A gas turbine engine (10) includes a compressor section, a turbine section, and an accessory gearbox (100). A turning unit (200) for the gas turbine engine includes an output assembly (204) configured to be mechanically coupled to the gas turbine engine, and an electric motor (202). The electric motor is operable to rotate, through the output assembly, one or more components of the compressor section or the turbine section at a rotational speed less than about fifty revolutions per minute during a shut-down condition of the gas turbine engine.

A gas turbine engine system includes an engine component comprising ceramic matrix composite materials, at least one control system configured to control at least a temperature of the engine component, and a controller. The controller includes a degradation map stored therein. The degradation map includes degradation fields, each field defined by a unique range of temperatures and stresses of the component and correlated to different types of degradation of the component. The controller is configured to determine a first temperature and stress of the component and a first field based on the first temperature and stress, determine a second field different from the first and a second temperature and stress that would locate the component in the second field, and instruct the control system to change the temperature of the component from the first to the second temperature to locate the component in the second field.

Systems and methods for optimizing clearances within an engine include an adjustable coupling configured to couple a thrust link to the aircraft engine, an actuator coupled to the adjustable coupling, where motion produced by the actuator adjusts a hinge point of the adjustable coupling, sensors configured to capture real time flight data, and an electronic control unit. The electronic control unit receives flight data from the sensors, implements a machine learning model trained to predict clearance values within the engine based on the received flight data, predicts, with the machine learning model, the clearance values within the engine based on the received flight data, determines an actuator position based on the clearance values, and causes the actuator to adjust to the determined actuator position.

Embodiments of the present disclosure include a method for controlling a power generation system, the method including: detecting a heat distribution across a component of a power generation system from a thermal output of the component, during operation of the power generation system; calculating a projected heat distribution across the component based on a library of modeling data for the power generation system; calculating whether a difference between the heat distribution and the projected heat distribution exceeds a thermal threshold; adjusting the power generation system in response to the difference exceeding the predetermined threshold, wherein the adjusting includes modifying an operating setting of the power generation system.

Embodiments of the present disclosure include a method for controlling a power generation system, the method including: detecting a heat distribution across a component of a power generation system from a thermal output of the component, during operation of the power generation system; calculating a projected heat distribution across the component based on a library of modeling data for the power generation system; calculating whether a difference between the heat distribution and the projected heat distribution exceeds a thermal threshold; adjusting the power generation system in response to the difference exceeding the predetermined threshold, wherein the adjusting includes modifying an operating setting of the power generation system.

There is provided a system and method for detecting excess flow in an engine fluid system, the method comprising sensing a temperature of a fluid flowing in a fluid line of the fluid system, the fluid line located downstream of a fluid flow restrictor configured to receive the fluid from a source upstream thereof and to flow the fluid from the source into the fluid line downstream thereof, comparing the temperature to a temperature threshold, and when the temperature is beyond the temperature threshold, detecting excess flow of the fluid in the fluid line and outputting an excess flow indication accordingly.

The present application provides a hazardous gas detection system to determine hazardous gas concentrations and/or temperatures within a flow of exhaust air in an exhaust duct of a gas turbine compartment. The hazardous gas detection system may include one or more sensors positioned within or in communication with the exhaust duct and a static mixer positioned upstream of the one or more sensors to promote mixing of the flow of exhaust air.

An operation method of a turbine fracturing device and a turbine fracturing device are provided. The turbine fracturing device includes a turbine engine, a speed reducer, a brake mechanism, and a fracturing pump, the method includes: driving, by the turbine engine, the fracturing pump to perform a fracturing operation through the speed reducer so as to keep the fracturing pump in an operating state, the fracturing pump being configured to suck fluid of a first pressure and discharge fluid of a second pressure, the second pressure being greater than the first pressure; and in response to an idling instruction, the turbine engine entering an idling state and triggering a brake operation so as to keep the fracturing pump in a non-operating state.

An aircraft power plant comprising: a high-pressure spool including a high-pressure compressor, a high-pressure turbine, and a high-pressure shaft drivingly engaging the high-pressure turbine to the high-pressure compressor; a low-pressure spool including a low-pressure compressor, a low-pressure turbine, and a low-pressure shaft drivingly engaging the low-pressure turbine to the low-pressure compressor; an electrical machine operable as a generator; and a transmission having a first input drivingly engaged by the high-pressure shaft, a second input drivingly engaged by the low-pressure shaft, and an output drivingly engaging the electrical machine, the transmission having a coupling system selectively interconnecting the output with one of: the first input, with the second input disconnected from the output; the second input, with the first input disconnected from the output; and both of the first input and the second input.

Oil system for a turbomachine, making it possible to continue the supply of oil to the pieces of equipment of the turbomachine in case of occurrence of a fire within the turbomachine, including an oil circuit, at least one oil-consuming piece of equipment, supplied by the oil circuit, a pumping unit, including at least one speed-pilotable electrically driven pump, supplying the oil circuit, and an electronic control unit, configured to pilot the electrically driven pump, wherein the electronic control unit includes two separate logics of piloting the electrically driven pump, and wherein the electronic control unit is configured to pilot the electrically driven pump according to the first logic by default and to switch to the second logic in case of receipt of a signal representative of the presence of a fire or of an overheating.