Asea Brown Boveri Ag

Alstom

Abb Alstom Power (schweiz)

Jakob Keller

Roger Suter

Robin McMillan

Adnan Eroglu

Christian Oliver Paschereit

Jaan Hellat

Alexander Beeck

Bettina Paikert

Frank Reiss

Paul Marlow

Pirmin Schiessel

J&ouml;rgen Ferber

Ulf Christian M&uuml;ller

Martin Valk

Ulf Christian Muller

Jochem Fischer

Khawar Syed

Hugh Jackson

Vera Keller

Georg Keller

Gustav Hagstr&ouml;m

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.

Method for designing a flow device

Method and device for injecting a fuel/liquid mixture into the combustion chamber of a burner

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.

Oscillation attenuation in combustors

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

Method of preventing flow instabilities in a burner

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 ( ), at least two, spatially separated fuel sprays ( ) are formed in which the fuel is mainly present in the form of individual fuel droplets ( ), and in that the fuel sprays ( ) each have a propagation direction relative to one another such that the fuel droplets ( ) of one fuel spray ( ) collide with the fuel droplets ( ) of the other fuel spray ( ) in such a way that, during the collision of the fuel droplets ( ), a droplet cloud ( ) is formed with new fuel droplets ( ) whose diameter is smaller than that of the colliding fuel droplets ( ).

Method and appliance for atomizing liquid fuel for a firing installation

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.

Combustion chamber for a gas turbine

The temperature can nowadays be reduced by about 400&deg; C. as a result of the cooling of the guide vane (,) of the first guide wheel. The many film bores leading outward from the guide vane (,) 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 (,&prime;). 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.

Method and device for cooling guide vanes in a gas turbine plant

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.

Method of generating a gas flow of medium pressure and medium temperature from a gas flow of high pressure and high temperature and appliance for carrying out the method

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.

Method for measuring the temperature of hot gases by means of a thermocouple, and a measuring arrangement for carrying out the method

Method for operating a premix burner

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.

Burner having a frame for operating an internal combustion machine

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.

Fluid-flow machine for compressing or expanding a compressible medium

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.

Method for the isothermal compression of a compressible medium, and atomization device and nozzle arrangement for carrying out the method

A burner arrangement (,) for a gas turbine comprises an interior space (,) enclosed by a casing (,), in which interior space (,) at least one burner (,) is arranged, and into which interior space (,) in each case a jet (,) of a gaseous medium, in particular air, is sprayed through at least two nozzle openings (,) against the direction of flow of the burner (,) and along the inner wall (,) of the casing (,) which jets (,), guided by the inner wall (,), meet one another from opposite directions and combine to form a secondary flow (,) flowing off perpendicularly from the inner wall (,). 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 (,), a dividing plate (,) arranged in the flow path of the jets (,) and disposed essentially perpendicularly to the inner wall (,) is provided.

Burner arrangement for a gas turbine including an inlet-air impingement plate

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.

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Wohlen, Switzerland

Jakob Keller