Ansaldo Energia Switzerland Ag

Alstom Technology Limited

General Electric Technology Gmbh

Igor Tsypkaykin

Herbert Brandl

Ulrich Rathmann

Beat Von Arx

Marco Lamminger

Stefan Andreas Retzko

Julien Nussbaum

Christoph Nagler

Brian Kenneth Wardle

Christoph Didion

Martin Balliel

Andre Saxer

Cyrille Bricaud

Philipp Indlekofer

Carl Berger

Steffen Holzhaeuser

Frank Gersbach

Ruben Valiente

Bruno Stephan

Philippe Thomas Lott

Cornelia Santner

Sinisa Ivkovic

Georgeta-Ileana Panaite

A blade includes a leading edge, a trailing edge, a pressure surface, a suction surface, a root end, a tip end, a tip shroud attached to the tip end, the tip shroud comprising a platform and a fin, wherein the fin having a leading edge side facing towards the leading edge of the blade, a trailing edge side facing towards the trailing edge of the blade, a back end and a front end, the leading edge side and the trailing edge side extending between the back end and the front end, the fin extending across the tip end of the blade at an angle to the chord of the blade at the tip end of the blade. A first platform portion extends from the leading edge side of the fin to the suction surface. A second platform portion extends from the trailing edge side of the fin to the pressure surface at the tip end of the blade.

Blade with tip shroud

A turbine blade having an airfoil and a fir tree root is disclosed. The fir tree root has a lengthwise direction, a crosswise direction extending between two lateral sides of the fir tree root, and a span direction extending from a root base towards an airfoil tip. The fir tree root includes a web interposed between each pair of at least two neighboring channels. For each web, a web-to-channel ratio with each of the two neighboring channels is chosen to be larger than or equal to 0.5 and is smaller than or equal to 0.85 at least at a position where the root width is a minimum load bearing root width in a load bearing section of the fir tree root. In another aspect, overall web-to-channel ratio is defined as a ratio between the sum of all web lengths and the sum of all channel lengths.

Turbine blade, set of turbine blades, and fir tree root for a turbine blade

It is disclosed an arrangement of a rotor and at least a blade. The blade includes a root, a platform and an airfoil. The rotor includes a seat for the root. The root has side walls which complement side walls of the seat and axial walls between the side walls. A chamber is provided between the root and the rotor. A shank cavity is provided between the root and the platform. A lock plate facing at least an axial wall is connected to the rotor and the blade. The lock plate has at least a slot on a side facing the root.

Arrangement of a rotor and at least a blade

A rotating blade for a gas turbine includes an airfoil extending in a longitudinal direction and having a leading edge and a trailing edge, whereby the airfoil is bordered at its outer end by a tip shroud, whereby the airfoil includes two or more internal passages, which run in longitudinal direction and are separated by solid webs, and whereby a plurality of shroud fins is arranged on top of the tip shroud to improve gas sealing against a corresponding stator heat shield. The stability and life time of the blade can be enhanced by selecting a position of each of the shroud fins to be exclusively above one of the webs and/or a leading edge wall.

Rotating blade for a gas turbine

A blade is disclosed for a gas turbine including an airfoil, which extends along a longitudinal axis from a blade root to a blade tip, and has a shroud segment at the blade tip. The shroud segment abuts with first and second edges against shroud segments of adjacent blades to form a ring-like shroud. The first and second edges are each provided with a respective side rail on the upper side of the shroud segment. Each of the side rails is subdivided into sections of different height and/or width.

Blade for a gas turbine

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

Growing community of inventors

Turgi, Switzerland

Igor Tsypkaykin