Abstract: The thrust reverser includes a reverser cowl of which a downstream part of the reverser cowl forms a jet nozzle, cascade vanes fixed upstream from the reverser cowl, thrust reverser flaps, and an actuator. The thrust reverser is translatable under an effect of the actuator between a folded position of the thrust reverser flaps for operation of the nacelle in a direct jet mode, and a deployed position of the thrust reverser flaps for operation of the nacelle in a reverse jet mode. In particular, the stretching of the actuator results in causing a variation in a nozzle section of the jet nozzle as long as the stretching is below a predetermined value, and exposing the cascade vanes and deploying the thrust reverser flaps so as to perform the reverse jet mode beyond the predetermined value.

Abstract: To provide a multifuel gas turbine combustor capable of combusting gases containing hydrogen in a high concentration with a low NOx while maintaining a low emission performance brought about by the pre-mixture combustion in the main burner, the gas turbine combustor includes a main burner (12) for supplying to and combusting a premixed gas (M), containing a first fuel (F1), within a first combustion region (S1) of a combustion chamber (10), and a supplemental burner (20) for supplying to and combusting a second fuel (F2) of a composition different from that of the first fuel (F1) within a second combustion region (S2) defined downstream of the first combustion region (S1) within the combustion chamber (10). The first fuel (F1) is of a hydrocarbon system and the second fuel (F2) is a gas containing hydrogen in a concentration exceeding the stable combustion limiting concentration of the hydrogen.

Abstract: An inlet particle separator system for a vehicle engine includes a hub section, a shroud section, a splitter, and a hub suction flow passage. The shroud section surrounds at least a portion of the hub section and is spaced apart therefrom to define a main flow passageway that has an air inlet. The splitter is disposed downstream of the air inlet and extends into the passageway to divide the main flow passageway into a scavenge flow path and an engine flow path. The hub suction flow passage has a hub suction inlet port and a hub suction outlet port. The hub suction inlet port extends through the hub section and is in fluid communication with the air inlet. The hub suction outlet port extends through the splitter and is in fluid communication with the scavenge flow path.

Abstract: Methods and apparatus for an oxy-fuel combustion power cycle are provided, including converting gaseous carbon dioxide to liquid and/or supercritical carbon dioxide which may include the use of a cryogenic pump, removing a portion of the liquid and/or supercritical carbon dioxide from the cycle, combusting oxygen and a combustion fuel with the remaining liquid and/or supercritical carbon dioxide in an oxy-fuel combustor to generate steam and additional liquid and/or supercritical carbon dioxide which replaces the portion of the liquid and/or supercritical carbon dioxide sequestered from the cycle.

Abstract: A system for reducing emissions includes a gas production source that produces nitrogen oxides, sulfur oxides, hydrogen sulfide, sulfuric acid, nitric acid, formaldehyde, benzene, metal oxides, or volatile organic compound emissions. An exhaust plenum is downstream from the gas production source, and structure for dispersing a solvent is in the exhaust plenum. A collection tank is in fluid communication with the exhaust plenum to receive the solvent from the exhaust plenum, and a heat source is in the exhaust plenum downstream from the structure for dispersing the solvent. A method for reducing emissions from a gas production source includes flowing exhaust gases through an exhaust plenum, dispersing a solvent through a nozzle in the exhaust plenum, collecting the dispersed solvent in a collection tank, and heating the exhaust gases flowing through the exhaust plenum downstream from the nozzle.

Abstract: A fuel nozzle for a combustor includes a burner tube and a center nozzle assembly disposed within the burner tube. The center nozzle assembly includes a center body that at least partially defines a cooling air flow passage through the center nozzle assembly. A premix flow passage is defined between the burner tube and the center nozzle assembly. A tip assembly is disposed at a downstream end of the center body. The tip assembly includes an impingement plate, and a cap that is disposed downstream from the impingement plate. The impingement plate and the cap at least partially define a cooling plenum therebetween. An insert passage extends through the impingement plate and a cooling flow outlet extends through the cap. A plurality of cooling ports extends through the impingement plate to provide for fluid communication between the cooling air flow passage and the cooling plenum.

Abstract: A gas turbine engine and method for operating a gas turbine engine includes compressing an air stream in a compressor and combusting the compressed air stream to generate a post combustion gas. The post combustion gas is expanded in a first turbine. The expanded combustion gas exiting the first turbine is split into a first stream, a second stream and a third stream in a splitting zone including one or more aerodynamically shaped flow diverters. The first stream of the expanded combustion gas is combusted in a reheat combustor. An outer liner and flame stabilizer of the reheat combustor are cooled using the second stream of the expanded combustion gas. An inner liner of the reheat combustor is cooled using the third stream of the expanded combustion gas and a portion of the second stream of the expanded combustion gas passing through the one or more flame stabilizers.

Abstract: A flexible shield for fluid connectors of a gas turbine engine is disclosed. The flexible shield may comprise a flexible sleeve adapted to surround the fluid connector, and a coupling configured to secure the flexible sleeve onto a fluid tube proximate the fluid connector. A gas turbine engine employing such a flexible shield is also disclosed, as is a method of enclosing a fluid connector in a gas turbine engine using such a flexible shield.

Abstract: A seal end attachment is provided and includes a vessel through which a working fluid flows, the vessel being formed to define a recess with a mating surface therein, a seal contacting the mating surface and a pressing member being more responsive to a high temperature condition associated with the flow of the working fluid than the vessel and being disposed within the recess to press the seal against the mating surface responsive to the condition being present.

Abstract: An attemperation system and an atomizing air system are integrated for a combined cycle turbine including a gas turbine and a steam turbine. The atomizing air system receives compressor discharge air for fuel atomization. The atomizing air system includes an atomizing air cooler that serves to cool the compressor discharge air. A heat recovery steam generator receives exhaust from the gas turbine and generates steam for input to the steam turbine via an attemperation system. A feed water circuit draws feed water from the heat recovery steam generator and communicates in a heat exchange relationship with the atomizing air cooler to heat the feed water. The feed water circuit communicates the heated feed water to the attemperation system of the heat recovery steam generator.

Abstract: A reliable and flexible black start network restoration for a combined cycle power plant can be achieved by synchronizing a steam turbine and ramping that steam turbine up to an operating point where a maximum power increase is achieved. The resulting steam turbine load change can be compensated by the gas turbine. The increase in the demanded load can be provided by the steam turbine. The load of the steam turbine can also be gradually reduced to increase its load-increasing capacity.

Abstract: A combustor apparatus defining a combustion zone where air and fuel are burned to create high temperature combustion products. The combustor apparatus comprises an outer wall including a fuel inlet opening for receiving a fuel feed pipe. A coupling assembly is engaged with the fuel feed pipe at the fuel inlet opening to attach the fuel feed pipe to the outer wall. A fuel injection system is located in the interior volume of the outer wall and comprises fuel supply structure including a fuel feed block having a fuel intake passage aligned with the outlet portion of the fuel feed pipe. A coupling fastener is engaged against an exterior outer face of the fuel feed block to create a sealed coupling for containing fuel passing from the fuel feed pipe into the fuel feed block, and to secure the fuel feed block relative to the coupling assembly.

Abstract: A method is disclosed for operating a gas turbine power plant having a gas turbine, a heat recovery steam generator and an flue gas splitter which splits flue gases into a first flue gas flow for recirculation into an inlet flow of the gas turbine and into a second flue gas flow for discharge to an environment. An oxygen-depleted gas can be used in an open cooling system for cooling hot gas parts of the gas turbine. A split compressor intake can be provided for separate feed of recirculated flue gas and fresh air into a compressor intake. Compressor blades can include a separating band which blocks intermixing of recirculated flue gas and fresh air during compression.

Abstract: A midframe portion (313) of a gas turbine engine (310) is presented and includes a compressor section with a last stage blade to orient an air flow (311) at a first angle (372). The midframe portion (313) further includes a turbine section with a first stage blade to receive the air flow (311) oriented at a second angle (374). The midframe portion (313) further includes a manifold (314) to directly couple the air flow (311) from the compressor section to a combustor head (318) upstream of the turbine section. The combustor head (318) introduces an offset angle in the air flow (311) from the first angle (372) to the second angle (374) to discharge the air flow (311) from the combustor head (318) at the second angle (374). While introducing the offset angle, the combustor head (318) at least maintains or augments the first angle (372).

Abstract: A variable geometry (2) structure comprising: an flexural element (4); a tensioning element (6) connected to the flexural element (8); and an actuator (12) for adjusting the tensioning element (6) to change the load placed on the flexural element (4), thereby changing the geometry of the structure (2).

Abstract: A resonator device is provided for damping a pressure oscillation within a combustion chamber. The resonator device may comprise: a container filled with a gas; an opening in the container; and a heating element adapted to generate a flame. The flame is arranged to heat the gas within the container. The resonator device is comprised in a combustion arrangement comprising a combustion chamber for defining a combustion space for burning fuel. The container is connected to the combustion chamber such that an inside of the container is in communication with the combustion space via the opening. The resonator device has a resonance frequency equal to a pressure oscillation frequency within the combustion chamber under normal load conditions.

Abstract: First and second combustors are provided, and each combustor includes a fuel nozzle and a combustion chamber downstream from the fuel nozzle. Each fuel nozzle includes an axially extending center body, a shroud that circumferentially surrounds at least a portion of the center body, and vanes that extend radially between the center body and the shroud. A first fuel port through at least one of the vanes is located at a first axial distance from the combustion chamber, a second fuel port through the center body is located at a second axial distance from the combustion chamber, and the vanes are located at a third axial distance from the combustion chamber. The system varies one or more of the first, second, and third axial distances from combustor-to-combustor to produce a combustion instability frequency in the first combustor that is different from the combustion instability frequency in the second combustor.

Abstract: A preassembled modular drop-in transition having internal components in conformity with assembly and function specifications prior to and after insertion into an industrial gas turbine access port. The transition assembly maintains conformity with those specifications after insertion into the combustor case if it does not inadvertently impact other turbine components during its installation. Inadvertent impact is avoided by having a combustor service zone proximal the combustor case, enabling slidable insertion of each transition and/or combustor assembly into its corresponding access port along its corresponding insertion path without contacting other turbine system components. A multi-axis motion transition handling tool (THT) in the combustor service zone, preferably under automatic control, is coupled to a transition and facilitates precise alignment along the insertion path.

Abstract: A reaction turbine has channels formed in the top surface of a disc to create nozzles. The channels can be covered by a membrane sealed to the disc or by the housing extended from a combustor. Each channel may have a first section extending radially outwardly from an inlet of the reaction turbine and a second curved section extending from the first section to a periphery of the disc. A reaction turbine may also receive input from an impulse turbine. Fluid flows through the impulse turbine and fluid from the impulse turbine enters an inlet of the reaction turbine. The reaction turbine may have cooling channels and cooling fins to lower the temperature of the disc during operation. In addition, magnets may provide bearing support and electricity generation. In addition, the reaction turbine may have a dual shaft construction, with each shaft connected to a reaction turbine. One reaction turbine powers a compressor, while the second reaction turbine powers a load through the second shaft.

Abstract: A fuel system comprises a fuel actuation arrangement 28 operable to split a metered flow of fuel into at least a first stream and a second stream, a control unit 25 controlling the operation of the fuel actuation arrangement 28, and wherein the control unit 25 controls the operation of the fuel actuation arrangement 28 in response to the output of a temperature sensor 34 sensitive to a gas temperature downstream of the high pressure compressor 14 of an associated engine and the output of a gas sensor 24 sensitive to at least one parameter of the composition of a gas downstream of a combustor 15 of the engine.