The disclosure relates to a method for operating a gas turbine at a high temperature and to a gas turbine assembly. In the method, a gas turbine having a structural material and a thermal barrier layer disposed on the structural material is cooled down in a decelerated manner after operation at an operating temperature above 1000° C., so that damage to the structural material and/or the thermal barrier layer is minimized. In this way, the gas turbine can be operated permanently at temperatures above 1500° C.

A turbine engine fleet wash management system is configured to electronically communicate with a turbine engine system, a fleet management service, and a cleaning management service. The turbine engine fleet wash system causes a cleaning of a turbine engine to occur based on information received from the turbine engine system and other sources. The turbine engine fleet wash management system includes a cleaning schedule optimizer that generates a cleaning schedule based on engine health monitoring data, engine operation data, maintenance schedules for the turbine engine, and cleaning regimen data. The cleaning schedule optimizer estimates turbine engine performance improvements based on the selected cleaning regimen, and calculating an estimate of carbon credits earned based on the predicted improvement in turbine engine performance.

A measuring system for sensing vane positions that comprises a turbine, a target, and a sensor. The turbine includes a plurality of articulating vanes, with each vane being coupled to a sync ring that is configured to position the plurality of articulating vanes in accordance with a degree of rotation by the sync ring. The target is coupled to a first position of the turbine within a first region that is associated with a first vane of the plurality of articulating vanes. The sensor is coupled via a bracket to a second position of the turbine within the first region. The sensor is configured to detect an orientation of the target that corresponds to a vane position of the first vane.

The invention relates to a mechanical fuse intended to be rigidly mounted between a drive unit (8, 9), and a receiver unit (10), each rotating about the same axis (7) of rotation, said fuse comprising a body (13) extending in a longitudinal direction parallel to said axis (7) of rotation, once the fuse is mounted between said drive unit (8, 9) and receiver unit (10). The invention is characterized in that said body (13) comprises a plurality of longitudinal bars (14), each bar (14) being deformable by bending, such as to form a twist-breakable mechanical fuse.

The invention relates to a mechanical fuse intended to be rigidly mounted between a drive unit (8, 9), and a receiver unit (10), each rotating about the same axis (7) of rotation, said fuse comprising a body (13) extending in a longitudinal direction parallel to said axis (7) of rotation, once the fuse is mounted between said drive unit (8, 9) and receiver unit (10). The invention is characterized in that said body (13) comprises a plurality of longitudinal bars (14), each bar (14) being deformable by bending, such as to form a twist-breakable mechanical fuse.

A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan and a braking system. The braking system is configured to selectively engage the fan during ground windmilling to apply a first level of braking to slow rotation of the fan. Further, when the rotation of the fan sufficiently slows, the braking system is further configured to apply a second level of braking more restrictive than the first level of braking.

A system and method for monitoring a thrust reverser system are provided. The embodiments described herein utilize sensors located proximate locks comprising a thrust reverser locking system. The provided system and method detect deflection and displacement proximate the locks to determine when individual locks have failed.

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.

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.