Alstom Technology Limited

Abb Research Ltd.

Alstom (switzerland) Ltd

Alstom

General Electric Company

Asea Brown Boveri Ag

Ansaldo Energia IP UK Limited

Maxim Konter

John Fernihough

Matthias Hoebel

Wilfried Kurz

Alexander Anatolievich Khanin

Cyrille Bezencon

Abdus Suttar Khan

Hans-Peter Bossmann

Alexander Schnell

Sergey Vorontsov

Christoph Tonnes

Dietrich Eckardt

Peter David Holmes

Bernd Fehrmann

Andreas B&ouml;gli

Hans Joachim Schmutzler

Christoph Sommer

Marianne Sommer

Christoph Toennes

Jean-Daniel Wagnière

Michael Newnham

Alexander Bone

Jon Conrad Schaeffer

Ulrich Rathmann

Michael Douglas Arnett

Shailendra Naik

Arthur Samuel Peck

Thomas Etter

Markus Oehl

Arkadi Fokine

Robert Baumann

Valery Shklover

Martin Balliel

Joachim Rosler

Victor Vladimirovich Odinokov

Alexander Burmistrov

Julius Schurb

Anton Kaiser

Alexey Pavlovich Karelin

Andreas Weiland

Hans-Joachim Dorn

Matthias Gaumann

Edvard L Kats

Vladimir P Lubenets

Jan Ehrhard

Kenneth Franklin Kelton

Hossein Meidani

Alexey Karelin

Wilfrid Kurz

Cyrille Bezençon

Anton Soumine

Regina Schlegel

Andreas Bögli

In a non-limiting example, an article having a body including a nickel-based superalloy is provided. The nickel-based superalloy has a microstructure that includes a gamma phase matrix and a gamma prime phase including a plurality of rafting-resistant gamma prime particles dispersed in the gamma phase matrix. The plurality of the rafting-resistant gamma prime particles has an average particle perimeter of about 3 microns to about 15 microns, an average aspect ratio of about 1.2 to about 3, and where the microstructure of the nickel-based superalloy is substantially uniform throughout the body.

Nickel-based superalloy with microstructure including rafting-resistant gamma prime phase and article prepared therefrom

The invention refers to a method for manufacturing a hybrid component including the following steps of manufacturing a preform as a first part of the hybrid component, then successively building up on that preform a second part of the component from a metallic powder material by means of an additive manufacturing process by scanning with an energy beam, thereby establishing a controlled grain orientation in primary and in secondary direction of at least a part of the second part of the component. The controlled secondary grain orientation is realized by applying a specific scanning pattern of the energy beam, which is aligned to the cross section profile of the component or to the local load conditions for the component.

Method for manufacturing a hybrid component

A component, especially a hot gas component of a turbomachine, has at least one passage ('), especially a cooling passage, which is embedded in an outer wall () of the component () of the turbomachine and basically extends parallel to the surface () of the component (). The component () has a basic body () and at least one coating () which is applied to the basic body on the outside, and the passage (&#x2032;) on one hand is formed by a cavity which is formed in the basic body (), and on the other hand is closed off towards the surface () of the component () by the coating ().

Hot gas component of a turbomachine including an embedded channel

A seal assembly for a gas turbine is arranged in grooves of a rotor heat shield having several bends. The assembly comprises four seal portions overlapping one another and extending in the axial, radial, and circumferential direction with respect to the turbine rotor. A holding means retains the radial sections of one seal portion allowing a limited movement of said seal portion independent of another seal portion. The independent movement assures contact of the individual seal portions with all mating surfaces of the rotor heat shield and improved sealing function regardless of displacements of the rotor heat shield and tolerances of turbine parts.

Seal in gas turbine

A gas turbine () includes a rotor () which has two rotor blade rows () with a plurality of rotor blades (), and also a rotor heat shield (), which is arranged between them, with a plurality of heat shield elements (), and with a stator () which has a stator blade row (), with a plurality of stator blades (), which is arranged axially between the two adjacent rotor blade rows (). The stator blades () have a stator sealing structure () radially on the inside. The heat shield elements () have a rotor sealing structure () radially on the outside which interacts with the stator sealing structure () for forming an axial seal (). Furthermore, a blade radial seal () is formed between two adjacent rotor blades (), and also a heat shield radial seal () is formed between two adjacent heat shield elements (), and in each case separates a gas path () from the rotor (). For increasing efficiency, the heat shield elements () and the rotor blades () are matched to each other so that the heat shield radial seal () merges without interruption into the blade radial seals () of the two axially adjacent rotor blades () in such a way that a continuous radial seal () is formed from the one rotor blade (), via the heat shield element (), to the other rotor blade ().

Turbo machine and gas turbine

A fluid flow engine (), in particular a turbo engine, has at least one guide vane row () with a plurality of guide vanes () and at least one rotor blade row () with a plurality of rotor blades (). One guide vane row () and one rotor blade row () that follows the former directly downstream with respect to a working gas flow (), together form a stage () of the fluid flow engine (). To reduce the load on the rotor blades (), the guide vanes () and the rotor blades () are coordinated at least in one stage () so that in a reference relative position between the respective guide vane () and the respective rotor blade (), there is an axial distance (B) and a circumferential distance (C) between the outgoing flow edge () of the respective guide vane () and the oncoming flow edge () of the respective rotor blade () that is measured in the axial direction and is varied along a height (H) of a gas path () running axially between the blade rows () of this stage (), said height being measured radially.

Fluid flow machine

Method of producing a hot gas component of a turbomachine including an embedded channel

Turbo machine blade platform

A method is disclosed for recovering the properties of single crystal and directionally solidified Nickel based superalloys and articles made thereof, after use in a high temperature environment. The method comprises the steps of a stress relief treatment, a &#x3b3;' rejuvenation heat treatment at a temperature below the &#x3b3;&#x2032;-solvus temperature (T) of the superalloy, a precipitation heat treatment and an aging heat treatment.

Property recovering method

Turbo machine double blade and platform

A method for removing casting defects () from an article () with an oriented microstructure can include locating at least one casting defect () and melting the casting defect () locally by a heat source () to a depth at least as great as the casting defect () itself. The molten material can then be solidified epitaxially with respect to the surrounding oriented microstructure of the article () in a way that the resulting solidified area is substantially free of any defect.

Method of removing casting defects

A gas turbine component consists of a superalloy base material with a single crystal structure and a protective MCrAlY-coating (). The MCrAlY-coating () has a g/g' single crystal structure, which is epitaxial with the base material. It has be determined the critical factors for the successful epitaxial and crack-free growth of the MCrAlY-coating ().

MCrAlY-coating

In an emergency cooling system () for a component () which is subject to thermal load in operation, in, e.g., a turbine, the component () has a wall () which, in operation, is acted on by heat on a first wall side () and is acted on by a flow of cooling fluid () on a second wall side (). The wall () has at least one emergency cooling opening () which is closed off by a plug () and through which cooling fluid flows from the second wall side () to the first wall side () when the plug () is absent. The plug () is designed so as to melt at a predetermined temperature. The plug () is a body which is produced separately from the component (), the plug () being inserted into the emergency cooling opening (), in which it is connected to the component ().

Emergency cooling system for a thermally loaded component

The present invention relates to an icosahedral, quasicrystalline compound or compound present in the form of an approximant having the nominal composition: TiCrAlSiO, in which v=60-65; w=25-30; x=0-6; Y=8-15; z=8-20; and in which the atom percent of oxygen is in the range of between 8 and 15%, and that of aluminum in the range of between 2 to 5%. Due to their layered structure and ceramic intermediate layers, compounds of this type exhibit excellent properties, in particular for use as coatings for gas turbine components, such as for example, rotor blades or guide vanes.

Quasicrystalline alloys and their use as coatings

A method of casting a directionally solidified (DS) or single crystal (SX) article with a casting furnace having a heating chamber (), a cooling chamber (), a separating baffle () between the both chambers includes a first step in which the shell mould () is filled with liquid metal (), and the liquid metal () is directionally solidified by withdrawing the shell mould () from the heating to the cooling chamber (). An inert gas impinges from nozzles () arranged below the baffle () on the shell mould () and in steep transitions in outer surface area of the shell mould () the flow of the inert gas () is reduced or even stopped and when a protruding geometrical feature has passed the impingement area of the gas jets, the gas flow () is restored to a value adjusted to the geometry of the cast part presently passing the impingement area.

Method for casting a directionally solidified article

Growing community of inventors

Klingnau, Switzerland

Maxim Konter