Siemens Energy Global Gmbh & Co. Kg

Siemens Aktiengesellschaft

Ralph Gossilin

Fathi Ahmad

Andreas Heselhaus

Nihal Kurt

Björn Buchholz

Daniela Koch

Marco Schüler

Stephan Schwarz

Marco SCHÜLER

Olivier Gand

A wall of a hot gas part, having a first surface subjectable to a cooling fluid, a second surface located opposite of the first surface and subjectable to a hot gas and, at least one film cooling hole extending from an inlet area located within the first surface to an outlet area located within the second surface for leading the cooling fluid from the first surface to the second surface. The respective film cooling hole has a diffusor section located upstream of the outlet area, the diffusor section is bordered at least by a diffusor bottom and two opposing diffusor side walls, wherein the diffusor section has a delta wedge element for dividing the cooling fluid flow into two sub-flows and subsequent formation of a pair of delta vortices. The respective delta wedge element protrudes in a step-wise manner from the diffusor bottom and is, in a top view, triangular-shaped.

Wall comprising a film cooling hole

A turbine blade or vane for a gas turbine has successively along a radial direction of the gas turbine, a root for attaching the turbine blade or vane to a carrier, a platform, an aerodynamically shaped hollow airfoil with a suction side wall and a pressure side wall extending with respect to the direction of a hot gas flow from a common leading edge to common a trailing edge and extending transversely thereof from the platform to an airfoil tip. The airfoil has at least one cooling cavity extending in a cooling fluid flow direction from a platform level to the airfoil tip, the cooling cavity in fluid connection with a number of cooling fluid outlets distributed along the trailing edge through an array of impingement cooling features located therebetween. The array extends into a region which is located radially outside the airfoil within the platform having impingement cooling features.

Turbine blade or a turbine vane for a gas turbine

A cast turbine blade having a platform and hollow blade airfoil arranged thereon, wherein the blade airfoil has a pressure-side blade wall and a suction-side blade wall that extend, along a centrally arranged curved profile centerline, from a common leading edge to a common trailing edge, and having a transition, with an outer contour profile, between the blade airfoil and the platform. The blade walls each have a locally determined blade wall thickness, wherein the turbine blade has, internally, a contour profile that partially matches the outer contour profile of the transition such that the region of the transition has an essentially constant blade wall thickness. In the transition, the contour profile at a surface section of the blade airfoil facing the leading edge is such that the blade wall thickness is increased there in comparison to the blade wall thickness of the transition away from the leading edge.

Turbine blade

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Oberhausen, Germany

Ralph Gossilin