Cooling Module Design and Method for Cooling Components of a Gas Turbine System

摘要

A cooling arrangement in a gas turbine system (120). The arrangement includes a plurality of flow network units (208) to transfer heat to cooling fluid, at least one unit including first (218), second (220), and third (222) flow sections between openings (64a) in a first wall (66) and an opening in a second wall (68) to pass cooling fluid through the walls. The first section includes first flow paths, between the openings in the first wall and the second section, extending to the second section. The third section includes third flow paths, between the second section and the opening in the second wall, to effect flow of cooling fluid. The second section includes one or more cooling fluid flow paths between the first section and the third section. The number of flow paths in the second section is fewer than the number of first flow paths and fewer than the number of third flow paths.

主权项

1. A turbine airfoil comprising:
a root; a tip; a pressure side wall; a suction side wall; a leading edge connecting the pressure side wall to the suction side wall; a trailing edge connecting the pressure side wall to the suction side wall; a first plurality of cooling apertures defined through the trailing edge; and a cooling arrangement configured to route a cooling fluid from an entrance of the cooling arrangement to an exit of the cooling arrangement, the exit coinciding with at least one of the first plurality of cooling apertures; wherein:
the cooling arrangement comprises a first arrangement of serially interconnected flow sections each comprising one or more chambers, each chamber operatively defining a chamber primary cooling fluid flow direction of a sequence of cooling fluid flow directions, each chamber primary cooling fluid flow direction selected from:
a radial direction aligned substantially parallel to a path between the root and the tip;a trailing edge direction substantially parallel to a path between the leading edge and the trailing edge; anda transverse direction aligned substantially parallel to a path between the suction side wall and the pressure side wall; the first arrangement of serially interconnected flow sections comprises at least a first flow section, a second flow section, and a third flow section; the first arrangement of serially interconnected flow sections is configured to pass the cooling fluid through at least a portion of the turbine airfoil, and remove heat therefrom; the first section defines a first plurality of first flow paths extending between the entrance and the second section; the first section is configured to effect flow of the cooling fluid between the entrance and the second section; the third section defines a third plurality of third flow paths extending between the second section and the exit, the third section configured to effect flow of the cooling fluid from the second section and through the third flow paths; the second section defines one or more second flow paths extending between the first section and the third section, the second section configured to effect flow of the cooling fluid between the first flow paths and the third flow; and the number of second flow paths being less than the number of first flow paths.