Siemens Aktiengesellschaft

Fraunhofer-gesellschaft Zur Foerderung Der Angewandten Forschung E.v.

Chromalloy Gas Turbine Corporation

Siemens Energy, Inc.

Siemens Energy Global Gmbh & Co. Kg

Chromalloy New York

Georg Bostanjoglo

Rolf Wilkenhöner

Bernd Burbaum

Michael Ott

Norbert Pirch

Andres Gasser

Nikolai Arjakine

Stefanie Linnenbrink

Nigel-Philip Cox

Torsten Melzer-Jokisch

Torsten Jambor

Tobias Buchal

Volker Vosberg

Jan Münzer

Ursula Pickert

Ralf Müsgen

Matthias Oechsner

Dirk Goldschmidt

Thorsten Mattheis

Rudolf Küperkoch

Winfried Eβer

Torsten Koch

Katharina Bergander

Thomas Beck

Dimitrios Thomaidis

Werner Stamm

Jan Steinbach

Axel Kaiser

Selim Mokadem

Frank Mentzel

Alexander Ralph Beeck

Eckart Schumann

Arturo Flores Renteria

Silke Settegast

Martin Charles Gosling

Winfried Esser

Sebastian Piegert

Uwe Paul

Reiner Anton

Torsten Jokisch

Robert Herfurth

Jacek Grodzki

Andreas Oppert

Andre Mehlhorn

Robert S Willis

Scott P Irwin

Rüstü Söl

Stacy Fang

Thomas H Milidantri, Jr

Adam J Taetsch

Dan Shipman

Orville Morgan

Gerry Milidantri

Rustu Sol

Jr Thomas H Milidantri

Thorsten Koch

A turbine blade has a blade tip, a cooling structure with cooling channels which are designed to have cooling fluid passed through them in order to cool the turbine blade during operation, an end section at a lower level than that of the blade tip, and an outer wall section extending up to the blade tip. The cooling structure is formed between the end section and the blade tip. A method produces a cooling structure of this type.

Turbine blade comprising a cooling structure and associated production method

A method for generating, in layers, an application structure made of high heat resistant super alloys on a substrate is provided. A powdery construction material is melted by an energy beam at a working point, wherein the working point is guided across the substrate along a primary movement direction and thus swings transversely to the primary movement direction. The working point thereby swings from a first edge of a respective layer of the application structure to a second edge of the layer. In this way, a time interval passes between departure from a respective edge and a return to the respective edge directly following the departure, such that a melt bath on the respective edge solidifies into a paste-like zone during the time interval.

Laser build-up welding of high heat resistant super alloys by means of oscillating beam guidance

Applying material along parallel welding lines per welding layer, and changing a direction of extension of the welding tracks by 90&#xb0; for the next welding layer, is provided.

Build-up strategy for a crown base of a turbine blade, and turbine blade

Use of a laser beam () which has one external and one internal laser beam area () with different intensities enables a higher temperature gradient to be produced in the z-direction.

Laser method with different laser beam areas within a beam and devices

Known protective coatings with a high Cr-content and silicon as an additive have brittle phases which become additionally brittle under the influence of carbon during use. The protective coating herein has a double metallic layer that only contains tantalum on the outside contents of the layers.

Layer system with double MCrAlX metallic layer

A process for welding directionally solidified metallic materials is presented. Process parameters are targeted selected with respect to laser welding, advancement, laser power beam diameter and powder mass flow. The temperature gradient, which is fundamentally decisive for the single-crystal growth during laser cladding, may be set in a targeted manner.

Single crystal welding of directionally compacted materials

Known protective layers having high Cr content and additional silicon form brittle phases, which additionally become brittle under the effect of carbon during use. The protective layer according to the invention comprises a two-part metal layer, which contains tantalum on the outside.

Layer system having a two-ply metal layer

A method of welding workpieces of high-temperature superalloys is provided. Welding filler is applied in a plurality of layers to a surface of the workpiece via a heat input zone and a supply zone for supplying the welding filler into the heat input zone. The heat input zone and the supply zone on the one hand and the workpiece surface on the other hand are moved in relation to one another. A polycrystalline weld seam is generated by remelting a previously applied layer of the plurality of layers. Welding parameters are chosen such that a cooling rate during a solidifying of the material is at least 8000 Kelvins per second. Further, a welding apparatus for carrying out such a method is provided.

Method and device for welding workpieces made of high-temperature resistant super alloys

A welding method for welding workpieces made of highly heat-resistant superalloys is provided. The method includes generating a heat input zone on the workpiece surface by means of a heat source, feeding welding filler material into the heat input zone by means of a feeding device, and generating a relative motion between the heat source and the feeding device on one hand and the workpiece surface on the other hand by means of a conveying device. Furthermore, according to the welding method, the mass feed rate is &#x2266;350 mg/min.

Method for welding workpieces made of highly heat-resistant superalloys, including a particular mass feed rate of the welding filler material

A process for welding a component in which a recess is filled by welding tracks is provided. The process includes providing a recess with a contour which delimits an outer upper surface of the component with respect to the recess. The welding tracks are laid such that the welding tracks also reach the surface outside a contour of the recess and that a plurality of welding layers are used in order to fill the recess until a last layer protrudes completely beyond the surface.

Welding method and component

A process for determining the position of closed holes in a component is provided. By carrying out laser triangulation measurements on an uncoated component and a coated component with holes, the exact position of the holes to be reopened may be detected following the coating. A device used to carry out this process is also provided.

Surface analysis for detecting closed holes, and device

A welding apparatus for welding workpieces of high-temperature superalloys is provided. The welding apparatus includes a heat source for producing a heat input zone on the workpiece surface, a supplying device for supplying welding filler into the heat input zone and a transporting device for producing a relative movement between the heat source and the supplying device on the one hand and the workpiece surface on the other hand. The welding apparatus further includes a control unit with a control program, which carries out the relative movement in such a way that the welding power and the diameter of the heat input zone are set such that the cooling rate during the solidifying of the material is at least 8000 Kelvins per second.

Method and apparatus for welding workpieces of high-temperature superalloys

A guide vane for a gas turbine with a vane base body which is of single-piece design and comprises a profiled vane blade extending between a vane root and a cover plate and also the vane root formed integrally with the vane blade and the cover plate formed integrally with the vane blade, is intended, in a relatively simple way to be able to be matched to the individual conditions of use with especially little outlay on apparatus and logistics. For this purpose, according to the invention, a flow-routing body with an advance guide blade that is connected upstream of the vane blade as seen in the direction of flow of the working medium of the gas turbine is joined to the vane base body.

Gas turbine with a guide vane

A system and method for reconfiguring a turbine vane. In at least one embodiment, the system may be used to straighten an airfoil of a turbine vane segment to remove lean, twist, or racking, or any combination thereof. The airfoil may be straightened by fixing portions of the forward and aft hooks of the inner and outer shrouds of the turbine vane, restricting other portions of the forward and aft hooks of the inner and outer shrouds of the turbine vane to only move rotationally about a centerline of the inner or outer shrouds, and applying a load to various portions of the inner and outer shrouds and the airfoil to return the turbine vane to be within predetermined specifications.

Turbine vane restoration system

The invention relates to a guide blade segment of a thermal turbomachine, in particular a gas turbine, comprising a number of profiled blades which are arranged on a platform. A plurality of securing elements for securing the guide blade segment to an associated guide blade support are arranged on the side of the platform which is oriented away from the blade. The aim of the invention is to provide a guide blade segment which can be produced in a simple and economical manner avoiding casting problem areas enabling the guide blade segment to be attached in a particularly reliable and secure manner to the associated guide blade support. According to the invention, at least one section of at least one of the securing elements is a separately produced component which is rigidly connected to the platform or to an additional section of the securing element.

Stator blade segment of a thermal turbomachine, associated production method and also thermal turbomachine

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Berlin, Germany

Georg Bostanjoglo