An apparatus and method for passing fluid flow through at least a portion of a blade of turbomachinery such as a gas turbine or the like. The fluid flow is directed through a plurality of flow channels which are interwoven with each other. Each flow channel is non-intersecting with any other flow channel and thus does not contact fluid flowing within any other flow channel. The method and apparatus of this invention can be used to reduce heat transfer and thus reduce thermal stresses, particularly in the blade.
STATEMENT REGARDING FEDERALLY SPONSORED RESEARCH OR DEVELOPMENT
 This invention was made with government support under 101119631/105013 awarded by the United States Department of Energy. The government has certain rights in the invention.