A gas turbine engine starting system including an electric start generator (ESG) free of temperature sensors and configured to provide torque to a gas turbine engine. A fuel metering module is configured to provide a quantity of fuel to the gas turbine engine, and an electronic control system (ECS). The ESG includes a plurality of subcomponents. The ECS is configured to predict a future temperature of the ESG, predict that at an ongoing start or an uninitiated start will be unsuccessful, and provide the prediction that at an ongoing start or an uninitiated start will be unsuccessful to an operator. The prediction of the future temperature of the ESG is based on a plurality of historical ESG thermal trending information and an input ambient temperature. The prediction that at an ongoing start or an uninitiated start will be unsuccessful is based on the future temperature of the ESG.

Embodiments of the disclosure provide a method for controlling a power generation system during on-line maintenance. The method includes operating the power generation system in a first maintenance mode, which causes a controller of the power generation system to disable an automated response to at least one operational fault of the power generation system; monitoring a risk parameter of the power generation system or at least one sensor within the power generation system while operating the power generation system in the first maintenance mode; and operating the power generation system in a second maintenance mode in response to detecting an override command, an elapsed time exceeding a time limit, or the monitored risk parameter exceeding a safety threshold. The second maintenance mode causes the controller of the power generation system to enable the automated response to the at least one operational fault of the power generation system.

Propulsion engines and methods of accessing components within propulsor cavities of propulsion engines are disclosed. A propulsion engine includes an outer engine housing that includes a propulsor cavity located therein. The propulsor cavity is axially located between a low-pressure compressor and a fan of the propulsion engine. An electric converter is disposed within the propulsor cavity.

Embodiments of the present disclosure generally relate to methods for cleaning aerospace components having oxidation, corrosion, contaminants, and/or other degradations. In one or more embodiments, a cleaning method includes positioning the aerospace component into a processing region of a processing chamber, introducing hydrogen gas into the processing region, maintaining the processing region at a pressure of about 100 mTorr to about 5,000 mTorr, and heating the aerospace component at a temperature of about 500° C. to about 1,200° C. for about 0.5 hours to about 24 hours to produce a cleaned surface on the aerospace component. In other embodiments, a cleaning method includes exposing the aerospace component to ozone while maintaining the aerospace component at a temperature of about 15° C. to about 500° C. for 0.25 hours to about 24 hours to produce a cleaned surface on the aerospace component.

A method of monitoring a gas turbine engine includes the steps of: (a) receiving information from actual flights of an aircraft including an engine to be monitored, and including at least one of the ambient temperature at takeoff, and internal engine pressures, temperatures and speeds; (b) evaluating the damage accumulated on an engine component given the data received in step (a); (c) storing the determined damage from step (b); (d) repeating steps (a)-(c); (e) recommending a suggested future use for the component based upon steps (a)-(d). A system is also disclosed.

Apparatus for machining a component of a gas turbine engine, the apparatus including: a flexible pipe having a first end and a second end and defining a conduit for receiving a fluid; one or more first actuators arranged to enable the first end of the flexible pipe to be re-positioned relative to the second end of the flexible pipe; a turbine positioned adjacent to the first end of the flexible pipe, the turbine being arranged to receive fluid from the conduit of the flexible pipe; and a tool head coupled to the first end of the flexible pipe, the tool head including: a fastener arranged to fasten to a tool and to receive torque from the turbine.

A retention member for a component of a gas turbine engine and methods of using the same are provided. The retention member includes an annular body having a first side, a second side, a first end, and a second end, a retention element configured at the first end of the annular body and on the first side, the retention element configured to releasably engage with an interior surface of a case of the gas turbine engine, and a support element configured at the second end of the annular body, the support element configured to engage with a surface of at least one of a blade outer air seal or a blade outer air seal support.

A method for servicing a gas turbine engine includes providing access from a forward section of the gas turbine engine to a gearbox contained within a bearing compartment.

A gas turbine includes an exhaust cylinder comprising an inner circumferential slot, a diffuser shell disposed at least substantially concentrically within the exhaust cylinder and one or more baffle plates extending between the exhaust cylinder and the diffuser shell, a proximal end of each of the one or more baffle plates being fixed to the diffuser shell by one or more holding rings and a distal end of each of the one or more baffle plates being slidingly received within the inner circumferential slot of the exhaust cylinder. The one or more holding rings are secured to the diffuser shell, at one or more holding segments disposed along an inner diameter of the diffuser shell, via a plurality of radially inserted fastening members.

A tool assembly for safely rotating a heavy turbine generator rotor for alignment and maintenance purposes. The tool assembly includes a plurality of segments mounted to an outer face of a coupling affixed to an end of a shaft of the rotor, where the segments include a plurality of segment teeth extending beyond an outer edge of the coupling. A tool is positioned adjacent to the coupling and includes a support assembly, a hydraulic ram and a ratcheting pawl. The ratcheting pawl includes a drive pin positioned to engage the teeth of the segments, where extension of a piston rod from the hydraulic ram causes the coupling and shaft to rotate.