Provided is a steam turbine plant activation control device that can flexibly handle an initial state amount of a steam turbine plant and activate a steam turbine at a high speed. The activation control device 21 for the steam turbine plant includes a heat source device 1 configured to heat a low-temperature fluid using a heat source medium and generate a high-temperature fluid, a steam generator 2 for generating steam by thermal exchange with the high-temperature fluid, a steam turbine 3 to be driven by the steam, and adjusters 11, 12, 13, 14, 15 configured to adjust operation amounts of the plant.

A system and method for predicting a remaining oil life of oil in a gearbox of an air turbine starter of a vehicle. The method includes generating a temperature data, generating an environmental data set by an environmental sensor, predicting a remaining oil life based on the temperature data set and the environmental data set and scheduling a maintenance event in response to the prediction of the remaining oil life.

A system and method for predicting a remaining oil life of oil in a gearbox of an air turbine starter of a vehicle. The method includes generating a temperature data, generating an environmental data set by an environmental sensor, predicting a remaining oil life based on the temperature data set and the environmental data set and scheduling a maintenance event in response to the prediction of the remaining oil life.

A disclosed turbofan engine includes a gas generator section for generating a gas stream flow and a propulsor section for generating propulsive thrust as a mass flow rate of air through a bypass flow path. The propulsor section includes a fan driven by a power turbine through a speed reduction device at a second rotational speed lower than a first rotational speed of the power turbine. An Engine Unit Thrust Parameter (“EUTP”) defined as net engine thrust divided by a product of the mass flow rate of air through the bypass flow path, a tip diameter of the fan and the first rotational speed of the power turbine is between 0.05 and 0.13 during operation of the turbofan engine.

A disclosed turbofan engine includes a gas generator section for generating a gas stream flow and a propulsor section for generating propulsive thrust as a mass flow rate of air through a bypass flow path. The propulsor section includes a fan driven by a power turbine through a speed reduction device at a second rotational speed lower than a first rotational speed of the power turbine. An Engine Unit Thrust Parameter (“EUTP”) defined as net engine thrust divided by a product of the mass flow rate of air through the bypass flow path, a tip diameter of the fan and the first rotational speed of the power turbine is between 0.05 and 0.13 during operation of the turbofan engine.

An engine system for an aircraft includes a first gas turbine engine, a first core turning system, a second gas turbine engine, and a second core turning system. The engine system also includes a controller operable to shutdown the first gas turbine engine responsive to determining that the aircraft has landed and operate in the second gas turbine engine in a taxi mode while using the first core turning system to cool the first gas turbine engine. The controller is further operable to shutdown the second gas turbine engine and disable the first core turning system based on a power-down condition, restart the first gas turbine engine and use the second core turning system to cool the second gas turbine engine based on a restart condition, and complete cooling of the second gas turbine prior to restarting the second gas turbine engine.

An engine system for an aircraft includes a first gas turbine engine, a second gas turbine engine, and a control system. The control system is configured to operate the first gas turbine engine with an idle fuel burn schedule in a taxi mode of the aircraft and dry crank the second gas turbine engine in a first pre-takeoff portion of the taxi mode to cool the second gas turbine engine absent fuel burn by the second gas turbine engine. The control system operates the second gas turbine engine with a sub-idle fuel burn schedule in a second pre-takeoff portion of the taxi mode of the aircraft. The sub-idle fuel burn schedule includes a reduction of the idle fuel burn schedule. A fuel flow of the first gas turbine engine and the second gas turbine engine is increased above the idle fuel burn schedule prior to takeoff of the aircraft.

Suitability of an operational state of a steam-using equipment is accurately estimated to allow for early detection of a sign of abnormality in the steam-using equipment. A steam-using facility monitoring system (M) comprised of a steam-using equipment (4) includes a control state detector (D1) that detects a state of a steam controller (1) provided in a steam pipe (2) accompanying the steam-using equipment (4), and an operational state estimating means (S) having a signal input unit (S1) that inputs a detection signal (σi) from the control state detector (D1) and an operational state estimation unit (S2) that estimates the operational state of the steam-using equipment (4) based on one inputted detection signal (σi) or a preset particular combination of detection signals (σi).

Suitability of an operational state of a steam-using equipment is accurately estimated to allow for early detection of a sign of abnormality in the steam-using equipment. A steam-using facility monitoring system (M) comprised of a steam-using equipment (4) includes a control state detector (D1) that detects a state of a steam controller (1) provided in a steam pipe (2) accompanying the steam-using equipment (4), and an operational state estimating means (S) having a signal input unit (S1) that inputs a detection signal (σi) from the control state detector (D1) and an operational state estimation unit (S2) that estimates the operational state of the steam-using equipment (4) based on one inputted detection signal (σi) or a preset particular combination of detection signals (σi).

This steam turbine blade is provided with: a blade body (61) extending in a radial direction and having an airfoil profile in a cross section perpendicular to the radial direction; and a heater (H) including a heating wire disposed so as to extend along a trailing edge (Er) of the airfoil profile in the blade body (61). This configuration makes it possible to further mitigate an efficiency drop due to moisture attached to the surface of the steam turbine blade (60).