Abstract: In some examples, a processor may access past order information for a plurality of merchants to determine, for an upcoming time period, a number of orders predicted to be received by the merchants. The processor may determine geographic locations of delivery agent devices, each associated with a respective delivery agent. The processor may compare, for the upcoming time period, a number of active delivery agents with the number of orders predicted to be received. Based at least on determining a predicted shortage of active delivery agents for the upcoming time period, the processor selects a first delivery agent of the plurality of delivery agents to pick up a first order from a first pickup location of a first merchant and a second order from a second pickup location of a second merchant, and sends a message to a first delivery agent device associated with the first delivery agent.

Abstract: A combustion chamber of a gas turbine combusts a fuel in the presence of combustion air. The combustion chamber is configured as dual-fuel combustion chamber, wherein the combustion chamber, in a gas fuel operating mode, is supplied with a mixture of a gaseous fuel and combustion air via a main swirl body. In a liquid fuel operating mode, the combustion chamber is supplied with a liquid fuel via an atomization apparatus and combustion air via the main swirl body. The atomization apparatus has an atomization lance with an atomization nozzle centrally arranged with respect to a longitudinal center axis of a prechamber of the combustion chamber. The atomization nozzle of the central atomization lance includes a swirl chamber and, downstream of the swirl chamber, a nozzle orifice. The swirl chamber is supplied with the liquid fuel via a radial swirl generator and an axial swirl generator.

Abstract: A combustion chamber assembly of a gas turbine, for combusting a fuel in the presence of combustion air, includes: a combustion chamber, in which combustion of fuel occurs; a precombustion chamber upstream of the combustion chamber; an atomization device that feeds a liquid fuel to the precombustion chamber; and a swirl body that feeds combustion air and gaseous fuel to the precombustion chamber. The combustion chamber assembly is configured as a dual-fuel combustion chamber assembly, which, in a gas fuel operating mode, feeds a mixture of a gaseous fuel and combustion air to the combustion chamber via the swirl body, and which, in a liquid fuel operating mode, feeds liquid fuel to the combustion chamber via the atomization device and combustion air to the combustion chamber via the swirl body. The atomization device includes an atomization lance with a central atomization nozzle, and plural decentralized atomization nozzles.

Abstract: A combustion chamber assembly of a gas turbine, for combusting a fuel in the presence of combustion air, is configured as a dual-fuel combustion chamber assembly. In a gas fuel operating mode a mixture of a gaseous fuel and combustion air is supplied to the combustion chamber via a swirl body. In a liquid fuel operating mode liquid fuel is fed to the combustion chamber via a fuel lance and combustion air is fed to the combustion chamber via the swirl body. The fuel lance is surrounded by an adjoining lance cap to form a radial clearance therebetween such that the combustion chamber is feedable with combustion air via the radial clearance, bypassing the swirl body.

Abstract: A sealing segment for sealingly connecting two structural components parts which are movable relative to one another, with two sealing bodies which are connected to one another by a web and which can be arranged in recesses of the structural component parts in an articulated manner, and a sealing segment arrangement with a plurality of sealing segments of this type, and a flow machine with a sealing segment arrangement of this type.

Abstract: Combustor for a turbine having a housing in which an air collecting chamber, a combustion antechamber, and a combustion chamber are formed. A combustor head plate is arranged in the housing so that the combustor head plate separates the combustion antechamber from the combustion chamber. A baffle plate is arranged in the combustion antechamber so that the baffle plate divides the combustion antechamber into a first sub-chamber adjoining an air supply fluidically connected with the air collecting chamber and a second sub-chamber adjoining the combustor head plate. Wherein baffle plate has a plurality of through-passages that fluidically connect the first sub-chamber with the second sub-chamber so that air that has flowed into the first sub-chamber from the air collecting chamber via the air supply can flow into the second sub-chamber via the through-passages and to a back surface of the combustor head plate facing the second sub-chamber.

Abstract: A burner for a turbine has a flame tube, a casing enclosing the flame tube forming an oxidant collection chamber, a burner bottom which bounds the oxidant collection chamber and the combustion space, and a swirler which has a plurality of guide vanes arranged so that the distances between the guide vanes form a plurality of radial inlet passages to the combustion space. A fuel supply pipe is provided in the inlet flow region of at least some of the inlet passages, which fuel supply pipe extends lengthwise through the respective inlet passage in an axial direction of the burner and traverse to an oxidant flow direction, and wherein each fuel supply pipe has in its wall at least one radial fuel output opening by which fuel can be mixed into the respective inlet passage with a directional component extending transverse to the oxidant flow direction.

Abstract: Combustor for a turbine, and gas turbine outfitted with a combustor. The combustor has a housing in which an air collecting chamber, a combustion antechamber, and a combustion chamber are formed. A combustor head plate is arranged in the housing so that the combustor head plate separates the combustion antechamber from the combustion chamber. A baffle plate is arranged in the combustion antechamber so that the baffle plate divides the combustion antechamber into a first sub-chamber adjoining an air supply fluidically connected with the air collecting chamber and a second sub-chamber adjoining the combustor head plate. Wherein baffle plate has a plurality of through-passages that fluidically connect the first sub-chamber with the second sub-chamber so that air that has flowed into the first sub-chamber from the air collecting chamber via the air supply can flow into the second sub-chamber via the through-passages and to a back surface of the combustor head plate facing the second sub-chamber.

Abstract: A sealing segment for sealingly connecting two structural components parts which are movable relative to one another, with two sealing bodies which are connected to one another by a web and which can be arranged in recesses of the structural component parts in an articulated manner, and a sealing segment arrangement with a plurality of sealing segments of this type, and a flow machine with a sealing segment arrangement of this type.

Abstract: A method for operating a furnace with a multi-burner system for generating a hot gas is provided. The furnace has a combustion chamber with a plurality of burners, each having a fuel feed. The method includes regulating a first fuel feed to at least one of the plurality of burners as a function of pressure pulsations that occur in the combustion chamber so as to achieve a steady operation of the furnace. The multi-burner system may be a gas turbine, preferably of a power plant.

Abstract: A premix burner includes a swirler (7) for a combustion air stream and a device for injection of fuel into the combustion air stream. The swirler (7) includes one or more inlet openings for combustion air of the combustion air stream entering the burner. The device for injection of fuel into the combustion air stream includes one or more first fuel lines (8) with first fuel injection openings (4). The opening diameter and/or the injection angle of the injection openings varies with respect to the axial and/or radial direction. Alternatively or in addition, some of the first fuel injection openings (4) may be arranged in one or more first groups of closely grouped fuel injection openings (4) so that each of the first groups forms one fuel jet with a large cross section. An improved mixing of the fuel with the combustion air is achieved with the burner in particular in cases in which the fuel is injected at the end of the burner facing the combustion chamber.

Abstract: The present invention relates to a burner, substantially comprising a swirl generator for a combustion air stream and means for introducing fuel into the combustion air stream, the swirl generator having combustion-air inlet openings for the combustion air stream that enters the burner, and the means for introducing fuel into the combustion air stream comprising one or more first fuel feeds having a group of first fuel outlet openings, arranged distributed around the burner axis at a combustion chamber-side end of the burner. The burner is distinguished by the fact that the one or more first fuel feeds having the group of first fuel outlet openings are mechanically decoupled from the swirl generator. The present burner allows reliable and safe use of synthesis gas in both dilute and undiluted form as fuel.

Abstract: The invention relates to a method for operating a furnace with a multi-burner system for generating hot gas, particularly a gas turbine, preferably of a power plant, comprising a combustion chamber (1) with at least one burner (2). In order to operate the combustion chamber (1) in a stable manner close to the lean extinguishing limit, the fuel feed to at least one burner (2) is regulated as a function of the pressure pulsations that occur in the combustion chamber (1) in order to achieve a steady operation of the gas turbine.

Abstract: A premix burner includes a swirler (7) for a combustion air stream and a device for injection of fuel into the combustion air stream. The swirler (7) includes one or more inlet openings for combustion air of the combustion air stream entering the burner. The device for injection of fuel into the combustion air stream includes one or more first fuel lines (8) with first fuel injection openings (4). The opening diameter and/or the injection angle of the injection openings varies with respect to the axial and/or radial direction. Alternatively or in addition, some of the first fuel injection openings (4) may be arranged in one or more first groups of closely grouped fuel injection openings (4) so that each of the first groups forms one fuel jet with a large cross section. An improved mixing of the fuel with the combustion air is achieved with the burner in particular in cases in which the fuel is injected at the end of the burner facing the combustion chamber.

Abstract: The present invention relates to a burner, substantially comprising a swirl generator for a combustion air stream and means for introducing fuel into the combustion air stream, the swirl generator having combustion-air inlet openings for the combustion air stream that enters the burner, and the means for introducing fuel into the combustion air stream comprising one or more first fuel feeds having a group of first fuel outlet openings, arranged distributed around the burner axis at a combustion chamber-side end of the burner. The burner is distinguished by the fact that the one or more first fuel feeds having the group of first fuel outlet openings are mechanically decoupled from the swirl generator. The present burner allows reliable and safe use of synthesis gas in both dilute and undiluted form as fuel.

Abstract: In a method for operating a premix burner a water quantity is introduced into at least one of the burner and the reaction zone of the burner depending on at least one command variable formed from at least one measured value. The method can also be used if a burner is operated dry, i.e., without water injection for nitrogen oxide injection, and the injected water quantity is less than 20% of the fuel quantity. The method can be used advantageously especially if a characteristic value derived from combustion pulsations or material temperatures is used as a command variable. The method enables measured parameters to be kept below a permissible upper limit.

Abstract: In a method for operating a premix burner a water quantity is introduced into at least one of the burner and the reaction zone of the burner depending on at least one command variable formed from at least one measured value. The method can also be used if a burner is operated dry, i.e., without water injection for nitrogen oxide injection, and the injected water quantity is less than 20% of the fuel quantity. The method can be used advantageously especially if a characteristic value derived from combustion pulsations or material temperatures is used as a command variable. The method enables measured parameters to be kept below a permissible upper limit.

Abstract: In a method for operating a premix burner a water quantity is introduced into at least one of the burner and the reaction zone of the burner depending on at least one command variable formed from at least one measured value. The method can also be used if a burner is operated dry, i.e., without water injection for nitrogen oxide injection, and the injected water quantity is less than 20% of the fuel quantity. The method can be used advantageously especially if a characteristic value derived from combustion pulsations or material temperatures is used as a command variable. The method enables measured parameters to be kept below a permissible upper limit.

Abstract: In a method for operating a premix burner a water quantity is introduced into the burner and/or the reaction zone of the burner depending on at least one command variable formed from at least one measured value. The method in particular should also be used if a burner is operated in the actual sense dry, i.e., without water injection for nitrogen oxide injection, and the injected water quantity is less than 20% of the fuel quantity. The method can be used advantageously especially if a characteristic value derived from combustion pulsations or material temperatures is used as a command variable; such parameters are then kept below a permissible upper limit.

Abstract: In a method of operating a gas turbine, in which a gaseous fuel is burned in a combustion chamber and the hot combustion gases which are produced in the process are directed through the gas turbine, and in which method the gaseous fuel is fed to the combustion chamber via a plurality of controllable burners, working in parallel and arranged on one or more concentric, essentially circular rings, and is sprayed into the combustion chamber via fuel holes, high safety and availability within various operating ranges is achieved in a simple manner owing to the fact that the burners are divided into at least two groups (40-42) of burners, these groups in each case include the burners of one of the rings, and these groups are individually activated as a function of the operating state of the gas turbine.