Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: In recent years, there has been an increase in both credit card/debit card fraud and online purchasing. Within the emergence of the electronic commerce marketplace, there does not exist the same protections for merchants as there exists for traditional brick-and-mortar stores. Therefore, to assist in preventing fraud, specifically online fraud, with credit/debit cards, another level of abstraction can be added to the purchase system where purchases can be identified as potentially fraudulent. The identification is through the use of correlating purchased items with account identifiers, where the purchase of certain categories of items can predict potential fraudulent procurement of credit/debit card numbers. Thus, by implementation of a simple system, the incidences of fraud can be reduced, protecting both merchants and consumers.