Patent ID: 10830095

Abstract:
An impingement cooling system for a gas turbine engine includes an initial impingement surface (10) with a centrally located opening (12). A plurality of channels (14) and plurality of sub-channels (22) extends radially outward from the opening (12) and are formed by a plurality of fixtures (16) and plurality of sub-fixtures (24) that each separates each adjacent channel (14) and sub-channel (22) respectively. The plurality of fixtures (16) and plurality of sub-fixtures (24) each have a rounded upstream end (18) in a plane parallel relative to the initial impingement surface (10). The plurality of fixtures (16) and the plurality of sub-fixtures (24) each have a concave shape along a middle portion (54, 56) of the fixture (16) and sub-fixture (24) along an axis perpendicular to the initial impingement surface (10). The plurality of channels (14) is divided into the plurality of sub-channels (22) extending radially outward of an inlet of each channel (14) from a stagnation point (34) created in the channel at an upstream end (26) of the sub-fixture (24).