A variable geometry turbine (VGT) comprising an intake channel, a rotor, an adjustable nozzle, a nozzle actuator, and a controller. The controller comprises a calibration routine, arranged for calibrating the VGT during normal operation thereof. In the calibration routine, the controller is arranged for performing the steps of: adjusting the adjustable nozzle from an initial position towards a closed position, while monitoring a pre-turbine pressure; detecting a deflection point position of the adjustable nozzle at which a sharp difference in the pre-turbine pressure occurs; and adjusting a minimum cross sectional area in the closed position, to adjust a working range of the VGT in dependence of varying operating conditions, wherein the working range excludes the detected deflection point position.

A steam turbine include a steam chest casing that is provided with a plurality of nozzle openings along a circumferential direction; a partition wall to partition the steam chest casing into the main steam chest and a sub-steam chest with smaller capacity than the main steam chest; a main steam pipe that supplies steam to the main steam chest; a steam chest connection pipe that distributes part of the steam, which is supplied to the main steam chest, to the sub-steam chest; a steam chest connection valve; a pressure gauge that measures the pressure of the steam flowing in the main steam pipe; and a control unit that closes the steam chest connection valve when the measured pressure is less than more than or equal to a predetermined threshold value, and opens the steam chest connection valve when the measured pressure is less than the predetermined threshold value.

A system and method of monitoring for sand plugging in a gas turbine engine includes sensing differential pressure across a combustor during engine operation. The sensed differential pressure is processed to determine an amount of sand plugging of combustor cooling holes, and an alert is generated when the amount of sand plugging exceeds a predetermined threshold.

A method for determining an engine heath of an aircraft engine includes determining, by one or more control devices, the aircraft engine is operating in a bleed off condition; determining, by the one or more control devices, a first engine health modifier value while the aircraft engine is operating in the bleed off condition, the first of engine health modifier value including a compressor leakage flow value; determining, by the one or more control devices, a second plurality of engine health modifier values while the aircraft engine is operating in a bleed on condition; and determining, by the one or more control devices, an engine health parameter using at least one of the second plurality of engine health modifier values determined while the aircraft engine is operating in the bleed on condition and the compressor leakage flow value determined while the aircraft engine was operating in the bleed off condition.

An apparatus and method of controlling a multi-stage compressor of a gas turbine engine having a front-block of stages with variable stator vanes (VSVs), a rear block of stages downstream of the front-block, and a bleed air off-take from at least one of the stages. The method includes sensing the pressure of the bleed air from the bleed air off-take and adjusting the position of the VSV for the front-block.

A rotary machine system includes: a rotary machine including a gas seal portion; a gas seal device connected to the rotary machine and that supplies a seal gas to the gas seal portion; and a connecting pipe that connects the gas seal portion and the gas seal device. The rotary machine includes a casing through which a working fluid flows; a rotatable rotary shaft; and the gas seal portion that seals the working fluid by the seal gas having a pressure higher than a pressure of the working fluid in the casing. The gas seal device includes: a seal gas supply pipe through which the seal gas delivered to the connecting pipe flows; a pressure regulating valve provided in the seal gas supply pipe and that adjusts the pressure of the seal gas supplied to the gas seal portion; and a control part.

A bleed air control system is configured to vary the air pressure at the inlet of a gas turbine engine. The bleed air control system includes a first gas turbine engine configured to provide bleed air, a second gas turbine engine acting as an auxiliary power unit, and a bleed air control system configured to selectively provide bleed air from the first gas turbine engine to the second gas turbine engine.

A pressure and temperature probe includes a probe head, a probe tip extending from the probe head and ending with a sensor face, a pressure channel extending into the probe tip through the sensor face, and a temperature channel extending into the probe tip through the sensor face. A pressure sensor is in fluid communication with a pressure channel and a temperature sensor in fluid communication with the temperature channel. The temperature channel extends parallel to the pressure channel, and the temperature channel is fluidly separate from the pressure channel. The sensor face can be configured to minimally intrude the flowpath of a working fluid, thereby minimizing disruption of the flowpath. The probe can be configured on a gas turbine engine.

A control device that controls a fuel gas supply system that has: a compressor that supplies compressed fuel gas to a load apparatus; an inflow amount regulating means that regulates the amount of fuel gas that flows into the compressor; an anti-surge valve that is for returning to an inlet side of the compressor fuel gas that is discharged from the compressor; and an inlet pressure-regulating valve that regulates the pressure of fuel gas supplied toward the inflow amount regulating means. The control device includes: a main pressure-regulating unit that controls the inflow amount regulating means and the anti-surge valve using a first feedforward control value that is generated on the basis of the load of the load apparatus and of a first conversion process and using a feedback control value that is generated on the basis of the deviation between a set value and a measured value for the discharge pressure of the compressor; and an inlet pressure-regulating unit that controls the inlet pressure-regulating valve using a second feedforward control value that is generated on the basis of the load of the load apparatus and of a second conversion process.

A method for determining mechanical degradation of parts of a centrifugal pump having a fluid inlet, an impeller, and a fluid outlet. The method includes calculating at least one of a wear-ring clearance effect and an impeller wear effect. The wear-ring clearance effect is calculated using measurements of an actual pump flow rate Qp and actual pump power Pwp, calculating an internal flow rate of the pump Qp.sub.Pwp, calculating the mechanical power Pw.sub.Qp that should be used if the pump worked as specified in a theoretical curve, and calculating a difference between a theoretical Head and an internal Head Hp.sub.th?Hp.sub.Pwp to obtain the loss of Head due to the wear-ring clearance. The impeller wear effect is calculated by measuring an actual input pressure p.sub.in, an actual output pressure p.sub.out and an actual pump power Pwp, calculating a theoretical flow rate QpPwp corresponding to the measured mechanical power Pwp, calculating a theoretical Pump Head HpPwp, calculating the actual Pump Head Hp from the actual input pressure p.sub.in, and the actual output pressure p.sub.out and a pumped fluid density, and calculating a difference between the theoretical pump head and the actual pump Head HpPwp?Hp to obtain the loss of head due to the impeller wear.