Abstract: A system for managing thermal transfer in at least one of an aircraft or a gas turbine engine includes a first engine system utilizing an oil for heat transfer. The oil of the first system has a temperature limit of at least about 500° F. The system additionally includes a fuel system having a deoxygenation unit for deoxygenating fuel in the fuel system, as well as a fuel-oil heat exchanger located downstream of the deoxygenation unit. The fuel-oil heat exchanger is in thermal communication with the oil in the first engine system and the fuel in the fuel system for transferring heat from the oil in the first engine system to the fuel in the fuel system.

Abstract: A first jet tab and a second jet tab are symmetrically arranged with respect to a symmetry plane and have a symmetrical shape with respect to the symmetry plane, and are symmetrically driven with respect to the symmetry plane by a driving section. A distance between a tip of the first jet tab and a first rotation axis is larger than a distance between the first rotation axis and the symmetry plane. A distance between a tip section of the second jet tab and a second rotation axis is larger than a distance between the second rotation axis and the symmetry plane.

Abstract: A gas turbine engine includes an engine core outer casing and a fan nacelle spaced radially outwardly relative to the engine core outer casing to define a bypass duct. A plurality of drag links is used to pivot blocker doors into a flow blocking position in the bypass duct when a thrust reverser is deployed. The plurality of drag links is located within the bypass duct in an area of non-uniform flow defined by a plurality of local airflow angles. Each drag link is individually configured to align with one of the local flow angles.

Abstract: A gas turbine combustion chamber with a combustion chamber wall and with at least one shingle that is fastened to the combustion chamber wall at a distance from the same, wherein the shingle has a shingle edge that abuts the combustion chamber wall, wherein the combustion chamber wall and the combustion chamber shingle respectively have at least one mixed air hole, and wherein a tubular fastening element provided with a ring flange is inserted through the mixed air hole of the combustion chamber wall, abutting the side of the combustion chamber wall that is facing away from the combustion chamber shingle with the ring flange, characterized in that, at its exterior side, the fastening element is provided with first snap-in means that are in mesh with second snap-in means that are formed at a tubular snap-in element that braces the combustion chamber shingle against the combustion chamber wall.

Abstract: An axial fuel staging injector for a gas turbine includes a body. The body includes an upstream end and a downstream end. The body defines a primary compressed air flow path through which compressed air flows from a compressed air source to a transition duct of a gas turbine combustor. The body includes a plurality of outlets disposed on an interior surface thereof. Each outlet of the plurality of outlets includes a secondary fuel conduit in fluid communication with a secondary fuel source, and includes a first wall that defines a secondary fuel path. The secondary compressed air conduit is in fluid communication with a compressed air source, and includes a second wall disposed about the first wall in a substantially coannular arrangement, wherein the first wall and the second wall define a secondary compressed air flow path.

Abstract: A method of power production using a high pressure/low pressure ratio Brayton Power cycle with predominantly N2 mixed with CO2 and H2O combustion products as the working fluid is provided. The high pressure can be in the range 80 bar to 500 bar. The pressure ratio can be in the range 1.5 to 10. The natural gas fuel can be burned in a first high pressure combustor with a near stoichiometric quantity of pressurized preheated air and the net combustion gas can be mixed with a heated high pressure recycle N2+CO2+H2O stream which moderates the mixed gas temperature to the value required for the maximum inlet temperature to a first power turbine producing shaft power.

Abstract: The disclosed embodiments relate to a system and method that allows air to be extracted from a plurality of gas turbine engines and fed to a downstream process, even in situations in which one or more of the gas turbine engines are operating in a part load condition. For example, in an embodiment, a method includes monitoring signals representative of a header pressure of a header, or a pressure of extraction air flow from one or more gas turbine engines to the header, or both, and maintaining substantially continuous flows of extraction air from the gas turbine engines to the header. The substantially continuous flows are maintained when the gas turbine engines are under symmetric and asymmetric load conditions.

Abstract: An example thrust reverser blocker door includes a blocker door that is movable from a stowed position to a deployed position. Flow moves through an area of a bypass flowpath when the blocker door is in the stowed position. The blocker door blocks no less than about 70% and no more than about 85% of flow through this area when the blocker door is in the deployed position, wherein the area does not extend circumferentially past the blocker door.

Abstract: The exhaust system (60) includes an exhaust flow path liner (62) surrounded and supported by a plurality of structural duct segments (64, 70). Pluralities of links (84) are secured to and extend between the duct segments (64, 70) and the liner (62). A duct end (88) of the link includes a lock member (96) having a diameter greater than a width of the stem (86). The lock member (96) is configured to be secured within a capture nest (98) defined between and within adjacent junction flanges (76, 80} of the structural duct segments {64, 70) when the segments (64, 70) are secured to each other to secure the segments (64, 70) together. A catch member (100) at an opposed end of the link (84) is secured to a capture node (102) at the exhaust liner (62).

Abstract: Various embodiments include a system having: at least one computing device configured to monitor a combined-cycle (CC) power plant during a transient event by performing actions including: determining whether a change in an operating condition of a component of the CC power plant is unintentional, the determining including comparing control system instructions for the component of the CC power plant with a reference look-up table, the reference look-up table including correlation data for the control system instructions for the component and historical data about the operating condition of the component; and providing instructions to a control system of the CC power plant to modify the operating condition in the CC power plant in response to determining that the change in operating condition of the component is unintentional.

Abstract: A combustor arrangement includes a combustion chamber with a front panel, and a premix burner of the multi-cone type, which is connected to the front panel through an elongated mixing zone in an axially moveable fashion by a sealed sliding joint. A wide range of axial variation of the burner with a minimized influence of the leakage air flow on the oxidation process within the flame is achieved by positioning the sealed sliding joint upstream of the mixing zone.

Abstract: A seasonal process that captures stores and uses water in an ambient temperature-dependent manner to improve the efficiency of a natural gas power plant, comprising: (a) providing a natural gas power plant, the natural gas power plant having a flue gas stream, a cooling tower, and a gas turbine; (b) providing a water collection system; (c) providing a water storage facility; wherein the flue gas stream comprises uncondensed water vapor; wherein the water collection system is operably connected to the flue gas stream and the flue gas stream is directed to flow, at least in part, into the water collection system; wherein the water collection system is operably connected to the water storage facility; wherein the water storage facility is operably connected to the cooling tower and the water storage facility is operably connected to the gas turbine; wherein the process comprises the following steps of condensing flue gas water or using water that has been condensed from the flue gas stream based on outdoor ambie

Abstract: A power plant (1) that includes at least one of a gas turbine (GT), a steam turbine (ST) with a water-steam cycle, and a heat recovery steam generator (B) operatively connected to a heat generating member such as solar energy system (Ssolar) by means of a primary circuit (10a, 10b, 10c) and a secondary circuit system (20a). The primary heat transfer circuit (10a, 10b) includes solar heating system (Ssolar) configured to heat a primary fluid (10), and the secondary circuit (20a) comprises a flow line (20A) for a secondary flow (20) and a main heat exchanger (23) to exchange heat between the secondary water flow and a gas turbine inlet air flow (2). A first line (10B) in the primary circuit (10b) leads to a first heat exchanger (12) to heat the water flow in the secondary circuit (20a).

Abstract: An object of the present invention is to provide a method and a system for implementing the method so as to alleviate the disadvantages of a reciprocating combustion engine and gas turbine in electric energy production. The invention is based on the idea of arranging a combustion chamber (10) outside a gas turbine (22) and providing compressed air to the combustion chamber (10) in order to carry out a combustion process in controlled and optimal conditions.

Abstract: The described method of supplying fuel to an internal fuel manifold of a bypass gas turbine engine includes directing a fuel flow through a fuel fairing having an outer surface exposed to a cool bypass airflow, directing the fuel flow in the fuel fairing through a heat exchanging structure on the outer surface of the fuel fairing to cool the fuel flow being below a coking temperature of the fuel, and then feeding the cooled fuel flow from the fuel fairing to the internal fuel manifold.

Abstract: The invention relates to a bypass turbojet comprising an exhaust housing having a central hub (13) and connecting means (11) that can transmit the forces generated by the turbojet to the structure of the aircraft that it propels, said connection means being two arms extending radially from the central hub in order to cross the cold flow of said turbojet and being characterized in that they are secured to said central hub and positioned in a diametrically opposed manner in relation to each other. An additional connection means (14) extends between the hub (13) and the area (9) for securing the exhaust housing to the structure (12) of the aircraft in order to transmit the exceptional dimensioning loads, said connection means being on standby during normal use, without any transmission of force between said hub and said area.

Abstract: Various embodiments include a system having: at least one computing device configured to monitor a combined-cycle (CC) power plant during a transient event by performing actions including: determining whether a change in an operating condition of a component of the CC power plant is unintentional, the determining including comparing control system instructions for the component of the CC power plant with a reference look-up table, the reference look-up table including correlation data for the control system instructions for the component and historical data about the operating condition of the component; and providing instructions to a control system of the CC power plant to modify the operating condition in the CC power plant in response to determining that the change in operating condition of the component is unintentional.

Abstract: A gas turbine engine assembly comprising, a gearbox including a first housing that includes a first auxiliary gear drive on a first portion thereof, a second housing that includes a second auxiliary gear drive on a second portion thereof, and a third housing that includes a third auxiliary gear drive on a third portion thereof, the housings being interconnected so that the first portion of the first housing, the second portion of the second housing and the third portion of the third housing form a substantially triangular polyhedron shape, with the second portion of the second housing disposed between the first portion of the first housing and the third portion of the third housing. The first auxiliary gear drive, the second auxiliary gear drive and the third auxiliary gear drive project outwardly in mutually divergent directions.

Abstract: In one or more of the inventive aspects, when a gas turbine system of a power plant operates at part load, a moisture content of fuel gas provided to the gas turbine system may be controlled so as to minimize combustion dynamics and/or to comply with emission requirements. The fuel gas moisture content may be controlled by modulating a flow of heated water to a fuel moisturizer. By using heated water from a heat recovery steam generator to moisturize the fuel gas, heat energy from the water may be transferred to the fuel gas, and the overall mass flow may be enhanced to thereby increase overall combined cycle efficiency.

Abstract: A combustion chamber arrangement including an outer wall and an inner wall spaced from the outer wall and the outer wall supports the inner wall. The inner wall including at least one row of circumferentially arranged tiles. At least one tile in the at least one row of tiles having an L, or V, shaped downstream end and the downstream end of the tile in the row of tiles having a first portion extending from the downstream end of the tile towards and sealing with an inner surface of the outer wall and a second portion extending from the first portion in a downstream direction and away from the inner surface of the outer wall. The first portion of the downstream end of the tile having a plurality of apertures to supply coolant over an inner surface of the second portion of the downstream end of the tile.