MICROCHANNEL SYSTEMS AND METHODS FOR COOLING TURBINE COMPONENTS OF A GAS TURBINE ENGINE

摘要

The present application and the resultant patent thus provide a microchannel system for cooling a hot gas path surface of a turbine. The microchannel system may include a turbine component having an outer surface extending along a hot gas path of the turbine, a microchannel defined within the turbine component and extending about the outer surface, and a number of pockets defined within the turbine component and positioned along the microchannel. The present application and the resultant patent further provide a method of forming a microchannel system for cooling a hot gas path surface of a turbine. The method may include the steps of forming a turbine component having an outer surface extending along a hot gas path of the turbine, defining a microchannel within the turbine component and extending about the outer surface, and defining a number of pockets within the turbine component and positioned along the microchannel.

主权项

1. A microchannel system for cooling a hot gas path surface of a turbine, the microchannel system comprising:
a turbine component comprising an outer surface extending along a hot gas path of the turbine; a microchannel defined within the turbine component and extending about the outer surface; and a plurality of pockets defined within the turbine component and positioned along the microchannel.