Alstom Technology Limited

Alstom (Switzerland) Ltd

General Electric Technology Gmbh

Heinz Neuhoff

Remigi Tschuor

Reinhard Fried

Iouri Strelkov

An arrangement is disclosed for the admission of cooling air to the internal walls of a component rotating about a rotation axis, such as a moving blade in a rotary machine. A component root can be fastened to a rotor unit in a rotationally fixed manner and adjoining in a radially extending manner is a one piece component airfoil in which at least one radially extending cooling passage region (K) is provided which, in the region of the component root, opens out via an opening into a cooling-air supply passage passing at least partly through the component root longitudinally relative to the rotation axis. A distribution plate forms a fluid-tight connection with an opening margin, surrounding the opening of the cooling passage region (K), at least during the rotation of the component about the rotation axis. The distribution plate provides at least one through-opening in the region of the opening of the at least one cooling passage region (K), through which through-opening cooling air passes from the axial cooling-air supply passage into the radial cooling passage region (K).

Arrangement for the admission of cooling air to a rotating component, in particular for a moving blade in a rotary machine

A turbomachine blade, in particular a turbine blade of a gas turbine includes a blade root with a cooling-fluid feed, a blade tip formed with a shroud element. At least one throughflow passage which extends in the blade longitudinal direction is arranged inside the airfoil. A shroud cooling passage is formed in the shroud element at least along a section of the latter, the shroud cooling passage being connected via an opening to the throughflow passage, and a cooling fluid flowing through this shroud cooling passage during operation of the turbomachine blade. At least one flow-guiding element for guiding at least some of the cooling-fluid flow flowing through the shroud cooling passage is arranged in the shroud cooling passage and/or in an inflow or outflow to or from the shroud cooling passage.

Turbomachine blade with fluidically cooled shroud

A process and a device for coating a temperature-stable component with a thermal protection layer ( ), in which the temperature-stable component has a surface ( ) which is to be coated with the thermal protection layer ( ) and at which there is at least one cooling-passage opening ( ) which is connected to a cooling passage running inside the component. During the coating a mass flow ( ) emerges through the cooling-passage opening ( ), the coating takes place by a coating mass flow ( ) directed onto the surface ( ) which is to be coated, and the mass flow ( ) emerges through the cooling-passage opening ( ) and the coating mass flow ( ) include an angle &agr;&ne;0&deg;.

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Waldshut-Tiengen, Germany

Heinz Neuhoff