A system includes an engine configured to generate power to drive a load. The system also includes a power augmentation system configured to augment a power output of the engine when the power augmentation system is activated. Additionally, the system includes a controller operatively coupled to the power augmentation system. The controller is configured to estimate a potential change in the power output of the engine caused by activation of the power augmentation system using a power augmentation model and an engine performance model.

A gas turbine having a wet compression device which allows droplets of an aqueous liquid mixture to be introduced into a compressor of the gas turbine during operation of the gas turbine, the aqueous liquid mixture containing at least one surfactant. The aqueous liquid mixture additionally contains at least a defoaming agent, and the gas turbine has a second metering device, which is designed to feed a predetermined quantity of defoaming agent into water which is provided for use in the wet compression device.

A gas turbine engine includes a compressor, a cooling source, and a thermoelectric intercooler adapted for selective operation in response to operational states of the gas turbine engine.

An intercooler for a gas turbine engine can include a shell having a partial annular shape, the shell defining a duct comprising an inlet and an outlet, the shell defining a first flow path between the inlet and the outlet; a supply manifold disposed proximate the outlet of the duct and extending circumferentially around the shell; and an outlet manifold disposed proximate the inlet of the duct and extending circumferentially around the shell, the supply manifold in fluid communication with the outlet manifold through a heat transfer region in the duct.

A propulsion system for an aircraft includes a core engine that generates a core gas flow, a propulsor section that is driven by the core engine and disposed aft of the core engine, a nacelle that surrounds the core engine and the propulsor section, a water recovery system that is disposed in the nacelle, an exhaust duct where the core gas flow is directed radially outward from the core engine to the nacelle, an evaporator assembly that is in thermal communication with the exhaust duct where water is recovered by the water recovery system and is heated to generate a steam flow that is subsequently communicated to the core engine.

Systems, apparatuses and methods (utilities) for use in internally cooling an centrifugal compressor of a gas turbine engine so as to approximate isothermal compression and thereby increase the power and/or efficiency of the engine. In one arrangement, a centrifugal housing having fluid or coolant paths is provided to absorb heat or thermal energy generated while compressing intake air.

A system includes a gas turbine engine, including a compressor, a combustor, and a turbine. The system includes an intercooler configured to receive a discharge air from the compressor and to cool the discharge air. The system includes a first conduit to divert a portion of the cooled discharge air from the intercooler or a location downstream of the intercooler to a bearing located within the turbine to pressurize the bearing to block leakage of fluid from the bearing.

A system includes an intercooler configured to flow a working fluid and compressed air of a gas turbine engine through the intercooler to exchange heat between the working fluid and the compressed air. The system also includes a multi-effect distillation system configured to flow the working fluid and a mixture to exchange heat between the working fluid and the mixture to enable distillation of the mixture.

A gas turbine engine includes a compressor section, a combustor fluidly connected to the compressor section via a primary flowpath and a turbine section fluidly connected to the combustor via the primary flowpath. Also included is a cascading cooling system having a first inlet connected to a first compressor bleed, a second inlet connected to a second compressor bleed downstream of the first compressor bleed, and a third inlet connected to a third compressor bleed downstream of the second compressor bleed. The cascading cooling system includes at least one heat exchanger configured to incrementally generate cooling air for at least one of an aft compressor stage and a foremost turbine stage relative to fluid flow through the turbine section.

A cooling system is provided. The cooling system may comprise a heat exchanger and a first conduit fluidly coupled to an outlet of the heat exchanger. An annular passage may be fluidly coupled to the first conduit. A tangential onboard injector (TOBI) may be fluidly coupled to the annular passage. A gas turbine engine is also provided and may comprise a compressor, a combustor in fluid communication with the compressor, and a diffuser around the combustor and a turbine. A heat exchanger may have an inlet fluidly coupled to the diffuser. A second conduit may be fluidly coupled to an outlet of the heat exchanger. An annular passage may be fluidly coupled to the second conduit. A tangential onboard injector (TOBI) may be fluidly coupled to the annular passage.