An inner diffuser case for a turbine engine includes a fore gas path edge and an aft gas path edge defining a strut, wherein each of the fore gas path edge and the aft gas path edge include a gas path opening, a support cone structure extending radially outward from the strut, wherein the support cone structure is operable to structurally connect the strut to a turbine engine case, a diffuser case skirt structure extending radially inward from the strut, wherein the diffuser case skirt structure is operable to structurally connect the diffuser case strut to an inner support structure of the turbine engine, and at least one direct feed air passage passing radially through the strut including a radially outward upper mixing chamber opening and a radially inward direct air feed opening, the direct air feed opening is connected to a direct air feed.

An energy storage system is disclosed. The energy storage system includes a turbo train drive, a hot heat sink, and a reservoir. The turbo train drive is in mechanical communication with a compressor and an expander. The hot heat sink is in thermal communication between an output of the compressor and an input of the expander. The reservoir is in thermal communication between an output of the expander and an input of the compressor. The compressor and the expander, via the turbo train drive, are operable between a charging function for charging the hot heat sink and a discharging function for discharging the hot heat sink.

The invention relates to a container (200) for a heat storage and restitution system, comprising a vessel in which a gas is circulating in order to be cooled or heated. The vessel is limited by a first jacket formed from concrete (203) surrounded by a thermally insulating layer (206), which is itself surrounded by a steel shell (204). The vessel comprises at least two modules (210), each comprising a double wall formed from concrete and a perforated base (205) limiting at least two volumes (217 and 216) which are each capable of containing a fixed bed of particles of a material for storage and restitution of heat (207). The modules are disposed one above the other in a centered manner such that the double wall formed from concrete forms the first jacket formed from concrete (203) and a second jacket formed from concrete (215).

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.

In one aspect of the present disclosure, there is provided a gas turbine engine. The gas turbine engine includes a primary gas path having, in fluid series communication: an air inlet, a compressor fluidly connected to the air inlet, a combustor fluidly connected to an outlet of the compressor, and a turbine section fluidly connected to an outlet of the combustor section. In embodiments, a hydrogen expansion turbine is in fluid communication to receive hydrogen from the gaseous hydrogen outlet of the heat exchanger. In certain embodiments, the gas turbine engine includes a heat exchanger having a gas conduit fluidly connected to the primary gas path, and a fluid conduit in fluid isolation from the gas conduit and in thermal communication with the gas conduit.

A steam injected turbine engine includes a core engine section that generates a first gas flow, a burner where an inlet flow is mixed with fuel and ignited to generate thermal energy, and an evaporator where thermal energy from at least the first gas flow is used to transform water into a first steam flow. The first steam flow is injected into a core flow through the core engine.

A compressed air energy storage (CAES) power generation apparatus includes a motor driven by renewable energy, a compressor driven by the motor, a pressure accumulating tank storing compressed air compressed by the compressor, an expander driven by the compressed air from the pressure accumulating tank, and a generator connected to the expander. The apparatus includes a first heat exchanger that performs heat exchange between the compressed air from the compressor to the pressure accumulating tank and a heat medium, cools the compressed air, and heats the heat medium, a heat accumulating tank that stores the heat medium heated by the first heat exchanger, a second heat exchanger that performs heat exchange between the compressed air from the pressure accumulating tank to the expander, heats the compressed air, and cools the heat medium, and third heat exchangers that perform heat exchange between the exhaust heat outside a system and a fluid in the system. The power generation efficiency of the apparatus is improved using the exhaust heat outside the system while the exhaust heat outside the system is cooled using the cold heat generated in the system of the apparatus.

A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream most end, and more upstream locations. A turbine section has a high pressure turbine. A first tap taps air from at least one of the more upstream locations in the main compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger. A second tap taps air from a location closer to the downstream most end than the location(s) of the first tap. The first and second tap mix together and are delivered into the high pressure turbine. An intercooling system for a gas turbine engine is also disclosed.

A ventilation flow path, a cooling air flow path, a mixing space, and a mixed air flow path are formed in a gas turbine rotor. The ventilation flow path guides compressed air farther on an axially upstream side than an air discharge port of a compressor to an interior of a compressor rotor as compressor extracted air. The cooling air flow path guides cooling air to a part farther on an axially downstream side than the air discharge port. The compressor extracted air and the cooling air are mixed in the mixing space. The mixed air flow path guides mixed air containing the compressor extracted air and the cooling air into a turbine rotor.

A variable orifice flow device controls the flow of a fluid between a volute casing and a compressor motor casing in a compressor. The variable orifice flow device may be a shuttling valve, with positions controlled by, for example, valves controlling the flow of the fluid into a space opposite a side within the shuttling valve assembly. The variable orifice flow device may have one or more orifices through which a fluid can enter the compressor motor casing, and the surface area of the orifices may be controlled by the position of the shuttling valve.