Siemens Energy Global Gmbh & Co. Kg

Siemens Aktiengesellschaft

Daniel Vöhringer

Daniel M Eshak

Samuel R Miller, Jr

Heiko Lammers

Susanne Kamenzky

Kay Krabiell

Björn Anders

Constantin Garske

Ricardo Nilsson

Heinrich Stüer

Reiner Anton

Stefan Schmitt

Yuekun Zhou

Andrew Lohaus

Markus Lempke

Jörg Ziege

Albin Bajric

Jörg Kiebert

Mike Bindrich

Jr Samuel R Miller

A turbine rotor having an improved rotor tip, which has at least one cooling channel in the rotor blade, the cooling channel, in the region of its cuspidal point, having at least one locally limited constriction that is caused by a thickened portion at the end of a partition of the cooling channel.

Rotor-blade tip including cooling configuration

A method for repairing a damaged leading or trailing edge region of a metallic turbine blade, which has a suction-side blade wall, a pressure-side blade wall and a leading edge and a trailing edge, includes: removing the damaged leading or trailing edge region, with a cutout being formed; providing a replacement part which can be inserted in form-fitting fashion into the cutout and which restores the intended geometry of the turbine blade; inserting the replacement part in form-fitting fashion into the cutout in a predetermined insertion direction, and cohesively connecting the replacement part to the turbine blade, wherein mechanical connection of the replacement part and turbine blade using separate fastening elements is performed in addition to the cohesive connection.

Method for repairing a damaged leading or trailing edge region of a metallic turbine blade

A method for repairing an at least externally coated hollow component. The direct mechanical machining of a coated component after use removes the need for a coating-removal and selective hollowing step and a selective repair of cracks, since a design adaptation leads to a component being engineered or used such that it can be used again as a result of external dimensional stipulations.

Repair of coated components using design adaptation

A method is provided for machining an airfoil section () of a turbine blade or vane produced by a casting process. The airfoil section () has an outer wall () delimiting an airfoil interior having one or more internal cooling passages (). The method involves: receiving design data pertaining to the airfoil section (), including a nominal outer airfoil form () and nominal wall thickness (T) data; generating a machining path by determining a target outer airfoil form (), the target outer airfoil form () being generated by adapting the nominal outer airfoil form () such that a nominal wall thickness (T) is maintained at all points on the outer wall around the one or more internal cooling passages () in a subsequently machined airfoil section; and machining an outer surface () of the airfoil section () produced by the casting process according to the generated machining path, to remove excess material to conform to the generated target outer airfoil form ().

Adaptive machining of cooled turbine airfoil

A gas turbine blade having a casted metal airfoil, the airfoil has a main wall defining at least one interior cavity, having a first side wall and a second side wall, which are coupled to each other at a leading edge and a trailing edge, extending in a radial direction from a blade root to a blade tip and defining a radial span from 0% at the blade root to 100% at the blade tip. The main airfoil has a radial span dependent chord length defined by a straight line connecting the leading edge and the trailing edge as well as a radial span dependent solidity ratio of metal area to total cross-sectional area. Solidity ratios in a machined zone of the airfoil from 80% to 85% of span are below 35%, in particular all solidity ratios in the zone.

Gas turbine blade and method for producing such blade

A bladed rotor system includes first and second sets of blades with respective airfoils each having at least one internal cavity. The airfoils of both the first and second sets of blades have identical outer shapes defined by an outer surface of an outer wall of the respective airfoils. The airfoils of the first set of blades are distinguished from the airfoils of the second set of blades by a geometry and/or position of at the least one internal cavity, which is unique to blades of a given set. The natural frequency of a blade of the first set differs from the natural frequency of a blade of the second set by a predetermined amount. The blades of the first set and the second set are alternately arranged in a periodic fashion in said circumferential row, to provide a frequency mistuning to stabilize flutter of the blades.

Mistuning of turbine blades with one or more internal cavities

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Berlin, Germany

Daniel Vöhringer