the probe housing that prevents a sensor component from rotating when the tip clearance probe fails due to extraordinary wear and tear.

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: Disclosed is a probe including a housing; a plurality of axially stacked caps disposed within the housing, the plurality of stacked caps including an inner cap and an outer cap, a probe sensor fixedly disposed between the inner cap and an axial bottom of the housing, and an electronic lead connected to the probe sensor and axially extending through the plurality of caps to an exterior of the probe.

Abstract: A disclosed probe assembly includes a sensor member and an outer holder including a main bore for the sensor member, the outer holder including a first coefficient of thermal expansion. The sensor member is held within a sensor bore of an inner holder. The inner holder is held within the main bore of the outer holder by an interference fit. The inner holder includes a second coefficient of thermal expansion greater than the first coefficient of thermal expansion. Expansion of the inner holder is constrained by the outer holder to maintain the sensor member within the probe bore of the inner holder at elevated temperatures.

Abstract: A proximity sensor includes a lead supported on an outer surface of a case structure and a sensor wire that extends from the lead and through an opening in the case structure. The sensor is formed by applying alternating layers of electrically conductive and non-conductive materials in a non-cured state. A base non-conductive layer is applied to an inner surface of the case structure around the sensor wire in a non-cured state. Once cured, a conductive layer is deposited onto the base non-conductive layer and encapsulates the sensor wire. A cover non-conductive layer is then deposited over portions of the conductive layer to insulate the conductive layer. Portions of the non-conductive layer are then removed such that an area of the conductive layer is exposed to define a sensor area.

Abstract: A method for installing a probe assembly in a case of a gas turbine engine is disclosed. The method may include 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 is also disclosed. The case assembly may include a case in at least one of a compressor and a turbine, and a probe assembly. The probe assembly may include 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: 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: 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: A method for installing a probe assembly in a case of a gas turbine engine is disclosed. The method may include 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 is also disclosed. The case assembly may include a case in at least one of a compressor and a turbine, and a probe assembly. The probe assembly may include 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 includes a first end, a second end, an outer housing, an inner housing concentric with the outer housing, flow holes within the inner housing at the first end, and an optics holder within the inner housing between the flow holes and the second end. The optical probe further includes high temperature optical lenses inside the optics holder between the flow holes and the second end, fiber holders inside the optics holder between the high temperature optical lenses and the second end, optical fibers coated in a high temperature material extending from inside fiber holders towards the second end, and a high temperature adhesive for securing the optical fibers, the fiber holders, and the high temperature optical lenses.

Abstract: A capacitance based clearance probe has a partial sensor housing mounted on a surface and a sensor rod anchored in the partial sensor housing. The sensor rod extends into a sensor opening in the surface such that the partial sensor housing and the surface combine to operate as a complete sensor housing.

Abstract: An example turbomachine probe assembly includes a probe body extending along a probe axis from a first sensor end to an opposing second end. An eccentric retention feature is configured to engage the probe body into contact with wall having an aperture that receives the probe body. The eccentric retention feature limits movement of the probe body along the probe axis relative to the wall.

Abstract: An example split-face probe includes a sensor component having a split-face, a housing arranged about the sensor component, and at least one ceramic fitting that supports the sensor component.

Abstract: An instrumentation component includes an instrumentation portion, a casing at least partially surrounding the instrumentation portion, a lead protruding from the instrumentation portion through a lead egress hole in the casing, a lead egress adapter, and a lead egress cap. The lead egress adapter is situated in the lead egress hole. The lead egress adapter includes a cup portion and a lip portion at least partially circumscribing the cup portion. The lead egress adapter includes a hole in the cup portion. The lead protrudes through the cup hole and the cup hole is tight fit to the lead. A potting material fills a remainder of the cup portion. The lip portion of the lead egress adapter contacts the casing. A lead egress cap seals the lead egress adapter to the casing. The lead egress cap further includes a cap hole through which the lead protrudes, and the cap hole is tight fit to the lead egress.

Abstract: A disclosed probe assembly includes a sensor member and an outer holder including a main bore for the sensor member, the outer holder including a first coefficient of thermal expansion. The sensor member is held within a sensor bore of an inner holder. The inner holder is held within the main bore of the outer holder by an interference fit. The inner holder includes a second coefficient of thermal expansion greater than the first coefficient of thermal expansion. Expansion of the inner holder is constrained by the outer holder to maintain the sensor member within the probe bore of the inner holder at elevated temperatures.

Abstract: A turbine section according to an exemplary aspect of the present disclosure includes, among other things, an airfoil including an edge and a probe positioned a distance from the airfoil. The probe is configured to detect radiation emitted from a radiation source. A sensor is operatively coupled to the probe and is configured to generate a signal utilized to determine when the edge of the airfoil extends into a line-of-sight between the probe and the radiation source.

Abstract: A disclosed probe assembly includes a sensor member and an outer holder including a main bore for the sensor member, the outer holder including a first coefficient of thermal expansion. The sensor member is held within a sensor bore of an inner holder. The inner holder is held within the main bore of the outer holder by an interference fit. The inner holder includes a second coefficient of thermal expansion greater than the first coefficient of thermal expansion. Expansion of the inner holder is constrained by the outer holder to maintain the sensor member within the probe bore of the inner holder at elevated temperatures.

Abstract: A proximity sensor includes a lead supported on an outer surface of a case structure and a sensor wire that extends from the lead and through an opening in the case structure. The sensor is formed by applying alternating layers of electrically conductive and non-conductive materials in a non-cured state. A base non-conductive layer is applied to an inner surface of the case structure around the sensor wire in a non-cured state. Once cured, a conductive layer is deposited onto the base non-conductive layer and encapsulates the sensor wire. A cover non-conductive layer is then deposited over portions of the conductive layer to insulate the conductive layer. Portions of the non-conductive layer are then removed such that an area of the conductive layer is exposed to define a sensor area.

Abstract: A turbine section according to an exemplary aspect of the present disclosure includes, among other things, an airfoil including an edge and a probe positioned a distance from the airfoil. The probe is configured to detect radiation emitted from a radiation source. A sensor is operatively coupled to the probe and is configured to generate a signal utilized to determine when the edge of the airfoil extends into a line-of-sight between the probe and the radiation source.

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.