Asea Brown Boveri Ag

Alstom (switzerland) Ltd

Alstom

Abb Alstom Power (switzerland) Ltd.

Alstom Technology Limited

Abb Research Ltd.

Abb Alstom Power (schweiz) Ag

Bernhard Weigand

Alexander Beeck

Kenneth Hall

Klaus Semmler

Beat Von Arx

Gordon David Anderson

Fathi Tarada

Konrad Vogeler

Bruce Johnson

Pey-Shey Wu

Hans Wettstein

Hartmut Haehnle

Ibrahim El-Nashar

Sacha Parneix

Michael Hock

Conor Fitzsimons

Mohamed Youssef Nazmy

Alexander Ralph Beeck

Reinhard Fried

Rudolf Kellerer

Wilhelm Endres

J&ouml;rgen Ferber

Wolfgang Kappis

Jens Von Wolfersdorf

Bernhard Bonhoff

Jörgen Ferber

Prith Harasgama

James P Downs

A device separates foreign particles from cooling air fed to turbine rotor blades. The cooling air is fed directly or indirectly via stationary nozzle units to an annular space between wall parts of a turbine stator and rotating wheel disk as a cooling-air stream in the circumferential direction. The annular space communicates with ducts, arranged in the disk, for feeding the cooling air into the blades. A diverter unit is provided inside the annular space or so as to delimit the annular space on one side, so cooling air emerging from the nozzle units, before entering the ducts, is diverted on one side and foreign particles are centrifugally thrown into a radially outer part of the annular space and separated therefrom with a barrier-air fraction. The diverter unit has a surface region on which the stream impinges so it can be diverted radially outward through an angle greater than 90&#xb0;.

Device for separating foreign particles out of the cooling air that can be fed to the rotor blades of a turbine

A thermally highly loaded machine component (), which is protected from overheating by film cooling, is provided with conical cooling passages () of circular cross section. The cooling passages are designed so as to be divergent from the cold-gas side () toward the hot-gas side. The conical cooling passages, as compared with cylindrical passages with regard to the mass flow of cooling medium () fed through the cooling passages, are substantially less dependent on the pressure ratio between the cold-gas side () and hot-gas side () of the component. The straight conical cooling passages of round cross section throughout may be produced in a very simple manner by laser drilling, with a convergent cutting beam being used for the machining.

Cooled components with conical cooling passages

Arrangement for cooling a flow-passage wall surrounding a flow passage, having at least one rib feature

A method of forming a curved cooling channel into a gas turbine component such as a turbine blade uses an electrode in the form of a helix. The electrode is driven to rotate around the central rotational axis of the helix and axially along the central rotational axis. A turbine blade for a gas turbine component is provided with at least one helical cooling channel.

Method for providing a curved cooling channel in a gas turbine component as well as coolable blade for a gas turbine component

An apparatus and a process are provided for impingement cooling of a component exposed to heat in a flow machine. The component includes a wall section on at least one side of which at least one impingement air flow impinges, the air flow passing through a flow channel within a surface element arranged spaced apart from the wall section and striking against the wall section to be cooled. The flow channel has an inlet aperture and an outlet aperture, with the outlet aperture directly facing toward the wall section to be cooled, and the inlet aperture has a throughflow cross section which is smaller than the throughflow cross section of the outlet aperture.

Apparatus and process for impingement cooling of a component exposed to heat in a flow power machine

In an air-cooled turbine blade ( ) which has a shroud-band element ( ) at the blade tip, the shroud-band element ( ) extending transversely to the blade longitudinal axis, hollow spaces ( &prime;) for cooling being provided in the interior of the shroud-band element ( ), which hollow spaces ( &prime;) are connected on the inlet side to at least one cooling-air passage ( ) passing through the turbine blade ( ) to the blade tip and open on the outlet side into the exterior space surrounding the turbine blade ( ), the hollow spaces ( &prime;) and the shroud-band element ( ) are matched to one another in shape and dimensions in order to reduce the weight of the shroud-band element ( ).

Turbine blade with actively cooled shroud-band element

Arrangement for cooling a flow-passage wall surrrounding a flow passage, having at least one rib element

A blade component of a gas turbine is disclosed around the outside of which hot air flows. The blade component is constructed as a hollow profile having outside walls and a tip cover, and having guiding walls arranged between the outside walls and connecting said outside walls. The blade component is cooled on the inside by cooling air flowing through cooling channels between the outside walls and the guiding walls. Cooling air flows through deflection areas in which the cooling air is deflected into flow stagnation zones. An efficient cooling of the blade component in the area of the stagnation zones is obtained in the area of the flow stagnation zones which are located at the outer corner of the deflection area. At least one drilled opening is provided in the outside wall through which drilled opening cooling air is able to flow at the stagnation zone from the cooling channel onto the outside of the blade component.

Drilled cooling air openings in gas turbine components

The invention relates to an impact flow for wall sections including a plurality of impact openings which are arranged on a plane in a flat or curved support. The support is fitted it a distance from the wall section, and the impact surface of the wall section that is to be cooled is configured as a bulged relief. The bulge elements are arranged around the impact surface of the impact beam. The surfaces of the bulge elements facing the impact beam include two curves which blend into one another.

Turbine blade wall section cooled by an impact flow

A cooling arrangement for blades of a gas turbine or the like, in each case the blades being built up from a suction-side wall and a pressure-side wall which are connected, to form a cavity, via a leading edge, a trailing edge, a blade tip and a blade root, and a flow path, through which a cooling medium, in particular steam, is capable of flowing, being integrated in the cavity, and in which the flow paths in each case of two or more adjacent blades are connected to one another in such a way that a continuous cooling duct sealed off relative to the hot-gas stream is formed. It thus becomes possible to increase cooling efficiency by better utilization of the cooling medium and at the same time to reduce the outlay in terms of construction.

Cooling arrangement for blades of a gas turbine

At least one adjustable restricting point is introduced into the cooling air path of a coolable gas turbine component, and means which make it possible to change this restricting point during the operation of the machine are provided. In this way it is possible to adapt the amount of cooling air fed to the component continuously to the specific operating conditions.

Cooled gas turbine component with adjustable cooling

A process for producing a casting core which is used for forming within a casting a cavity intended for cooling purposes, through which a cooling medium can be conducted, the casting core having surface regions in which there is incorporated in a specifically selective manner a surface roughness which transfers itself during the casting operation to surface regions enclosing the cavity and leads to an increase in the heat transfer between the cooling medium and the casting.

Process for producing a casting core, for forming within a cavity intended for cooling purposes

A coolable blade for a gas turbine or the like, having a blade body and a blade root, in which case the blade body is composed of a suction-side wall and a pressure-side wall, which, while forming a cavity, are connected via a leading edge, at least partly via a trailing edge and via a blade tip, the cavity is subdivided by essentially radially running separating webs into passages which form a continuous, repeatedly deflected flow path for a cooling medium, at least one blow-out opening is provided for the cooling medium, and the separating web adjacent to the trailing edge has one or more through passages close to the blade tip.

Coolable blade for a gas turbine

A cooling passage of a component subjected to high thermal loading, which is formed as a cavity ( ), running in a longitudinal direction (L) and curved orthogonally to the longitudinal direction (L), between a first wall ( ) and a second wall ( ), which in each case are connected to one another in a laterally adjacent manner, which has ribs ( ), which are arranged on the first wall ( ) and the second wall ( ) such that they alternate in a longitudinal direction (L) and are staggered relative one another and, at least in sections, assume a non-orthogonal angle relative to a projected center axis ( &prime;), and through which a cooling fluid (K) can flow in a longitudinal direction (L), in which case, when the profile of the cavity ( ) is curved orthogonally to the longitudinal direction (L), the ribs ( ) are formed in such a way that, in each case locally with regard to the adjacent rib of the opposite wall, they maintain a distance (a) which is half a respective local rib spacing (p). It is thereby possible to even out the heat transfer at a curved passage profile.

Cooling passage of a component subjected to high thermal loading

In an air-cooled turbine blade which, at the blade tip, has a shroud-band element extending transversely to the longitudinal axis of the blade, a plurality of cooling bores passing through the shroud-band element for the purpose of cooling, which cooling bores are connected on the inlet side to at least one cooling-air passage running through the turbine blade to the blade tip and open on the outlet side into the exterior space surrounding the turbine blade, improved and assured cooling is achieved owing to the fact that the cooling bores run from inside to outside in the shroud-band element at least approximately parallel to the direction of movement of the blade and in each case open upstream of the outer margin of the shroud-band element into a surface recess open toward the exterior space. The top side of the shroud band is preferable provided with at least two ribs and, which run in parallel and, in interaction with the opposite casing wall, form a cavity, into which the cooling air discharging from the cooling bores flows.

Growing community of inventors

Filderstadt-Sielmingen, Germany

Bernhard Weigand