An internal cooling system (14) including an impingement jet strike channel system (16) for increasing the effectiveness of impingement jets (18) is disclosed. The impingement jet strike channel system (16) may include an impingement jet strike cavity (20) offset from one or more impingement orifices (22). A plurality of impingement jet strike channels (24) may extend radially outward from the impingement jet strike cavity (20) forming a starburst pattern of impingement jet strike channels (24) and may be formed by a plurality of ribs (26) that each separate adjacent impingement jet strike channels (24). The ribs (26) forming the impingement jet strike channels (24) may be split one or more times into multiple channels to increase the number of stagnation points (28, 38, 52) to increase the cooling capacity. The impingement jet strike channel system (16) may be used within components, such as, but not limited to, gas turbine engines (12), including vane inserts, airfoil leading edge cooling systems, platforms, advanced transitions, acoustic resonators, ring segments and the like.