A method of developing a suggested blend repair to an airfoil includes the steps of: (a) storing history with regard to a particular airfoil in a particular engine; (b) taking information with regard to new damage to the particular airfoil; (c) reaching an initial blend recommendation based upon step (b); (d) assessing whether the initial blend recommendation of step (c) would be appropriate to repair the new damage based upon a consideration of steps (a)-(c); and (e) reporting a final blend recommendation. An airfoil repair recommendation system is also disclosed.

Providing wear-related prognostics and diagnostics on a turbine engine includes, while operating a turbine control device, tracking a total device travel distance over time by recurrently: selectively identifying actual device movement based on device position data associated with a displacement sensor monitoring the turbine control device; and accumulating an incremental device travel distance corresponding to the identified actual device movement with the total device travel distance.

A method is provided for testing an annular seal within a gas turbine engine. During this method, a vacuum is applied to a first volume through a conduit. The annular seal is between the first volume and a second volume. A vacuum pressure is measured within the conduit while the vacuum is applied. The measured vacuum pressure is compared to a threshold vacuum pressure. A difference between the measured vacuum pressure and the threshold vacuum pressure is indicative of leakage across the annular seal from the second volume to the first volume.

A method of operating a turbine engine that includes shutting down the turbine engine such that a rotational speed of the turbine engine decreases, and actuating a starter motor of the turbine engine at one of as the rotational speed of the turbine engine decreases or at a preset time after the turbine engine receives a full stop command such that residual heat is exhausted from the turbine engine.

A method of operating a turbine engine that includes shutting down the turbine engine such that a rotational speed of the turbine engine decreases, and actuating a starter motor of the turbine engine at one of as the rotational speed of the turbine engine decreases or at a preset time after the turbine engine receives a full stop command such that residual heat is exhausted from the turbine engine.

An angled face cap probe includes a housing having a radially inner end and a radially outer end, defining a cavity, and configured to be located radially outward from an airfoil. The angled face cap probe further includes a sensor located in the cavity at the radially inner end of the housing, having a sensor body with a sensing face that is angled to match or substantially match an angle of a radially outward face the airfoil, and having a sensor flat that is elongated in a first direction. The angled face cap probe further includes an outer cap located in the cavity, coupled to the housing, and having an outer cap main body and cap legs that extend radially inward from the outer cap main body to interface with the sensor flat to resist rotation of the sensor relative to the housing.

A propeller health monitoring system for an aircraft includes an aircraft having one or more propellers that includes light in or on them. The system includes one or more receptors mounted to a fuselage or a nacelle of the aircraft, each receptor having a sensor surface which is able to detect a position for each light beam crossing over the sensor surface as the propeller rotates, such that the receptor generates a signal that is indicative of the position as a measure of blade tip trajectory for each passing propeller blade The system also includes a processing unit which analyses the signals from the receptor to determine health of the propeller blades of the one or more propellers based on where the beams of light from the propeller blades have crossed over the sensor surface.

An embodiment of a gas turbine engine component includes an abrasive coating disposed on at least a portion of a sealing region. The abrasive coating includes an inner abrasive region disposed outward of the sealing region in a coating thickness direction, and an outer abrasive region disposed outward of the inner abrasive region in the coating thickness direction. The inner abrasive region includes abrasive particles retained in an inner matrix, and the outer abrasive region includes abrasive particles retained in an outer matrix. At least one of the inner matrix and the outer matrix is modified with a first indicator material. At least one aspect of the first indicator material corresponds to a thickness range of the abrasive coating being within the inner thickness region or the outer thickness region.

A bowed rotor prevention system for a gas turbine engine includes a core turning motor operable to drive rotation of an engine core of the gas turbine engine. The bowed rotor prevention system also includes a full authority digital engine control (FADEC) that controls operation of the gas turbine engine in a full-power mode and controls operation of the core turning motor to drive rotation of the engine core using a reduced power draw when the FADEC is partially depowered in a low-power bowed rotor prevention mode.

A monolithic lead separator includes a primary lead tube defining a primary channel, a plurality of secondary lead tubes formed monolithically with the primary lead tube, and an instrumentation lead splitter. A cap is positioned in an aperture in the instrumentation lead splitter in a fluid-tight manner. Each of the secondary channels intersects the primary channel. The instrumentation lead splitter is situated at the intersection of the primary channel and the secondary channels.