Abstract: A first steam turbine and a second steam turbine of a combined cycle plant are connected by a reheat steam line via a reheat section of an exhaust heat recovery boiler. The reheat steam line and a condenser are connected by a second bypass line. A control device includes: a determination unit that determines whether or not the flow rate of first steam flowing into the first steam turbine has reached a stipulated flow rate; a command output unit that, upon determining that the flow rate of the first steam flowing into the first steam turbine has reached the stipulated flow rate, outputs a close command to close a ventilator valve that is provided in the second bypass line and is open; and a threshold alteration unit that alters the threshold with which the determination unit determines whether or not the stipulated flow rate has been reached, the threshold being positively correlated with a temperature of the first steam.

Abstract: A gearbox assembly for a gas turbofan engine includes a sun gear rotatable about an axis and a plurality of intermediate gears driven by the sun gear. A baffle disposed between at least two of the plurality of intermediate gears includes a first gap distance within a first gap portion and a second gap distance within a second gap portion. The first gap portion is disposed between the baffle and one of the intermediate gears away from the meshed interface with the sun gear and the second gap portion is disposed near the interface with the sun gear. The first gap distance within the first gap portion is different than the second gap distance within the second gap portion to define a desired lubricant flow path.

Abstract: A gas turbine system includes a turbine combustor, a turbine, an exhaust gas compressor, an exhaust gas recirculation (EGR) system, a carbon black recovery system, and a carbon black production controller. The carbon black production controller monitors data corresponding to a parameter of the carbon black. The carbon black production controller is also configured to adjust, based on the data, the fuel provided to the turbine combustor while maintaining a ratio of the fuel to the oxidant within a predetermined range to adjust the parameter of the carbon black.

Abstract: A method for starting a combustion system having a first ignition device and an at least second ignition device, a processing unit and a sensor system. To obtain a reliable ignition the method includes as a starting sequence at least the following: monitoring during a working condition of the combustion system, an operational state of the first and the at least second ignition device by the sensor system; identifying a predefined state of the first and/or the at least second ignition device by the processing unit; and as a further step: in case of an identification of the predefined state changing in at least one parameter of at least one of the ignition devices by the processing unit. A combustion system is equipped to be operable with the method as well as to a flow engine with such a combustion system.

Abstract: An adapter for a gas turbine engine has a first portion with a control module mount interface. A second portion with a sensor mount interface defines a sensor mount position relative to a control module. A connecting body connects the first and second portions such that the second portion provides a re-orientated sensor mount position relative to the control module. A lubrication system for a gas turbine engine is also disclosed.

Abstract: A fuel system for a gas turbine engine includes, among other things, a plurality of components defining a plurality of localized nodes at distinct locations relative to a fuel flow path, each of the plurality of localized nodes characterized by a distinct set of failure parameters. One or more fuel sensors are configured to measure at least one fuel condition relating to flow through the fuel flow path. A fuel observation assembly is coupled to one or more engine sensors configured to measure at least one engine condition.

Abstract: A module for a gas turbine engine comprises a frame and a frame cooling system. The frame includes a circumferentially distributed plurality of radially extending struts. Each strut is joined to an outer frame section at an outer frame junction, and joined to an inner frame section at an inner frame junction. The frame cooling system comprises an inlet, a plurality of cooling air passages extending from the inlet radially through each of the plurality of frame struts; and an outlet. The outlet is in fluid communication with at least one of the cooling air passages and includes a film cooling hole formed through the frame proximate the outer frame junction.

Abstract: A gas turbine engine that includes a compressor, a turbine, a heat exchanger, and a combustor. The compressor is mounted on a rotating shaft with at least one rotor with an inlet and an outlet, and at least one diffuser downstream from each rotor. The turbine includes at least one stator, and at least one rotor with an inlet and outlet located downstream of each stator, and mounted on the rotating shaft as the at least one of the compressor rotors. The inlet of the compressor rotor faces toward the outlet of the turbine rotor. The heat exchanger is configured to preheat the compressed air leaving the compressor by transferring heat from the turbine exhaust. The combustor can be configured for mixing fuel with the compressed air, either upstream or downstream from the heat exchanger, and further configured for igniting the preheated fuel/air mixture located downstream from the heat exchanger.

Abstract: Embodiments of a flow limiting duct vent valve (DVV) are provided, as are embodiments of a bleed air system including a flow limiting DVV. In one embodiment, the bleed air system a flow limiting DVV and a first valved device, such as a high pressure regulator. The DVV includes, in turn, a housing assembly having an inlet and an outlet. The inlet is fluidly coupled to the valved device when the bleed air system is installed on a gas turbine engine. A valve element is mounted in the housing assembly and, during operation of the DVV, moves from: (i) the closed position to an open vent position when the pressure differential across the valve element exceeds a first threshold, and (ii) from the open vent position to an overpressure shutoff position when the pressure differential across the valve element exceeds a second threshold greater than the first threshold.

Abstract: In one embodiment, a system includes a gas turbine system, having: a turbine driven by combustion products produced by a turbine combustion system; and a separation unit positioned between turbine stages of the turbine, wherein the separation unit separates oxygen out of the combustion products. The separation unit may include an ion transport membrane.

Abstract: A combustor is provided. The combustor may comprise a shell including a ceramic material. A gradient transition from ceramic to metal may have a predominantly ceramic side coupled to the shell. A metal mating surface may also be coupled to a predominantly metal side of the gradient transition from ceramic to metal.

Abstract: A combustor seal for use between a downstream end of a combustor and a turbine vane includes a seal body and a plurality of seal alignment features. The plurality of seal alignment features projects from the seal body. The seal alignment features are arranged such that there is only one alignment of the combustor seal with the turbine vane.

Abstract: A valve actuating device for variable valve control wherein at least one articulation point between a valve lever and a gas exchange valve, or a force transmission element which acts on the gas exchange valve, is adjustable by way of an adjusting device which includes a piston displaceably mounted in the valve lever, a piston rod which is connected to the piston is connected in an articulated manner at a first articulation point to a first end of a push rod whose second end is connected in an articulated manner at a second articulation point to the gas exchange valve, or the force transmission part which acts on the gas exchange valve, the first articulation point being displaced in the longitudinal direction of the piston rod at least between a first position and a second position.

Abstract: A diesel exhaust fluid (DEF) delivery system and method for operating same. The method includes determining, by an electronic processor, an operating pressure, and receiving, from a pressure sensor of the DEF delivery system, a system pressure. The method further includes determining, by the processor, a dosing request and a pressure disturbance based on the dosing request. The method further includes determining, by the processor, a control request based on the system pressure and the operating pressure, and a feed forward control value based on the pressure disturbance. The method further includes generating, by the processor, an adjusted control request based on the control request based and the feed forward control value. The method further includes controlling, by the processor, a dosing valve of the DEF delivery system based on the dosing request, and a pressure adjustment component of the DEF delivery system based on the adjusted control request.

Abstract: A method for monitoring a degree of clogging of the starting injectors of a turbine engine, which includes: a combustion chamber into which at least one starting injector supplied with fuel leads, the starting injectors being suitable for initiating the combustion in the chamber by igniting the fuel; and a turbine rotated by the gases resulting from the combustion of the fuel in the chamber, the method including the steps involving: the measurement, during a phase of starting the turbine engine, of the temperature of the exhaust gases at the outlet of the turbine; and the determination, from the changes over time in the temperature thus measured, of a degree of clogging of the starting injectors. A system for monitoring a degree of clogging capable of implementing the method, and a turbine engine including such a system.

Abstract: A fuel circuit of a turbomachine, this circuit including a fuel return valve connected to the main fuel circuit and to a tank, the valve being able to take a first and a second open position, separate from one another, and a closed position, two primary hydraulic lines connecting the valve to the main circuit and including, respectively, first and second filters through which the fuel passes when the valve is in its first open position, two secondary hydraulic lines which connect the valve to the main circuit and which are positioned in relation to the first and second filters in such a way that the circulation of fuel in these secondary lines contributes, respectively, to the cleaning of the first and second filters, the fuel circulating in the secondary lines when the valve is in its second open position.

Abstract: A hybrid adhesion system includes an adhesion head including at least one suction cup and a handle and a vacuum generator mechanically coupled to the adhesion head. The vacuum generator includes at least one pneumatic cylinder having an internal volume in fluid communication with the at least one suction cup and a piston having a piston rod mechanically coupled to a manual actuator.

Abstract: An adjustable camshaft can be used in valve drives of internal combustion engines, amongst other places. The adjustable camshaft may include an outer shaft and an inner shaft that is concentric with and rotatably supported in the outer shaft. A cam having a cam bore may be rotatably supported on an outer surface of the outer shaft so as to form a slide bearing gap between the cam and the outer shaft. The cam may be rotatably-fixed to the inner shaft so that the inner shaft and the cam rotate with one another. Furthermore, the adjustable camshaft may include an oil channeling groove disposed beneath the cam in the outer surface of the outer shaft. In many cases, at least one side of the oil channeling groove may be exposed such that it extends beyond the slide bearing gap and the cam.

Abstract: A rotor (1) for a vane cell adjuster of a camshaft adjusting device including a central through opening (10) and at least one radially outwardly projecting vane (2). The rotor (1) is made of at least two parts, an inner part (8) made of a first material and an outer part (3) made of a second material and which surrounds, from the outside, the inner part (8). The first material has a higher strength than the second material, and the inner part (8) is connected in a positive fit in the rotational direction of the outer part (3) by an outer form which is irregular in the cross-section to the rotational axis (14) of the rotor (1).

Abstract: An apparatus for providing improved cooling to a combustion liner of a gas turbine combustor is provided. A plurality of flow deflectors is secured to a flow sleeve in order to improve the flow of impingement air from a flow sleeve to the combustion liner outer surface, such that the amount of impingement air being swept away by a cross flow of cooling air is reduced.