Alstom Technology Limited

Ansaldo Energia IP UK Limited

General Electric Technology Gmbh

Alstom

Abb Research Ltd.

Eth Eidgenoessische Technische Hochschule Zuerich

Ansaldo Energia Switzerland Ag

Eidgenossische Technische Hochschule Zurich

Ansaldo Energia S.p.a.

Hans-Peter Bossmann

Herbert Brandl

Gregoire Etienne Witz

Michael Stuer

Maxim Konter

Marianne Sommer

Christoph Sommer

Christoph Toennes

Peter David Holmes

Dietrich Eckardt

Hans Joachim Schmutzler

Philipp Indlekofer

Daniel Renusch

Maryam Bahraini Hasani

Matthias Hoebel

Carlos Simon-Delgado

Alexander Schnell

Harald Reiss

Thomas Zierer

Christoph Tonnes

Raiko Milanovic

Claus Paul Gerdes

Ludwig Weiler

Valery Shklover

Jörg Krückels

Vasileios Stefanis

Klaus Erich Schneider

Laura Bogdanic

Otto-Ernst Bernhardi

Hans-Joachim Schmutzler

Giuseppe Carlo Gualco

Maryam Bharaini Hasani

Matthieu Esquerre

Sven Schofer

Rene Koehnke

Markus Schaudinn

Sharath Bachegowda

Jakob Kuebler

Mathieu Esquerre

Hans Rudolf Elsener

Anish Paul

Alessandra Bonadei

Cyrille Jerome Bricaud

Tsu-Te Chu

Toni Ivas

Martin Michalek

Grégoire Etienne Witz

Gregoire Etiennne Witz

Anup Kumar Bhattacharya

Rico Iten

The present disclosure relates to building very large gas turbines without changing rotor materials. The gas turbine part can include a structure composed of a metal and a ternary ceramic called MAX phase, having a formula Mn+1AXn, where n=1, 2, or 3, M is an early transition metal such as Ti, V, Cr, Zr, Nb, Mo, Hf, Sc, Ta, and A is an A-group element such as Al, Si, P, S, Ga, Ge, As, Cd, In, Sn, Tl, Pb, and X is C and/or N.

Method for manufacturing gas turbine part

The present disclosure relates to a gas turbine part, which can be exposed to high temperatures and centrifugal forces within a gas turbine. The gas turbine part can include plural sliced parts, wherein at least one of said sliced parts is made from a ternary ceramic called MAX phase, having the formula MAX, where n=1, 2, or 3, M is an early transition metal such as Ti, V, Cr, Zr, Nb, Mo, Hf, Sc, Ta, and A is an A-group element such as Al, Si, P, S, Ga, Ge, As, Cd, In, Sn, Tl, Pb, and X is C and/or N.

Gas turbine part and method for manufacturing such gas turbine part

Provided are metal-ceramic coatings for heat exchanger tubes of a central solar receiver and methods of preparing the same. The metal-ceramic coatings comprise at least one ceramic phase dispersed in a metal matrix and are disposed along the heat exchanger tubes to improve heat transfer and reduce oxidation of the heat exchanger tubes. Methods of preparing the metal-ceramic coatings and systems for using the same are provided.

Metal-ceramic coating for heat exchanger tubes of a central solar receiver and methods of preparing the same

A composite turbine blade for high-temperature applications such as gas turbines or the like includes a root for mounting the blade in a corresponding circumferential assembly groove of a rotor and an airfoil connected to said root. An inner carrying structure is provided extending at least over a portion of the root as well as at least a portion of said airfoil. The inner carrying structure is made of a high strength eutectic ceramic and the airfoil is made of a ceramic matrix composite (CMC) material.

Composite turbine blade for high-temperature applications

A rotor blade arrangement (), especially for a gas turbine, which can be fastened on a blade carrier () and includes in each case a blade aerofoil element () and a platform element (), wherein the platform elements () of a blade row form a continuous inner shroud. With such a blade arrangement, a mechanical decoupling, which extends the service life, is achieved by the blade aerofoil element () and the platform element () being formed as separate elements and by being able to be fastened in each case separately on the blade carrier ().

Rotor blade arrangement and gas turbine

The invention refers to a method for producing means with thermal resist for applying at a surface of a heat exposed component. The method includes providing at least one mixture of at least two different inorganic powder materials:

Method for producing means with thermal resistance for applying at a surface of a heat exposed component

A configuration for joining a ceramic layer has a thermal insulating material to a metallic layer. The configuration includes an interface layer made of metallic material located between the ceramic layer and the metallic layer, which includes a plurality of interlocking elements on one of its sides, facing the ceramic layer, the ceramic layer comprising a plurality of cavities aimed at connecting with the corresponding interlocking elements of the interface layer. The configuration also includes a brazing layer by means of which the interface layer is joint to the metallic layer. The invention also refers to a method for obtaining such a configuration.

Method for obtaining a configuration for joining a ceramic material to a metallic structure

A stator component of a turbomachine includes at least one axially extending outer ring which serves as a frame of an inner ring composed of partial segments. The partial segments are arranged on one another such that, on the rotor side, to form a coherent circular circumferential surface in relation to the rotational movement of rotor blades. The individual partial segment is composed of a material of uniform construction or, at least in a radial direction, of multiple partial bodies constructed from different materials, such as for example ceramic, wherein a partial segment thus formed exhibits predetermined stress and/or expansion behavior as a function of the load ranges of the turbomachine.

Stator component with segmented inner ring for a turbomachine

Shroud device thermally protecting a gas turbine blade, having a ceramic layer and a metallic layer, the metallic layer being thermally protected by the ceramic layer, the ceramic layer being mechanically joined to the metallic layer by a fixation device having a plurality of protrusions extending from the metallic layer designed so as to engage with a plurality of cavities located in the ceramic layer, such that there exists a gap between the cavities and the protrusions at ambient temperature, the gap disappearing at high temperature operation of the gas turbine, the protrusions being then locked into the cavities.

Gas turbine thermal shroud with improved durability

The invention refers to a method for applying heat resistant protection components onto the surface of a heat exposed component. The method including providing at least two separate heat protection components, and joining the at least two separate heat protection components onto their top surface and/or bottom surface and/or at least one side surface by flexible means for obtaining an integrally handable entity. The method further includes fixing the integrally handable entity by applying and brazing the surface of each heat protection component on the surface of the heat exposed component. The materials of the flexible means and for joining the flexible means on the separate heat protection components are selected such that the materials withstand brazing being performed under protective atmosphere, i.e. an atmosphere without or with reduced amount of oxygen, at process temperatures between 700&#xb0; C. and 1200&#xb0; C., and that the materials are burned out after brazing during a following oxidizing thermal step.

Method for applying heat resistant protection components onto a surface of a heat exposed component

A method for manufacturing a metal-ceramic composite structure for high temperature exposure is provided, whereby the composite structure includes a base metal structure or component, which is on at least one side covered and permanently joined with one or more ceramic tiles. The method may include the steps of: manufacturing green bodies with cavities and sintering the green bodies to receive ceramic tiles into cavities; arranging the ceramic tiles in a cast mould; pouring liquid metal into the cast mould to substantially fill the cavities; creating an intermediate metal layer; and solidifying the liquid metal to permanently join the ceramic tiles and the intermediate metal layer.

Method for manufacturing a metal-ceramic composite structure and metal-ceramic composite structure

A thermal barrier coating system on a base material includes a bond coat layer with a lower face in direct contact with the base material and an upper face, a first ceramic layer in direct contact with the upper face of the bond coating layer and a second ceramic layer disposed on an outermost surface of the coating system and configured to be exposed to hot gas. The first ceramic layer includes a layer, combination, mixture, alloy, blend or multilayer structure of at least one of yttria-stabilized zirconia with a yttria content in a range of 6-8 wt-%, YTaO4 doped zirconia, and titania doped zirconia. The second ceramic layer includes a layer, combination, mixture, alloy, blend or multilayer structure of at least one of YTaO4 doped zirconia, titania doped zirconia, scandia stabilized zirconia, ceria containing perovskite material, yttrium aluminum garnet material, Monazite material, and spinel material. A material of the second ceramic layer is different from a material of the first ceramic layer.

Thermal barrier coating system, components coated therewith and method for applying a thermal barrier coating system to components

A rotor blade () for a gas turbine includes a blade airfoil (), a blade tip (), a blade root (), and a platform () which is formed between the blade tip () and the blade root (), and is assembled from a plurality of individual sections (), the material of which is adapted in each case to the intended purpose of the individual section concerned. With such a rotor blade, a simplified production is achieved as a result of each of the individual sections () from the dimensions being significantly smaller than the assembled rotor blade ().

Rotor blade for a gas turbine

A turbine blade is provided having an airfoil and a platform manufactured in two separate pieces, which are joined together. The blade includes a seal, which is a mechanically decoupled seal, interposed between the airfoil and platform in a position closer to a hot gases path than a joint.

Turbine blade

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Lauchringen, Germany

Hans-Peter Bossmann