Rolls-Royce Deutschland Ltd & Co. Kg

Alstom Technology Limited

Frank Haselbach

Erik Janke

Jens Taege

Timm Janetzke

Wolfgang Nitsche

Matthias Reyer

Christopher F Whitney

In impingement air cooling of gas turbine components, cooling air velocity packs of a certain amplitude and a given frequency are applied to impingement air openings, with intervallic annular swirl structures being formed which penetrate a cross-flow and hit a component to be cooled with high intensity, thus providing for efficient cooling. In order to obtain annular swirl structures with optimum cooling effect, the Strouhal number, which is determined by a ratio of amplitude, frequency of the velocity packs and size of impingement air cooling openings, ranges between 0.2 and 2.0, and preferably between 0.8 and 1.2.

Method for impingement air cooling for gas turbines

Passive shroud cooling of rotor blades () is accomplished by a multitude of cooling-air flows introduced into the hot-gas flow upstream of the rotor blades on the outer circumference, these cooling-air flows, depending on the aerodynamic and geometrical conditions, being orientated at a defined radial angle and a circumferentially related tangential angle such that the cooling air primarily and essentially hits the thermally highly loaded bottom surface () of the outer shrouds () allover. In the apparatus for the performance of the method, cooling air passages () tangentially and radially orientated to the hot-gas flow are provided in an area of a casing section () which protrudes beyond the stator blades () in the downstream direction, this casing section () interrupting the transport of cooling air in the axial direction.

Method and apparatus for the cooling of the outer shrouds of the rotor blades of a gas turbine

The invention relates to a turbine blade of a gas turbine with at least one cooling excavation which connects an interior and the surface of the turbine blade characterized in that a mouth of the cooling excavation is provided with a protrusion in its downstream area.

Turbine blade of a gas turbine with at least one cooling excavation

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Melbourne, United Kingdom

Frank Haselbach