Abstract: A method for protecting a gas turbine installation from overheating and for detecting flame extinction in the combustion chamber is described, in which air is compressed in a compressor unit and, after being admixed with fuel, is ignited in the form of a fuel/air mixture in a combustion chamber and is burnt, thus giving rise to a hot gas flow which sets a turbine stage in rotation downstream of the combustion chamber so as to perform expansion work. The pressure upstream of the turbine stage, that is to say the pressure pk of the compressed air in the plenum and/or the pressure within the combustion chamber pcom, is measured, in that a time change of the measured pressure, what is known as the pressure gradient ({dot over (p)}), is determined, in that at least one threshold value is selected, and in that the pressure gradient or a variable derived from the pressure gradient is compared with the at least one threshold value and, if the threshold value is overshot or undershot, a signal is generated.

Abstract: A turbomachine blade, in particular a turbine blade of a gas turbine includes a blade root with a cooling-fluid feed, a blade tip formed with a shroud element. At least one throughflow passage which extends in the blade longitudinal direction is arranged inside the airfoil. A shroud cooling passage is formed in the shroud element at least along a section of the latter, the shroud cooling passage being connected via an opening to the throughflow passage, and a cooling fluid flowing through this shroud cooling passage during operation of the turbomachine blade. At least one flow-guiding element for guiding at least some of the cooling-fluid flow flowing through the shroud cooling passage is arranged in the shroud cooling passage and/or in an inflow or outflow to or from the shroud cooling passage.

Abstract: A hot gas duct, such as a combustion casing in a gas turbine engine, includes a duct splitter held within the hot gas duct in at least three, preferably four, locations spaced around a peripheral edge of the duct splitter. At least one, preferably two, of the holding locations each comprise a generally cylindrical mounting that projects through a wall of the hot gas duct to engage an edge portion of the duct splitter by means of a slot formed in a circular face of the mounting. Mutually contacting surfaces of the slot and the duct splitter comprise hard face coatings to combat wear due to vibration and differential thermal expansion and contraction. The mountings have cooling holes that penetrate the mounting, so that coolant can flow through the mountings and into the interior of the hot gas duct to cool the mountings and the hard face coatings.

Abstract: A sorbent conditioning and feed apparatus for a circulating fluidized bed combustion system includes a dryer apparatus configured to dry unprocessed sorbent material transported thereto from a raw storage container; a sorbent crushing device configured to reduce the particle size of dried sorbent material discharged from the dryer apparatus; and a circulating fluidized bed (CFB) boiler configured to receive processed sorbent material conveyed from the sorbent crushing device; wherein the dryer apparatus utilizes an untempered hot air source diverted directly from a primary air stream input to the circulating fluidized bed boiler.

Abstract: A premixing burner is disclosed for operating a combustion chamber with a liquid and/or gaseous fuel, with a swirl generator for a combustion inflow air stream for forming a swirl flow, and with injection of fuel into the swirl flow. The swirl generator is adjacent to the combustion chamber indirectly via a mixing zone or directly, in each case via a burner outlet, a cross-sectional widening at the burner outlet being provided which, is discontinuous in the flow direction of the swirl flow and through which the swirl flow bursts open so as to form a backflow zone. A contour locally narrowing the flow cross section of the swirl generator or of the mixing zone in the flow direction can be provided upstream of the burner outlet.

Abstract: A secondary air flow biasing apparatus for a CFB combustion system includes a sorbent feed path configured to convey processed sorbent particles to a CFB furnace by utilizing a portion of secondary combustion air supplied to the furnace; a first air injection port disposed within a wall of a lower portion of the furnace, at a first elevation above a primary air distribution grate of the furnace; a second air injection port disposed within the wall of the lower portion of the furnace, at a second elevation above the first elevation; and an air/sorbent separation device in fluid communication with the sorbent feed path, the separation device configured to separate a substantial portion of the secondary combustion air from the processed sorbent particles such that a relatively lean sorbent-to-air mixture is introduced through the second air injection port and a relatively rich sorbent-to-air mixture is introduced through the first air injection port.

Abstract: A system & Method for Preventing Scaling in a Flue Gas Desulphurization System is provided. The system includes an injector configured to direct a barrier fluid toward a surface that is otherwise susceptible to scaling when it comes in contact with super-saturated alkaline solutions such as slurry used to capture CO2 from a flue gas stream.

Abstract: A premix burner has a swirl generator and two perforated through flow elements are arranged at a defined distance from one another in the inflow region for the combustion air. The through flow elements are preferably arranged in such a way that substantially the entire combustion airstream has to flow through the through flow elements. The degree of perforation of the through flow elements and the distance between these elements are preferably adapted to one another in such a way that a reflection free condition for combustion pulsation frequencies which may be expected is present at the exit from the burner into the combustion chamber.

Abstract: A thermal turbomachine is disclosed having at least one row of rotor blades. At least one first rotor blade has a greater radial length than the others and at the blade tip is equipped with a first abrasive layer. At least one rotor blade which has a shorter radial length than the first rotor blade is equipped with a second abrasive layer at the blade tip. The first abrasive layer has a better cutting capacity and a lower thermal stability than the second abrasive layer. During commissioning of the thermal turbomachine, the first abrasive layer is in contact with the abradable layer of the stator, and during continuous operation of the thermal turbomachine the second abrasive layer is in contact with the abradable layer of the stator.

Abstract: A lance for introducing fuel into a combustion chamber of a burner, in particular of a turbine plant is provided. The lance includes a lance head, a fuel feed, an oxidator feed and a control device. The lance head projects into the combustion chamber and includes a fuel nozzle and an oxidator outlet orifice. The fuel feed extends in the lance and is connected to the fuel nozzle. The oxidator feed extends in the lance head and is connected to the oxidator outlet orifice. The control device controls a flow cross sectional area of the oxidator feed. The control device has a control piston installed in the lance head with stroke adjustability for stroke-dependent controlling of the flow cross sectional area of the oxidator feed.

Abstract: A method used for combustion of a fuel-oxidizer mixture in a combustion chamber of a turbogroup, in particular of a power plant wherein total oxidizer flow is divided into a main oxidizer flow and a secondary oxidizer flow. The main oxidizer flow is lean mixed with a main fuel flow in a premix burner, and the mixture is fully oxidized in the combustion chamber. The secondary oxidizer flow is divided into a pilot oxidizer flow and a heat-exchanging oxidizer flow. The pilot oxidizer flow is rich mixed with a pilot fuel flow, and the mixture is partially oxidized in a catalyst, with hydrogen being formed. Downstream of the catalyst, the partially oxidized pilot fuel-oxidizer mixture and the heat-exchanging oxidizer flow are together introduced into at least one zone which is suitable for stabilizing the combustion of the main fuel-oxidizer mixture.

Abstract: A sealing element for sealing a component gap with respect to a flow, in particular for use in a fluid-flow machine, specifically in a turbomachine is provided. In addition a fluid-flow machine is provided including such a sealing element for sealing a component gap. The sealing element includes a hollow profile enclosing a cavity. Arranged in the hollow profile are a first opening and a second opening, which are spaced apart from each other in the longitudinal direction of the hollow profile. The first opening is formed as an inlet opening for a cooling fluid into the cavity of the hollow profile, the second opening is formed as an outlet opening for the cooling fluid from the cavity of the hollow profile. With the sealing element arranged in a fluid-flow machine, the sealing element can consequently be internally cooled by means of the cooling fluid. Furthermore, the sealing element uses the pressure gradient occurring in the flow in the direction of flow to form a stable cooling fluid flow.

Abstract: A device (1) for the feed of air to a compressor (2) of a gas turbine plant has an air inlet duct (8) and an air inlet chamber (9) which adjoins the air inlet duct. For the purpose of damping sound emissions of the compressor (2), a first and second inner wall (10, 11) of the inlet chamber (9) is at least partially lined by means of melamine foam. The invention is characterized by the advantages in that silencing is ensured both with wetness and with chemically aggressive conditions. The silencing device is consequently functionally reliable over an extended operating period.

Abstract: A method for the acceleration of an electromagnetic rapper, particularly for an electrostatic precipitator, which includes a metal cylinder as a hammer, an electrical coil for lifting the metal cylinder and a coil energizer for energizing the electrical coil. For cleaning a surface the metal cylinder is lifted by an initial electrical pulse generated by the coil energizer. The coil energizer supplies the electrical coil with an additional electrical pulse so that the metal cylinder is accelerated when it has reached the maximum point of its trajectory.

Abstract: A guide vane arrangement of a turbomachine includes a casing, at least one guide vane carrier connected to the casing and having a first carrying portion and a second carrying portion spaced apart axially from the first carrying portion, a plurality of guide vanes connected to the guide vane carrier and arranged next to each other in a circumferential direction, and at least one securing element connected to the guide vane carrier and configured to provide an axial fixing of at least one of the guide vanes. Each guide vane has a platform including a first locking portion and a second locking portion spaced apart axially from the first locking portion, wherein each of the first and second locking portions and the respective first and second carrying portion are adapted to provide an axially pluggable and a radially positive fastening between the guide vane carrier and the respective guide vane.

Abstract: A waste heat boiler includes an axial bypass pipe and multiple heat transfer pipes disposed within a cylindrical jacket. A hot exhaust gas stream transported between inlet and outlet ends of the heat transfer pipes is cooled by a coolant. A control system controls gas passage velocity and quantity of the exhaust gas stream through the bypass pipe whereby the exhaust gas stream exhaust temperature is maintained within a predetermined temperature range. The control system includes a stopper disposed at the outlet end of the bypass pipe and has a head plate extending into the outlet end of the bypass pipe. The stopper is axially displaceable from a closed position, where an outer surface of the stopper head plate contacts an inner surface of the bypass pipe outlet end. The gas passage formed between the inner surface of the bypass pipe outlet end and the outer surface of the stopper head plate has a cross-section that increases as the stopper is axially displaced from the closed position.

Abstract: A composite component (1), such as a turbine airfoil, includes a conductive portion (2), and a non-conductive portion (5), such as a thermal barrier coating or a wear protection coating, or both. In machining the component, a laser machining step is applied for machining the non-conductive portion, and an electro-machining step is applied for machining the conductive portion. The laser machining step is performed by applying preferably a high-frequency pulsed laser. The focussed laser beam working diameter (DL) is essentially smaller than the size of the contour (16) to be machined. The contour is scanned by the laser beam (9) along a pre-defined trace (17) thus literally inscribing the desired contour into the workpiece.

Abstract: In a fuel lance by means of which fuels can be injected, via at least two separate passages, into a combustion chamber alternately or simultaneously at an injection location arranged substantially at the lance tip, reliable operation is achieved, without the risk of flashbacks and also without coking, by virtue of the fact that the fuel lance, in addition to fuel, also passes purge air to the injection location, and that the purge air, at the injection location, is routed between the two fuel systems, in such a manner that these systems are shielded from one another by the purge air.

Abstract: A method for treating a thermally loaded component having a metallic substrate and at least partially coated on an outer side with a protective coating, is provided. The method includes the step of predamaging the protective coating before removing the protective coating from the substrate using dry ice blasting. The predamaging is performed so as to lead to an increase of efficiency of the removal process.

Abstract: A gas turbine has a cooling air passage which extends along the leading edge of the blade airfoil, which cooling air passage has an outlet opening which is arranged in the region of the blade tip. The contour of the outlet opening is geometrically similar to the cross section of the cooling air passage. As a result, flow inhomogeneities of the cooling air flow, which locally negatively influence heat transfer, and consequently cooling efficiency, are avoided.