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).

A device for cooling of an annular wall of a turbomachine combustion chamber provided with micro-perforations, and in particular the cooling of a region of the wall facing a wake induced by an ignition plug, the device includes, a deflector designed to divert air immersing the ignition plug towards a median plane of the wake and towards the annular wall of the combustion chamber, so as to increase the air pressure within the wake in proximity to the annular wall.

This IGCC plant is provided with an ASU which separates oxygen gas and nitrogen gas from air, a coal gasification furnace which uses an oxidizing agent to gasify coal, and a gas turbine which is driven by the combustion gas resulting from burning a gas generated by means of the coal gasification furnace. This IGCC plant control device (50) is provided with an air separation amount determination unit (52) which determines the production amount of nitrogen gas produced by the ASU depending on the operating load of the IGCC plant, and supplies to the coal gasification furnace the entire amount of oxygen gas generated as a byproduct in response to the determined nitrogen gas production amount. By this means, the IGCC plant can minimize blow-off of oxygen gas produced from the air.

A gas turbine engine includes a housing includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A rotor is connected to the hub and supports a compressor section. The geared architecture includes an epicyclic gear train. A fan is rotationally driven by the geared architecture. First and second bearings support the shaft relative to the intermediate case and the inlet case, respectively. The radially inner boundary of the core inlet is at a location of a core inlet stator and the radially inner boundary of the compressor section inlet is at a location of the first stage low-pressure compressor rotor.

A bundled tube fuel nozzle includes a forward plate, an intermediate plate, an aft plate and an outer sleeve. The forward plate, the intermediate plate and the outer sleeve define a fuel plenum therebetween. An aft plate axially is spaced from the intermediate plate and the intermediate plate, the aft plate and the outer sleeve define a cooling air plenum. A plurality of tubes extends through the forward plate, the fuel plenum, the intermediate plate, the cooling air plenum and the aft plate. Each tube of the plurality of tubes extends through a respective tube opening defined by the aft plate. A radial gap is defined between an outer surface of each tube and an inner surface of the respective tube opening. The plurality of tubes comprises at least one tube that is radially loaded against the inner surface of the respective tube opening.

A gas turbine system includes a combustor configured to combust an oxidant and a fuel in the presence of an exhaust gas diluent to produce combustion products, an oxidant supply path fluidly coupled to the combustor and configured to flow the oxidant to the combustor at an oxidant flow rate, and a turbine configured to extract work from the combustion products to produce an exhaust gas used to generate the exhaust gas diluent. The turbine causes a shaft of the gas turbine system to rotate when the work is extracted from the combustion products. The system also includes an electrical generator that generates electrical power in response to rotation by the shaft, and a controller that performs load control in response to a target load by adjusting the oxidant flow rate along the oxidant flow path as a primary load control parameter.

A nozzle guide is provided for a combustor of a gas turbine engine. The nozzle guide includes an annular structure including a plurality of cooling holes, a guide plate including a plurality of openings on an outer periphery of the guide plate, and a plurality of cooling passages within the annular structure to provide air flow from the plurality of cooling holes to the plurality of openings.

A turbine power generation system with enhanced stabilization of refractory carbides provided by hydrocarbon from high carbon activity gases is disclosed. The disclosure also includes a method of using high carbon activity gases to stabilize hot gas path components.

An airblast fuel injector for a gas turbine engine fuel spray nozzle has, in order from radially inner to outer, a coaxial arrangement of an inner air swirler passage, an annular fuel passage, an annular outer air swirler passage, and an annular shroud air swirler passage. The injector further has an annular shroud having an inner surface profile. Relative to the overall axial direction of flow through the injector the shroud inner surface profile has a convergent section followed by a divergent section, the transition of which forming a first inwardly directed annular nose. The injector further has an annular wall having an outer surface profile, and having an inner surface profile. Relative to the overall axial direction of flow through the injector the wall outer surface profile has a convergent section followed by an outwardly turning section which faces across the shroud air passage to the first nose.

A system is provided with a turbine combustor having a first diffusion fuel nozzle, wherein the first diffusion fuel nozzle has first and second passages that separately inject respective first and second flows into a chamber of the turbine combustor to produce a diffusion flame. The first flow includes a first fuel and a first diluent, and the second flow includes a first oxidant. The system includes a turbine driven by combustion products from the diffusion flame in the turbine combustor. The system also includes an exhaust gas compressor, wherein the exhaust gas compressor is configured to compress and route an exhaust gas from the turbine to the turbine combustor along an exhaust recirculation path.