Alstom Technology Limited

Sacha Parneix

Ulrich Rathmann

Beat Von Arx

Shailendra Naik

Stefan Schlechtriem

Shailandra Naik

Helene Saxer-Felici

Remigi Tschuor

Kenneth Hall

A cooled blade for a gas turbine has a blade airfoil, which emerges from a blade root and a blade shank and has a leading edge and a trailing edge and, within the blade airfoil, a plurality of sequential coolant ducts, in terms of flow, extending in a radial direction. A first coolant duct along the leading edge, and a second coolant duct along the trailing edge, have a main flow of a coolant flowing through them from the blade root to the tip of the blade airfoil. An inlet of the first coolant duct is in connection with a main coolant inlet, and an outlet of the first coolant duct is in connection with the inlet to the second coolant duct via a first deflection region. A third coolant duct is arranged between the first and the second coolant duct and a second deflection region. An additional flow of cooler coolant provided from outside is added from the third coolant duct into the heated main flow of the coolant flowing into the second coolant duct. An orifice can, for example, extend from the main coolant inlet to the second deflection region.

Cooled blade for a gas turbine

A cooled blade or vane for a gas turbine has a main blade or vane part which starts from a blade or vane root and a blade or vane shank and has a leading edge and a trailing edge, as well as, inside the main blade or vane part, a plurality of cooling ducts, which extend in the radial direction, are connected in series in terms of flow and of which a first cooling duct has a main stream of a cooling medium flowing through it along the leading edge. A second cooling duct has a main stream of a cooling medium flowing through it along the trailing edge, from the blade or vane root to the tip of the main blade or vane part. The outlet of the first cooling duct is in communication, via a first diverting region, a third cooling duct arranged between the first and second cooling ducts, and a second diverting region, with the inlet of the second cooling duct.

Cooled blade or vane for a gas turbine

A thermally loaded component has at least one cooling passage for the flow of a cooling fluid passing through it. In the region of a bend, at least one diverter device for the integral capturing of the flow of the cooling fluid is provided within the cooling passage. The diverter device comprises, over the height of the cooling passage, two diverter parts which are spaced apart from one another. The diverter maybe cast with a notch therein so that during cooling, the diverter breaks into separated portions proximate the notch.

Thermally loaded component

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Sacha Parneix