Abstract: Various embodiments and implementations of graph-neural-network (GNN)-based decoding applications are disclosed. The GNN-based decoding schemes are broadly applicable to different coding schemes, and capable of operating on both binary and non-binary codewords, in different implementations. Advantageously, the inventive GNN-based decoding is scalable, even with arbitrary block lengths, and not subject to typical limits with respect to dimensionality. Decoding performance of the inventive GNN-based techniques demonstrably matches or outpaces BCH and LDPC (both regular and 5G NR) decoding algorithms, while exhibiting improvements with respect to number of iterations required and scalability of the GNN-based approach. These inventive concepts are implemented, according to various embodiments, as methods, systems, and computer program products.

Abstract: Disclosed are apparatuses, systems, and techniques that may use machine learning for determining transmitted signals in communication systems that deploy orthogonal frequency division multiplexing. A system for performing the disclosed techniques includes receiving (RX) antennas to receive RX signals, each RX signal received over a respective resource element of a resource grid. Individual resource elements of the resource grid are associated with different radio subcarriers and/or data symbols. The RX signals include a combination of a plurality of transmitted (TX) streams. The system further includes a processing device to process the RX signals using one or more neural network models to determine TX data symbols transmitted via the plurality of TX streams.

Abstract: A method for designing a flow device, including the steps of defining the physical properties of the flow device, and deriving from the physical properties the corresponding geometry of the flow device using inverse flow equations. The flow device can be at least a part of a gas turbine, a steam turbine, or a combined gas/steam turbine-cycle plant.

Abstract: A method and a device are described for injecting a fuel/liquid mixture into the combustion chamber of a burner, with an atomizer nozzle and with at least one liquid delivery region, at least one fuel delivery region separated from the latter and at least one volume region which is provided upstream of the atomizer nozzle orifice and in which the liquid is mixed with the fuel. The invention is distinguished in that the liquid experiences the generation of vortices before or during intermixing with the fuel.

Abstract: The devices and methods according to the invention are used to attenuate acoustic and/or thermoacoustic oscillations in a combustor. The combustor may be, in most cases, constructed as a premixing combustor with low emissions of noxious substances and includes a fluid supply device, an antechamber, a premixing device, and a combustion chamber. The fluid is supplied to the combustion chamber completely or almost completely through the front panel located in the front. The combustion chamber has at least one recirculation opening for attenuating the oscillations. It is furthermore advantageous that an attenuation volume and an injector be provided. The recirculation opening preferably merges at least in part with the attenuation volume. By means of the injector, the combustor is supplied with a more compressed fluid in order to ensure an adequate and clear pressure drop across the combustor.

Abstract: In a method of, and an appliance for, operating a burner (26), in which a combustion air flow (14) transports fuel into a combustion chamber (28) where the fuel is burnt, the formation of coherent flow instabilities of the combustion air flow (15) after emergence into the combustion chamber (28) is prevented by perturbation air (22) being injected into the combustion air flow (15).

Abstract: A method and an appliance are described for atomizing liquid fuel for a firing installation, preferably for a combustion chamber of a gas turbine installation, having a nozzle arrangement through which the pressurized liquid fuel passes and is atomized to form a fuel spray. The invention is characterized by the fact that after the passage of the fuel through the nozzle arrangement (3, 4), at least two, spatially separated fuel sprays (5, 6) are formed in which the fuel is mainly present in the form of individual fuel droplets (16), and in that the fuel sprays (5, 6) each have a propagation direction relative to one another such that the fuel droplets (16) of one fuel spray (5) collide with the fuel droplets (16) of the other fuel spray (6) in such a way that, during the collision of the fuel droplets (16), a droplet cloud (9) is formed with new fuel droplets (17) whose diameter is smaller than that of the colliding fuel droplets (16).

Abstract: In a combustion chamber for a gas turbine, noise absorption is achieved over a wide frequency range with simultaneous cooling of the arrangement and low space requirement by the inner wall being formed, at least in a partial region of the inner walls by at least two perforated plates arranged essentially parallel to one another, and by the distances between the perforated plates and the geometrical dimensions of the openings being selected in such a way that a plurality of mutually connected Helmholtz resonators is formed and that, in addition, further expedients are available which act to absorb noise.

Abstract: The temperature can nowadays be reduced by about 400° C. as a result of the cooling of the guide vane (15) of the first guide wheel. The many film bores leading outward from the guide vane (15) must therefore remain free of blockages or deposits caused by suspended matter in the cooling medium. Only pure gas must therefore be used as the cooling medium for the first guide wheel. This purpose is served by a dust separator which is designed advantageously as an axial cyclone (24, 24′). The latter has no moving structural parts, has a simple design, is therefore insusceptible to faults and can be exposed to high temperatures. The axial cyclone is a centrifugal deduster without gas stream reversal.

Abstract: In a method of generating a third gas flow of medium pressure and medium temperature, which can be particularly employed as cooling air for a gas turbine, from a first gas flow of high-pressure and high temperature, a high effectiveness with simultaneous simple process control is achieved in an arrangement wherein the reduction is undertaken by stepwise energy exchange between the first gas flow and a second gas flow of low pressure and low temperature in a cascade consisting of a plurality of energy exchangers connected in series.

Abstract: In a method and an appliance for operating a burner (19), in which a flow of combustion air (10) transports fuel into a combustion chamber (21) where the fuel is burnt and, during transport, the flow of combustion air (10) is mixed with the fuel and guided by casing elements (13, 16), the resonant build-up interaction of coherent flow instabilities and acoustic field is reduced because the formation of first periodic, coherent flow instabilities in a boundary layer between the combustion air (10) and the casing elements (13, 16) is perturbed, and coupling of an acoustic field in the combustion chamber (21) to such first flow instabilities is reduced.

Abstract: A method and arrangement for measuring the temperature of hot gases present in a hot gas space. A portion of the hot gases is mixed in a mixing space arranged inside the hot gas space with a cooler gas. The temperature of the gas mixture is measured with a thermocouple which is provided in the mixing space. The gas mixture is guided past the thermocouple to determine the temperature of the hot gases from the measured temperature of the gas mixture. The hot gas space is located in the combustion chamber of a gas turbine.

Abstract: The object of the invention is to provide a method for operating a premix burner which has improved operational reliability and functioning during certain types of operation. In addition, it is intended to specify a corresponding premix burner for carrying out the method. According to the invention, this is achieved by the fact that at least one liquid fuel (2) is injected into the inner chamber (9) of the premix burner (4) in a plain jet (26, 26′) with an injection angle &agr; of less than 10°. For this purpose, the liquid-fuel nozzle (17) has a simple injection opening (19) with a guide length (1) and with a diameter (d).

Abstract: A fluid-flow machine for compressing or expanding a compressible medium is described, having a rotor on which there is arranged perpendicularly to the rotor axis at least one moving-blade row, the individual moving blades of which have moving-blades ends, which are free on the radial side and face the inner wall of a casing, surrounding the rotor, in a freely movable manner, through the interior space of which casing the compressible medium flows axially relative to the rotor axis. An annular-passage system is open to receive the compressible medium on either side of the moving-blade row and the flow in the interior of the casing, and in a modified form may have surface contours on the ends of the blades to create pressure conditions which correspond approximately to the static pressure conditions at the opposite sides of the blades.

Abstract: A burner for operating an internal combustion machine, a combustion chamber of a gas turbine group or firing installation is described, having at least two hollow half truncated-cone shaped bodies which are assembled within one another in such way that their longitudinal axes of symmetry extend so that they are mutually radially offset and which enclose at least two tangential air inlet slots for a combustion inlet airflow and also enclose a hollow conical space, and having a nozzle arrangement for injecting liquid, highly reactive fuel into the hollow conical space, which nozzle arrangement is located in the region of the narrowest internal diameter of the hollow conical space. The invention is distinguished by the fact that one injection appliance for fuel is respectively provided, in the direction of the combustion airflow, upstream of each of the tangential air inlet slots, which injection appliance injects the fuel into the air inlet slot with a flow direction parallel to the combustion inlet airflow.

Abstract: A method and a device for the isothermal compression of a compressible medium preferably air, for the operation of a turbomachine which is intended to generate energy and in which a pressurized liquid, preferably water, is atomized by means of an atomization device and, together with the air, forms a liquid-air mixture which, in order to be compressed, is introduced into a nozzle arrangement in which most of the kinetic energy of the liquid-air mixture is converted into compression energy as a result of an increase in the pressure of the air. The liquid-air mixture is introduced into the nozzle arrangement at a velocity which is greater than the speed of sound, and the atomization is carried out in such a manner that liquid droplets are formed within the liquid-air mixture, the diameters of which droplets are approximately 200 &mgr;m or less.

Abstract: A burner arrangement (20) for a gas turbine comprises an interior space (22) enclosed by a casing (23), in which interior space (22) at least one burner (21) is arranged, and into which interior space (22) in each case a jet (26, 27) of a gaseous medium, in particular air, is sprayed through at least two nozzle openings (24, 25) against the direction of flow of the burner (21) and along the inner wall (23a) of the casing (23) which jets (26, 27), guided by the inner wall (23a), meet one another from opposite directions and combine to form a secondary flow (28) flowing off perpendicularly from the inner wall (23a). In such a burner arrangement, the flow is stabilized and evened out by virtue of the fact that, to establish the impingement point of the jets (26, 27), a dividing plate (29) arranged in the flow path of the jets (26, 27) and disposed essentially perpendicularly to the inner wall (23a) is provided.

Abstract: A flow duct for the passage of a two-phase flow which has a liquid and a gaseous phase is described, comprising an inner wall completely enclosing the two-phase flow radially to the direction of flow. The invention is distinguished by the fact that raised contours are provided on the inner wall of the flow duct, and these raised contours are attached to the inner wall essentially perpendicularly to the direction of flow and are at a distance from one another in the direction of flow.

Abstract: A combustion chamber in a gas-turbine, wherein the combustion chamber has an annular-toroidal-shaped interior space. A plurality of burners are arranged on the periphery of the combustion chamber, wherein the burners are operatively connected to the annular-toroidal-shaped interior space so as to initiate a swirl flow. The swirl flow forms a vortex core and the vortex core ensures the stability of the flame front.

Abstract: Described is a plenum, in particular the air plenum of a gas-turbine combustion chamber, having at least two flow inlets, for introducing gas flows into the plenum, in which the gas flows are guided essentially along the inner wall of the plenum and are directed toward one another in such a way that the gas flows, after coinciding, are directed as a free gas flow away from the inner wall.The invention is distinguished by the fact that at least one flow obstacle (11) oriented in interaction with the direction of flow of the gas flows (1, 2) guided on the inner wall (3) is provided on the inner wall (3).