A system and method for adaptively controlling a cooldown cycle of an auxiliary power unit (APU) that is operating and rotating at a rotational speed includes reducing the rotational speed of the APU to a predetermined cooldown speed magnitude that ensures combustor inlet temperature has reached a predetermined temperature value, determining, based on one or more of operational parameters of the APU, when a lean blowout of the APU is either imminent or has occurred, and when a lean blowout is imminent or has occurred, varying one or more parameters associated with the shutdown/cooldown cycle.

Mounting support assemblies for fire and overheat detection systems are described. The mounting support assemblies include a support tube connector having a first portion and a second portion, wherein a captive space is defined between the first portion and the second portion, a fastener arranged at least partially within the captive space and passing through the first portion of the support tube connector, and a biasing element arranged about the fastener and positioned between an end of the fastener and the first portion of the support tube connector, the biasing element biasing the fastener in a direction toward the second portion.

An aircraft turbomachine module comprising a ventilation device configured to have a cooling air flow circulate in the turbomachine module, the ventilation device comprising an air outlet, blocking means fixed to the air outlet and mobile between a blocking position of the air outlet and an opening position of the air outlet, and locking means configured to maintain the blocking means in one of the blocking position and the opening position when the temperature within the module is less than a predetermined threshold value, the blocking means being configured to adopt the other of the blocking position and the opening position when the temperature within the module is greater than said predetermined threshold value.

A vacuum pump and a control device are capable of accurately determining timing of rotor blade replacement by creating an index which allows a degree of fatigue of a rotor blade to be determined quantitatively and easily. A motor current value output from a motor drive control portion is input to a time count processing portion, and time in which a current value of a rotating body remains in a range of a stage is totalized for each stage of the current value in the time count processing portion. A rotor blade temperature value output from a rotor blade temperature measurement portion is also input to the time count processing portion. A one-minute average value of the rotor blade temperature value acquired by sampling is calculated. For each stage of the rotor blade temperature value, time in which the average value remains in a range of the stage is totalized.

A system and method for controlling compressor inlet guide vanes of a gas turbine engine in an aircraft includes supplying, to a compressor inlet guide vane control algorithm, an inlet temperature value that is at least representative of sensed engine inlet total temperature. One or more gas turbine engine parameters are sensed with one or more sensors during operation of the gas turbine engine. The one or more gas turbine engine parameters are processed in the engine control unit to determine an inlet temperature modifier value that is an estimate of a difference between the sensed engine inlet total temperature and actual engine inlet total temperature. The inlet temperature modifier value is added to the inlet temperature value to derive a modified engine inlet total temperature. The modified engine inlet total temperature is used in the compressor inlet guide vane control algorithm, which controls the compressor inlet guide vanes.

Methods and apparatus are disclosed to determine material parameters of a turbine rotor. An example apparatus includes a rotor geometry determiner to determine a geometry of the rotor, a node radius calculator to calculate radial node locations of radial nodes including a first radial node, a thermocouple interface to record first temperature values over an interval, a first thermal stress calculator to calculate first thermal stress values at one or more of the radial nodes over the interval, a node temperature calculator to calculate second temperature values at respective internal nodes of the first radial node, a reference value lookup to lookup first material parameter information, a second thermal stress calculator to determine second thermal stress values, a thermal stress comparator to calculate a difference between the thermal stress values, and, in response to the difference not satisfying a threshold, a material parameter adjuster to determine material parameters.

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.

A gas turbine control device includes a detection value acquisition unit that acquires a detection value of at least one of a supply amount of fuel, pressure of compressed air, and electric power generated by a generator; a flue gas temperature acquisition unit that acquires a flue gas temperature detection value; a combustion gas temperature estimate value calculation unit that calculates a combustion gas temperature estimate value based on the detection value; a correction term acquisition unit that calculates a correction term based on a ratio between the combustion gas temperature estimate value and the flue gas temperature detection value; a corrected combustion gas temperature estimate value calculation unit that corrects the combustion gas temperature estimate value using the correction term to calculate a corrected combustion gas temperature estimate value; and a gas turbine controller that controls the gas turbine based on the corrected combustion gas temperature estimate value.

A hot gas path component of an industrial machine includes an adaptive cover for a cooling pathway. The component and adaptive cover are made by additive manufacturing. The component includes an outer surface exposed to a working fluid having a high temperature; an internal cooling circuit; and a cooling pathway in communication with the internal cooling circuit and extending towards the outer surface. The adaptive cover is positioned in the cooling pathway at the outer surface. The adaptive cover may include a heat transfer enhancing surface at the outer surface causing the adaptive cover to absorb heat faster than the outer surface.

In a gas turbine system which includes a compressor for sucking and compressing air and an air supplying means for supplying the compressed air from the compressor to a combustor and a turbine and which drives a power generator through rotation of the turbine, a control apparatus includes a sensing unit and a compressed air control unit. The sensing unit measures a turbine inlet temperature indicating a temperature of combustion gas introduced into the turbine and measures an exhaust gas temperature indicating a temperature of exhaust gas discharged from the turbine. The compressed air control unit control the air supplying means to adjust the amount of compressed air supplied to the turbine, based on the measured turbine inlet temperature and the measured exhaust gas temperature. The control apparatus allows the combustor to completely combust fuel even in a low load state, thereby reducing the amount of harmful exhaust gas discharged to the atmosphere.