Alstom Technology Limited

Alstom (Switzerland) Ltd

Abb Alstom Power (Schweiz) Ag

Abb Alstom Power (Switzerland) Ltd.

Christoph Nagler

Erich Kreiselmaier

Sergei Riazantsev

Erhard Kreis

Jose Anguisola McFeat

Ulrich Rathmann

Alexander Beeck

Hartmut Haehnle

Klaus Semmler

Ulrich Wellenkamp

Joerg Stengele

Christof Pfeiffer

Ingo Schwarz

Mark Richter

Lothar Schneider

Alexander Ralph Beeck

Herbert Brandl

Beat Von Arx

Brian Kenneth Wardle

Igor Tsypkaykin

Marcel Koenig

J&ouml;rgen Ferber

Stefan Irmisch

Bruno Benedetti

Kurt Rubischon

André Schwind

Jose Ma Anguisola McFeat

Ralf Walz

The disclosure relates to a hollow gas turbine vane that is cooled by an arrangement configured to sequential cooling an endwall of the vane and its airfoil and, at the same time, the two endwalls of the vane. This arrangement can reduce cooling air demand, which can have a positive effect on the turbines efficiency.

Gas turbine vane with improved cooling

A rotor is provided for an axial-throughflow turbo machine, which carries a plurality of moving blades which are each pushed with a blade root into a rotor groove extending about the axis and are held. The blade root includes a hammer root with a hammerhead and is supported on radial stop faces of the rotor groove which lie further outward in the radial direction, against centrifugal forces acting on the moving blades, and are supported on axial stop faces lying further inward in the radial direction, against axial forces which act on the moving blade. The rotor groove has at its bottom, to reduce thermal stresses, an axially and radially widened bottom region with a continuously curved cross-sectional contour. In such a rotor, an advantageous adaptation of the blading is achieved by the blade root of the moving blades being adapted to the widened bottom region in the radial direction.

Rotor for an axial-throughflow turbomachine and moving blade for such a rotor

The guide vane of a gas turbine comprises a blade having an outer platform connectable to a guide vane carrier or gas turbine casing, and at the opposite end an inner platform that carries a cover plate. The inner platform has a dovetail housing to which the cover plate is connected. The method for replacing the cover plate consists in separating the cover plate from the inner platform by cutting along the profile of the dovetail housing, then making the cover plate to slide out of the dovetail housing, thus inserting a new or refurbished cover plate into the dovetail housing.

Guide vane of a gas turbine and method for replacing a cover plate of a guide vane of a gas turbine

A cooling passage arrangement is provided inside a hollow-cast cast part, with a flow region, delimited by at least two spaced apart cast-part walls, for a cooling medium. The flow region is divided in the flow direction into two cooling passages by at least one rib line which is connected to the two cast-part walls. At least one gap is provided along the at least one rib line. At the least one gap, two rib ends are oppositely disposed a distance apart, of which one rib end has a contour in the style of a 'wish bone -'Y'-cross-section'.

Cooling duct arrangement within a hollow-cast casting

A stator vane for a gas turbine includes a vane airfoil which extends in the longitudinal direction of the vane and which is delimited by a leading edge and a trailing edge, and also an outer platform, the inner side of which is exposed to the hot gas which flows through the gas turbine, and on which provision is made for a hook-like fastening element, projecting outwards in the region of the trailing edge, for fastening the stator vane on a casing of the gas turbine, which fastening element, on its side facing the trailing edge, has a locating slot above the trailing edge for the fixing of a heat shield which adjoins the outer platform of the stator vane in the flow direction of the hot gas. Provision is made on the outer platform of the stator vane between the locating slot and the trailing edge of a structure for reducing the thermal and mechanical stresses in the region of the transition between trailing edge and outer platform.

Guide vane having hooked fastener for a gas turbine

A stator blade for a gas turbine includes a blade airfoil extending in a longitudinal direction of the blade and is delimited by leading and trailing edges. The stator blade includes a shroud, whose inner side is exposed to hot gas which flows through the gas turbine. A hook-like fastening element for fastening the stator blade on a casing of the gas turbine projects outwards in the region of the trailing edge. The fastening element has a locating slot above the trailing edge for fixing a heat shield, which is connected to the shroud in the flow direction of the hot gas. A cavity is provided on the shroud between the locating slot for the heat shield and the trailing edge of the blade airfoil for reducing the thermal and mechanical stresses in the region of transition between the trailing edge and shroud.

Guide vane for a gas turbine

A method of modifying an existing casting mold for a turbine moving blade having a shroud band segment with an initial coupling geometry for coupling with a further shroud band segment, the coupling geometry having an initial coupling angle of the shroud band segment relative to a circumferential direction of the turbine, includes calculating a modified coupling geometry for the shroud band segment, the modified coupling geometry including a modified coupling angle of the shroud band segment relative to the circumferential direction. The method further includes creating at least one of a removal zone and an application zone, wherein the creating of the removal zone includes removing a first amount of casting mold material from the removal zone and wherein the creating of the application zone includes applying a second amount of an additional casting mold material to the application zone, wherein the removing and the applying steps result in the casting mold having the modified coupling angle.

Method of modifying an existing casting mold for a turbine moving blade

A method of modifying a coupling geometry in a shroud band segment of a turbine moving blade includes the following steps: calculation of a modified coupling geometry; removal of shroud band material situated outside the modified coupling geometry; and/or application of additional material not present inside the modified coupling geometry; reworking the removal and/or application zones. The method avoids disadvantages of the prior art and provides improved wear behavior in the coupling region so as to prolong the life of the turbine blades in an effective and inexpensive manner.

Method of modifying the coupling geometry in shroud band segments of turbine moving blades

In a process for producing a turbine blade or vane, providing a casting mold for casting the turbine blade or vane, the casting mold including a blade or vane platform and a main blade or vane part, and a position of the main blade or vane part relative to the blade or vane platform determining a first angle of incidence; providing additional machining stock to the blade or vane platform at predetermined locations; machining the casting using a process which is specified for the first angle of incidence; rotating the casting around a longitudinal axis for an angle which is equal to the difference between said first angle of incidence and a second angle of incidence, and subjecting said rotated casting to said machining process to remove at least partially the additional machining stock.

Process for producing a turbine blade or vane

A cooling arrangement () for supplying a first cavity () with a cooling gas, in particular in a gas turbine of a power plant, includes a cooling-gas passage () which is formed in a first component () and connects the first cavity () to a second cavity (). A second component () bears against a bearing side () remote from the second cavity () and separates the first cavity () from a third cavity (). The second component () is displaceable within a range of displacement. To improve the cooling effect, an orifice region () of the cooling-gas passage () is dimensioned and/or positioned in such a way that its orifice cross section () projects from the range of displacement to such an extent that it is open at least with a predetermined minimum cross section in any position of the second component ().

Cooling arrangement

A device for producing a soldered joint between two joining partners which can be joined via a common contact surface ( ), using a solder material which can be introduced between the two joining partners. At least one joining partner ( ), in the region of the contact surface ( ), provides at least one recess, known as a solder reservoir ( ), which faces the contact surface and into which the solder material can be introduced, and the solder reservoir ( ) is completely delimited and surrounded by the contact surface ( ).

Device and process for producing a soldered joint between two joining partners which can be by means of a common contact surface

A device for fastening and fixing components to a cylindrical wall. The cylindrical wall may be both the convex-cylindrical outer contour of a cylinder and the concave-cylindrical inner contour of a hollow cylinder, in which the component is fixed in the radial, axial and circumferential directions. The fastening and fixing is effected by shaped elements which are attached to the component and by a counterpart to each shaped element on the wall. In each case a shaped element and a counterpart interlock, such that the component has at least three shaped elements, of which at least one shaped element has a defined accuracy of fit with its associated counterpart in the radial direction and has clearance in the axial and circumferential directions. At least one shaped element has a defined accuracy of fit with its associated counterpart in the axial direction and has clearance in the radial and circumferential directions. Furthermore, at least one shaped element has a defined accuracy of fit with its associated counterpart in the circumferential direction and has clearance in the radial and axial directions.

Fastening and fixing device

A method is disclosed for reducing the variance in the coolant consumption of components of a turbo-machine, in particular a gas turbine. The components are provided with one or more holes for the passage of a coolant, wherein a surface roughness existing inside the holes is reduced by mechanical finishing. The method is characterized by mechanical finishing that is performed by reshaping rough points that cause the surface roughness using a cold working process such as at least one of beating, pressing and rolling. The method permits a simple reduction of the surface roughness without creating finishing residues that could result in obstructions of the holes.

Method for reducing variance in the coolant consumption of components of a turbo-machine

A platelike projecting component portion of a component used in gas turbines or other similar applications includes a surface upon which hot gas acts and cooling bores through which a cooling medium is capable of flowing. Effective cooling is achieved by providing at least one plenum assigned solely to the component portion. The plenum is arranged so as to be directly adjacent to the surface upon which hot gas acts and through which the cooling medium is capable of flowing to provide convective heat transfer. The cooling bores are designed as blow-out orifices which emanate from the plenum and issue the cooling medium onto the surface upon which hot gas acts, thereby forming a cooling film.

Platelike projecting component portion of a gas turbine

In a gas-turbine guide element ( ) around which a hot air flow ( ) flows and which, at least in a trailing edge region ( ), in which the air flow ( ) separates from the guide element ( ), comprises at least two walls ( ) arranged essentially in parallel and connected to one another by ribs ( ) in such a way as to form internal cooling passages ( ), and which is cooled on the inside with cooling medium ( ) flowing through the cooling passages ( ), the cooling medium discharging from the guide element ( ) at the trailing edge ( ) essentially parallel to and between the walls ( ), and in a method of producing it, easier reworking and less susceptibility to foreign particles are achieved owing to the fact that at least some of the ribs are arranged as choke ribs ( ) so as to terminate essentially flush with the trailing edge ( ).

Growing community of inventors

Zurich, Switzerland

Christoph Nagler