Control systems and methods for securely authenticating and validating a control system. The control system may include a plurality of dependent control nodes and master control nodes. Each dependent control node is communicatively coupled to one or more peripheral devices. Each control node maintains a unit level distributed ledger, where each unit level distributed ledger includes information from corresponding peripheral devices. Each control node may transmit a portion of the unit level distributed ledger to a master control node. Each master control node may maintain a system level distributed ledger that includes information from the corresponding unit level distributed ledgers. Each master node may transmit a portion of the system level distributed ledger to a central node that maintains a separate secure distributed ledger. The master node may authenticate the control system based on the received portion of the system level distributed ledgers and the secure distributed ledgers.

An exemplary system may include a gas turbine engine configured to operate at an engine power level to satisfy an engine power demand. The system may also include at least one generator operatively coupled to the engine and configured to generate electrical power based at least in part on the engine power demand. The system further may include at least one heating element in communication with the at least one generator, and at least one control unit coupled to the at least one heating element. The at least one heating element may be configured to receive electrical power from the at least one generator to generate thermal energy. The at least one control unit may be configured to energize the heating element when the engine power demand is below the engine power level and/or there is an anticipated increase in the engine power demand.

A monitoring system that monitors a steam-using facility includes a temperature sensor that is a trap temperature sensor configured to detect a temperature of a steam trap provided in a steam discharge unit and/or a steam temperature sensor configured to detect a temperature of steam flowing into the steam trap and a pressure sensor configured to detect a pressure of steam flowing into the steam trap. The monitoring system determines that there is an occurrence of an abnormality or a sign of the abnormality in the steam trap when (i) a temperature detection value obtained by the temperature sensor and/or statistical temperature data obtained by performing statistical processing on the temperature detection value deviates from a predetermined criterion thereof and (ii) a pressure detection value obtained by the pressure sensor and/or statistical pressure data obtained by performing statistical processing on the pressure detection value deviates from a predetermined criterion thereof.

In a gas turbine and a control method thereof, and a combined cycle plant, the gas turbine includes a compressor that compresses air, a combustor that mixes and combusts compressed air compressed by the compressor and fuel, a turbine that obtains rotational power using combustion gas generated by the combustor, a compressed air cooling heat exchanger that cools the compressed air to produce air for heat exchange, air temperature adjusting heat exchangers that exchange heat between the air and the compressed air, a heat exchange amount adjusting device that adjusts a heat exchange amount of each of the compressed air cooling heat exchanger and the air temperature adjusting heat exchangers, and a control device that controls the heat exchange amount adjusting device, in which the control device controls the heat exchange amount adjusting device based on a temperature of the air to be taken into the compressor.

When the output power of a gas turbine is going to be reduced and when the relationship between the target output power and the rotational frequency of the gas turbine satisfies predetermined conditions, a control device of a power unit system reduces the output power of the gas turbine to the target output power and thereafter reduces the rotational frequency of the gas turbine to the target rotational frequency, whereas when the relationship between the target output power and the rotational frequency of the gas turbine does not satisfy the predetermined conditions, the control device reduces the rotational frequency of the gas turbine to the target rotational frequency and thereafter reduces the output power of the gas turbine to the target output power.

A gas turbine engine is provided having: a turbomachine; a fan section having a fan rotatable by the turbomachine; a nacelle enclosing the fan; and an engine controller positioned within the nacelle. The nacelle defines an inner surface radius (r) along the radial direction inward of the engine controller, wherein the engine controller defines a radial height (Δr) along the radial direction, a total volume (V), and a normalized radius (r′). The normalized radius (r′) is a ratio of the inner surface radius (r) to the total volume (V) to cube root, and wherein these parameters are related by the following equation: $0.1{\left(r^{\prime }\right)}^{-1}<\frac{\Delta r}{r}<{K\left(r^{\prime }\right)}^{-4/3},$
wherein the normalized radius (r′) is between 1.25 and 8 and K is equal to 40%, or the normalized radius (r′) is between 2.75 and 4.5 and K is equal to 65%.

A shaft assembly for use with a turbine engine includes a shaft and a magnetic mode control unit. The shaft extends along an axis and is configured to rotate about the axis. The magnetic mode control unit is configured to control deflection of the shaft as the shaft rotates about the axis.

A rotor for a gas turbine engine has: a first rotor disk; an interstage flange that extends from the first rotor disk to a flange end portion that has an axial end surface and first radial outer and inner surfaces; a circumferential groove, formed in the flange end portion and extending from the axial end surface toward the first rotor disk; radial outer and inner slots formed in the first radial outer and inner surfaces along the circumferential groove and extend through the first radial outer and inner surfaces; and a valve member disposed within the circumferential groove and is secured within the circumferential groove when the flange end portion is connected to a second rotor disk, wherein the valve member deflects from rotor rotational speeds to seal or unseal the radial outer slot.

A networked electronic ordnance system is provided. The system includes a first plurality of pyrotechnic devices connected to a first network bus. The system further includes a first bus controller connected to the first network bus. The system further includes a second plurality of pyrotechnic devices connected to a second network bus. The system further includes a second bus controller connected to the second network bus. The system further includes a bus interface circuit connected to the first bus controller by a first electrical connection and connected to the second bus controller by a second electrical connection.

A gas turbine engine is provided having: a turbomachine; a fan section having a fan rotatable by the turbomachine; a nacelle enclosing the fan; and an engine controller positioned within the nacelle. The nacelle defines an inner surface radius (r) along the radial direction inward of the engine controller, wherein the engine controller defines a radial height (Δr) along the radial direction, a total volume (V), and a normalized radius (r′). The normalized radius (r′) is a ratio of the inner surface radius (r) to the total volume (V) to cube root, and wherein these parameters are related by the following equation:

[00001]$0.1{\left(r^{\prime }\right)}^{-1}<\frac{\text{Δ}r}{r}<\text{K}{\left(r^{\prime }\right)}^{-4/3}.$

wherein the normalized radius (r′) is between 1.25 and 8 and K is equal to 40%, or the normalized radius (r′) is between 2.75 and 4.5 and K is equal to 65%.