the group of cooling holes 160 are spaced circumferentially about the third panel 90 it should be appreciated that each group of cooling holes 160 is positioned corresponding hot spots to facilitate channeling cooling fluid onto the corresponding hot spot third panel 90 includes any number of cooling holes 160 that facilitates cooling of liner 52 during operation of gas turbine engine 10 an inner surface 33 of liner 52 becomes hot and requires cooling consequently in the exemplary embodiment cooling features such as cooling holes 160 are positioned in liner 52 to facilitate channeling cooling fluid onto hot spots of liner 52 more specifically cooling holes 160 channel cooling fluid from outer passage 62 and or inner passage 64 to the combustion chamber 60 thus providing a layer of cooling fluid to inner surface 33 it should be appreciated that other embodiments may use any configuration of cooling holes 160 that enables cooling holes 160 to function as described herein similarly holes 160 could be in liner 54 to cool its outer surface during operation as atomized fuel is injecting into combustion chamber 60 and ignited heat is generated within combustion chamber 60 although air enters combustion chamber 60 through cooling features 160 and forms a thin protective.