A training apparatus is provided that includes a stand and at least one gas turbine engine fan stage. The at least one gas turbine engine fan stage has a plurality of fan rotor blades attached to a disk. The at least one gas turbine engine fan stage has an axially extending centerline, and the disk is mounted for rotation about the axially extending centerline. The stand is configured to support the at least one gas turbine engine fan stage.

A gas turbine includes a main shaft connecting a turbine to a compressor and an additional shaft extending coaxially to the main shaft. The additional shaft has a first shaft section connected to the compressor and a second shaft section connected to the turbine, the shaft sections separated from each other by a gap. At mutually facing ends, the two shaft sections have mutually corresponding structures. The gap been the two shaft sections is dimensioned such that, upon a break of the main shaft, the mutually corresponding structures of the mutually facing ends of the two shaft sections come into interaction and rotate relative to one another as a result of their differing rotational speeds. The mutually corresponding structures are formed such that the two shaft sections are moved away from one other in the event of twisting of the two shaft sections.

A compressor surge control system includes a rotor system with at least one compressor section and at least one turbine section operably coupled to a shaft. The compressor surge control system also includes one or more rotor system sensors configured to collect a plurality of sensor data from the rotor system, an electric motor operably coupled to the rotor system, and a controller. The controller is operable to monitor the one or more rotor system sensors while the rotor system is rotating. The controller determines whether the plurality of sensor data from the one or more rotor system sensors is indicative of an early-stage compressor surge oscillation. A surge control torque is determined to diminish the early-stage compressor surge oscillation of the rotor system. The electric motor is commanded to apply the surge control torque to the rotor system.

A wellhead assembly for use with a well that includes a production tree, a production line for carrying produced fluid from the production tree, and a choke in the production line. The choke assembly includes a turbine member that rotates in response to fluid flowing through the production line. The kinetic energy of the rotating turbine is converted into electricity by a generator that is coupled with the turbine member. Selectively impeding turbine rotation with a brake system introduces a pressure drop in the production line fluid, and which regulates flow of the production line fluid. The turbine member can be disposed in a straight run of the production line, or adjacent a bend in the production line.

A gas turbine engine has an engine static structure and at least one component rotatable relative to the engine static structure about an engine axis of rotation. A fan is coupled to at least one component for rotation about the engine axis of rotation. An actuator is mounted to the engine static structure, wherein the actuator is activated to prevent the fan from rotation and is inactivated to allow the fan to rotate. A method for preventing rotation of a fan in a gas turbine engine is also disclosed.

A low pressure compressor section of a gas turbine engine includes low pressure compressor stages spaced apart along an axis of rotation of the low pressure compressor section. The low pressure compressor section includes at least one of a fluid conduit extending between an air inlet of the gas turbine engine and the low pressure compression stages. The fluid conduit having at least one flow diverter displaceable between a first position and a second position to modulate air through the low pressure compressor stages. And/or a compressor stage disabler is engageable with at least one of the low pressure compressor stages and configured to reduce a rotation thereof.

A gearbox arrangement of an electric machine of an engine includes a planetary gear arrangement configured to receive rotational input from the electric machine and from the engine and to mechanically couple the electric machine and the engine in first and second power flow directions, the planetary gear set comprising a ring gear, a ring brake, a free-wheel clutch attachable to a fixed structure and the ring brake, the free-wheel clutch permitting rotation of the ring brake in a first direction and preventing rotation of the ring brake in an opposite second direction, and an arrangement for moving the ring gear between a first position in which the ring gear is non-rotatably engaged with the ring brake and a second position in which the ring gear is non-rotatably engaged with the carrier. An engine starter and power generator device Is also provided.

A data center cooling system configured to cool one or more components of a data center thereby enabling a data center to be maintained at a higher overall temperature while still providing sufficient cooling to the components housed in the data center is disclosed. By maintaining the data center at a higher overall temperature, significant operational costs are realized due to savings in power costs. The data center cooling system may include one or more turbo-expanders having a rotary turbine positioned within a turbo-expander housing in which compressed air expands and drives the rotary turbine. The cooled expanded air is heated passing through a thermal transfer system that pulls heat from the data center component. The air is further heated passing through a brake system that generates heat by applying resistance to a shaft coupled to the rotary turbine. The heated air is exhausted outside of the data center.

The abrupt cessation or run-away of a combustion engine may damage the combustion engine and pose a safety hazard to the surrounding environment. The combustion engine operational mode may be controlled, regulated or maintained by regulating the combustion mixture of the combustion engine. The oxidizer flow, a material or both of the combustion mixture may be regulate to create or form a combustion material that is outside a combustible range such that the combustion engine is placed or maintained in a spin-down operational mode. The material added to the combustion mixture may include a combustible, non-combustible, oxidizer, or exhaust material. A brake may also provide a secondary mechanism to maintain or place the combustion engine in a spin-down mode.

A gas turbine engine has an engine static structure. At least one component rotatable relative to the engine static structure about an engine axis of rotation. A fan is coupled to at least one component for rotation about the engine axis of rotation. An actuator is mounted to the engine static structure, wherein the actuator is activated to prevent the fan from rotation and is inactivated to allow the fan to rotate. A method for preventing rotation of a fan in a gas turbine engine is also disclosed.