Gas turbine cooling

摘要

A gas turbine having internally cooled thermal barrier coated turbine blades is disclosed. The turbine blades are made from an alloy substrate exhibiting a low coefficient of thermal expansion, an intermediate bond coating and an exterior ceramic coating. Cooling fluid is supplied from the shaft of the compressor where it flows into and out of the turbine blade. Thermal barrier coated turbine blades result in more efficient gas turbine designs.