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.

Disclosed is a vane assembly fixed to a turbine casing of a turbine and configured to guide the flow of combustion gas having passed by a turbine blade airfoil. The vane assembly comprises a vane airfoil configured to guide the flow of the combustion gas, a platform portion combined with an end of the vane airfoil, carrier hook portions formed at respective periphery portions of the platform portion and provided with a thermal stress prevention slot on a surface facing the turbine casing, and a seal plate installed in the thermal stress prevention slot, thereby preventing a portion of compressed air produced by a compressor and supplied to the platform portion between the carrier hook portions from leaking out of the platform portion through the thermal stress prevention slot.

A method of modulating cooling of gas turbine engine components includes the steps of identifying an input indicative of a usage rate for at least a first gas turbine engine component of a plurality of gas turbine engine components. A cooling system is operated for at least the first gas turbine engine component. The cooling system is moved between a higher cooling potential mode and a lower cooling potential mode based on the identified rate. A gas turbine engine is also disclosed.

According to an aspect, a method includes predicting, by a processor, a projected oil-wetted metal temperature in a lubrication system of a gas turbine engine at shutdown based on one or more thermal models prior to shutdown of the gas turbine engine. The processor determines a coking index based on the projected oil-wetted metal temperature and a coking limit threshold associated with one or more engine components. An oil coking mitigation action is triggered as a shutdown management event of the gas turbine engine based on the coking index.

A method for operating a gas turbine installation with a measured compressor inlet temperature (Ti-actual) and a virtually constant turbine inlet temperature (TiTiso), wherein to provide safe operation of the gas turbine installation, an increase in a calculated exhaust gas temperature (ATK) is compensated by a reduced mass flow (m) of a flow medium flowing through a compressor of the gas turbine installation. An arrangement for operating the gas turbine installation includes a functional unit and a gas turbine installation with a compressor, a turbine, a control system for operating the method.

A gas turbine engine component includes a conformal surface. An array of resistance temperature detector (RTD) sensors is disposed across at least a portion of the conformal surface and a plurality of printed circuit traces are deposited on the conformal surface. The printed circuit traces connect each of the RTD sensors to a controller via a corresponding four wire circuit. Each circuit trace in the plurality of circuit traces extends to a circumferential edge of the conformal surface.

A method of modulating cooling flow to an engine component based on a health of the component is provided. The method includes determining a cooling flow requirement of the engine component for each of a plurality of operating conditions and channeling the determined required flow to the engine component during each respective operating condition of the plurality of operating conditions. The method also includes assessing a health of the engine component. The method further includes modifying the determined cooling flow requirement based on the assessed health of the engine component, and supplying the modified cooling flow requirement to the engine component during each subsequent respective operating condition of the plurality of operating conditions.

An aircraft turbomachine (100) comprising a first channel (200) putting into communication the high-pressure compressor (30) and a high-pressure turbine (50), a second channel (400) putting into communication the high-pressure compressor and a low-pressure turbine (60), the first channel being equipped with a valve (600), a third channel (700) being in selective communication with the first channel via the valve, the third channel being in communication with the low-pressure turbine, the valve having a first configuration in which air circulation in the first channel is allowed and prohibited in the third channel, and a second configuration in which air circulation of the first channel is diverted to the third channel, a control device (800) being configured to determine an air pressure of the low-pressure turbine and command the valve to cause it to transition from the first configuration to the second configuration depending on the determined pressure.

An operational support device sets an execution time of overfiring serving as an operation of a power generation facility at an output higher than a rated output. The device includes a life index value acquisition unit that acquires a life index value at a start time, the life index value being an index indicating a life of the power generation facility and changing in value in one direction with the output of the power generation facility; an output pattern setting unit that sets an output pattern per unit time of the power generation facility from the start time to a stop time based on the life index value such that the life index value reaches a predetermined value; and an overfiring setting unit that sets, based on the output pattern, a time in a period from the start to the stop time at which the overfiring is to be performed.

A method for controlling compressed air sent to pneumatic systems. The method includes acquiring a set of performance demands for each of a plurality of pneumatic systems in a platform, where the performance demands indicate needs for the compressed air supplied to each of the pneumatic systems, identifying a maximum allowable air discharge temperature limit of a variable speed air compressor configured to supply compressed air to the pneumatic systems, and controlling an operation of the compressor to supply the compressed air to the pneumatic systems to meet the acquired performance demands for at least one of the pneumatic systems while operating the compressor below the maximum allowable air discharge temperature limit.