Ansaldo Energia Switzerland Ag

Marco Lamminger

Igor Tsypkaykin

Stefan Andreas Retzko

Martin Balliel

Cyrille Bricaud

Frank Gersbach

Carl Berger

Carlos Simon-Delgado

Christoph Didion

Steffen Holzhaeuser

Julien Nussbaum

Philippe Thomas Lott

Cornelia Santner

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 rotating gas turbine blade is disclosed which includes an airfoil with a suction side and a pressure side, the airfoil extending in a radial direction from a blade root to a blade tip. The blade tip includes a tip shroud, the airfoil having internal cooling passages for a cooling medium, which extend through the tip shroud. Outlet ports are provided above a selected internal airfoil cooling passage for the cooling medium to be ejected above the tip shroud in a direction of the blade's pressure side. Dust accumulation is avoided at the tip end of the selected internal cooling passage.

Rotating gas turbine blade and gas turbine with such a blade

The present invention relates to a rotor assembly for a rotary machine such as a gas turbine. The present solution provides a sealing wire located inside a groove engraved in the rotor body. The sealing wire is responsive to radial centrifugal forces acting during normal operation of the machine, and moves radially in the groove until a sealing configuration is achieved such to prevent damaging hot leakage towards machine components.

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Ennetbaden, Switzerland

Marco Lamminger