A gas turbine engine includes a main compressor section with a downstream most location. A turbine section has a high pressure turbine. A tap line is connected to tap air from a location upstream of the downstream most location in the main compressor section. The tapped air is connected to a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and is connected to deliver air into the high pressure turbine. A bypass valve is positioned downstream of the main compressor section, and upstream of the heat exchanger. The bypass valve selectively delivers air directly to the cooling compressor without passing through the heat exchanger under certain conditions.

A low emission, high efficiency Gas Turbine engine operating on a combination of Natural Gas and Bio Gas as fuel, driving either a high efficiency turbo-blower or a high efficiency Turbo Pump system combined with heat recovery systems and in other embodiments is provided a generator of electricity or providing evaporate cooling from using the remaining waste heat in the exhaust gas.

A gas turbine engine system includes a gas turbine engine and a fuel turbine system. The gas turbine engine includes an air inlet, compressor, combustor, turbine, and heat exchange system. The heat exchange system is configured to transfer thermal energy from an inlet air flow or exhaust air flow to a fuel to produce a gaseous fuel that is used to drive a fuel turbine and fuel pump and used for combustion in the gas turbine engine. The fuel turbine is in fluid communication with the heat exchange system and the combustor and configured to extract energy from expansion of the gaseous fuel. The fuel pump is configured to be driven by the fuel turbine and is in fluid communication with the heat exchanger system.

A heat exchanging arrangement is integrated within a gas turbine engine case that at least partially encloses a gas turbine engine. The gas turbine engine has an upstream end and a downstream end which are defined by a core fluid flow through the gas turbine engine. The heat exchanging arrangement includes at least one flow passage defined within the gas turbine engine case having an inlet port and an outlet port. The at least one flow passage is configured to direct at least a portion of a fluid flowing through the gas turbine engine from between a downstream position and an upstream position while traveling between the inlet port and the outlet port.

A propulsion system for an aircraft includes a gas generating core engine that generates an exhaust gas flow that is expanded through a turbine section. A power turbine engine is forward of the core engine and is coupled to drive a propulsor. A hydrogen fuel system supplies hydrogen fuel to the combustor through a fuel flow path. A condenser extracts water from the exhaust gas flow. A water separator is in communication with the condenser and directs the extracted water to a water storage tank. An evaporator receives a portion of the water that is extracted by the condenser and generates a steam flow. The steam flow is injected into the core flow path upstream of the turbine section.

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 multi-stage turboexpander and a method for generating mechanical power therewith are disclosed. The multi-stage turboexpander includes a casing and a shaft, arranged for rotation in the casing. The shaft is supported by a first bearing at a first shaft end portion and a second bearing at a second shaft end portion. A first radial impeller and a second radial impeller are arranged between the first bearing and the second bearing on the shaft for co-rotation therewith around a rotation axis.

A compressor, a first heat exchanger, a first heat storage unit, a pressure accumulation unit, a second heat exchanger, and a second heat storage unit are provided. The first heat storage unit and the second heat storage unit are connected by a first flow passage and a second flow passage. The first and second flow passages are connected by a third flow passage. A first on-off means is provided in a first region of the first flow passage and a second on-off means is provided in a second region. A third on-off means is provided in a third region of the second flow passage, and a fourth on-off means is provided in a fourth region. A driving means and a heating means are provided in the third flow passage.

The present invention discloses embodiments for a power augmentation system of a gas turbine engine resulting in performance improvements while also improving efficiency. The invention provides systems and methods for generating a heated air supply by way of mixing compressed air from an electrically-driven process with air drawn from the engine compressor discharge plenum.

The high pressure compressor wheel of a two stage turbocharger assembly is cooled by charge air bled from the charge air flowpath downstream of the aftercooler. A wastegate may be arranged across the high pressure stage and operated by an actuator which in turn is operable by the static or dynamic pressure of the charge air in the cooling flowpath. The cooling airflow may be blocked to open the wastegate and released or resumed to close the wastegate so that cooling air is supplied only while the high pressure compressor wheel is under load.