A combined cycle power plant including a gas turbine engine having a compressor inlet and a turbine outlet that is configured to discharge a first exhaust gas stream therefrom. A heat recovery steam generator is configured to receive the first exhaust gas stream, extract heat from the first exhaust gas stream to make steam, and discharge a second exhaust gas stream therefrom. A steam turbine is configured to discharge a steam stream therefrom, a carbon capture system is configured to receive the steam stream, a recirculation blower is configured to pressurize a portion of the second exhaust gas stream for recirculation towards the compressor inlet, and an air inlet blower is configured to pressurize an airflow stream channeled towards the compressor inlet, such that a pressurized mixed flow stream, formed from the portion of the second exhaust gas stream and the airflow stream, is received at the compressor inlet.

There is provided a system and a method for operating a multi-engine rotorcraft. When the rotorcraft is cruising in an asymmetric operating regime (AOR) at least one engine is an active engine and is operated in an active mode to provide motive power to the rotorcraft and at least one second engine is a standby engine and is operated in a standby mode to provide substantially no motive power to the rotorcraft, at least one of a power level of the at least one second engine is increased and at least one variable geometry mechanism of the at least one second engine is moved to shed any ice accumulation on the at least one second engine.

Wind funnel and gas combustion turbine systems are disclosed. Air travels through a wind funnel where it is compressed, and then flows into a compression section of a gas turbine that is fueled by a hydrocarbon fuel source such as natural gas. Compressed air from the wind funnel enters the compressor section of the gas turbine at relatively high density and force, and then flows to the combustion section of the gas turbine where oxygen from the wind-compressed air is used to combust the hydrocarbon fuel supplied to the gas turbine. The combustion section drives a power output generator having first and second generators that are selectively engageable and disengageable from each other. During periods when compressed air from the wind funnel is delivered to the compression section of the gas combustion turbine, the first and second generators may be drivingly engaged with each other by a generator coupling mechanism.

The present disclosure provides methods and systems for operating a rotorcraft comprising a plurality of engines configured to provide motive power to the rotorcraft. A request to enter into an asymmetric operating regime (AOR), in which at least one first engine of the plurality of engines is an active engine and is operated in an active mode to provide motive power to the rotorcraft and at least one second engine of the plurality of engines is a standby engine and is operated in a standby mode to provide substantially no motive power to the rotorcraft, is obtained. A power capability of the active engine of the rotorcraft is determined. The power capability is compared to a current power demand for the rotorcraft. When the current power demand is greater than the power capability of the active engine, a standby-engine power output of the standby engine of the rotorcraft is reduced, and the reduction in the standby-engine power output is compensated for by adjusting an active-engine power output of the active engine and/or at least one flight control of the rotorcraft.

An engine compressor bleed system of an engine for an aircraft is provided including a plurality of compressor pressure ports configured to supply bleed air to satisfy a cooling load for at least a first stage of a flight profile of an aircraft. A first pressure port of the plurality of compressor pressure ports is configured to provide bleed air having a pressure at least equal to a cabin pressure of an aircraft and a temperature that does not exceed a predetermined threshold.

The gas turbine engine can have an engine core; a core output shaft drivable by the engine core; a power output shaft; an auxiliary power shaft; and a reduction gearbox having gears, the gears drivingly connecting the core output shaft to the auxiliary power shaft. The gears can include an epicyclic gearing drivingly connecting the core output shaft and the auxiliary power shaft to the power output shaft. The gas turbine engine can further have a second auxiliary power shaft interconnected to the auxiliary power shaft, the power output shaft, and the core output shaft by the gears.

A pericritical fluid system for a thermal management system associated with a turbine engine may include one or more sensors configured to generate sensor outputs corresponding to one or more phase properties of a pericritical fluid flowing through a cooling circuit of the thermal management system, and a controller configured to generate control commands configured to control one or more controllable components of the thermal management system based at least in part on the sensor outputs. The one or more sensors may include one or more phase detection sensors, such as an acoustic sensor.

Vehicles, such as aircraft, may include turbine-based combined cycle power plants (TBCC) for power to achieve high-mach speeds. An anti-unstart configuration provides control for transitioning between the amount of air directed to either engine during operation of gas turbine engine and scramjet engines, to avoid unstart during operation above sonic speeds.

Wind funnel and gas combustion turbine systems are disclosed. Air travels through a wind funnel where it is compressed, and then flows into a compression section of a gas combustion turbine that is fueled by a hydrocarbon fuel source such as natural gas. Compressed air from the wind funnel may enter the compression section at selected locations. The compression section may have a front relatively low compression section and a downstream relatively higher compression section, and the compressed air from the wind funnel may be selectively delivered to one or both of the lower and higher compression sections. In addition, ambient air may be introduced into the lower compression section. During periods when compressed air from the wind funnel is delivered to the downstream higher compression section, the front lower compression section may be decoupled from the downstream section.

Wind funnel and gas combustion turbine systems are disclosed. Air travels through a wind funnel where it is compressed, and then flows into a compression section of a gas turbine that is fueled by a hydrocarbon fuel source such as natural gas. Compressed air from the wind funnel enters the compression section of the gas turbine through one or more air inlets toward multiple rotating turbine blades in an air feed direction having a component normal to air impact surfaces of the turbine blades. In addition to the compressed air from the wind funnel, ambient air may be introduced into the compression section of the gas combustion turbine.