Mtu Aero Engines Gmbh

Man Energy Solutions Se

Paul Storm

Martin Pernleitner

Dieter Freno

Peter Wiedemann

Thorsten Pöhler

Dirk Frank

Hernan Victor Arrieta

Rolf Kleinstueck

Electra Stavropoulou

A cooling system for cooling a turbine blade with a cooling fluid via an internal flow passage formed in the turbine blade extending from an inlet to an outlet edge having a first passage section defining a first flow direction, a second passage section defining a second flow direction, a wall between the first and second passage section and a diverter, between the first and the second passage section. The wall in a region of the diverter forms a pier head which extends into the region of the first passage section and thereby reduces the flow cross section of the flow passage.

Cooling system for actively cooling a turbine blade

A turbine vane of a gas turbine, especially a gas turbine aircraft engine, is disclosed. The turbine vane includes a vane base body with an outer surface forming a suction side and a pressure side, the outer surface of the vane base body being at least partially coated with a thermal barrier coating. The thermal barrier coating extends continuously or uninterruptedly at least largely over the suction side and largely over the pressure side of the surface of the vane base body, with the layer thickness of the thermal barrier coating being variable or adjustable.

Turbine vane of a gas turbine

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Munich, Georgia

Paul Storm