A gas turbine engine comprising: a combustor section; a compressor section; and a turbine section downstream from the combustor section, the turbine section comprising at least one component, wherein the at least one component comprises: a platform; an airfoil body extending from the platform and having a leading edge, a trailing edge, a pressure side, and a suction side; and a partitioned baffle (400;500;600;700) installed within the airfoil body, the partitioned baffle comprising: a baffle body defining a first cavity, the baffle body having a first inlet (410;510;710) and at least one first impingement hole (414;514;614;714) arranged for flow to pass through the first cavity from the first inlet to the at least one first impingement hole; and a partitioned channel (404;504;604;704) installed within the baffle body and defining a second cavity (408;508;608;708) that is fluidly separate from the first cavity, wherein the partitioned channel has a second inlet (412;512;712) and at least one second impingement hole (416;516;616;716) extending through the baffle body, wherein a flow through the second cavity flows from the second inlet to the at least one second impingement hole, wherein the baffle body is configured to receive cooling air from a first source and the partitioned channel is configured to receive cooling air from a second source, wherein the first source is different from the second source; wherein the at least one second impingement hole (416;516;616;716) is arranged proximate a hot spot of the airfoil body. a combustor section; a compressor section; and a turbine section downstream from the combustor section, the turbine section comprising at least one component, wherein the at least one component comprises: a platform; an airfoil body extending from the platform and having a leading edge, a trailing edge, a pressure side, and a suction side; and a partitioned baffle (400;500;600;700) installed within the airfoil body, the partitioned baffle comprising: a baffle body defining a first cavity, the baffle body having a first inlet (410;510;710) and at least one first impingement hole (414;514;614;714) arranged for flow to pass through the first cavity from the first inlet to the at least one first impingement hole; and a partitioned channel (404;504;604;704) installed within the baffle body and defining a second cavity (408;508;608;708) that is fluidly separate from the first cavity, wherein the partitioned channel has a second inlet (412;512;712) and at least one second impingement hole (416;516;616;716) extending through the baffle body, wherein a flow through the second cavity flows from the second inlet to the at least one second impingement hole, wherein the baffle body is configured to receive cooling air from a first source and the partitioned channel is configured to receive cooling air from a second source, wherein the first source is different from the second source; wherein the at least one second impingement hole (416;516;616;716) is arranged proximate a hot spot of the airfoil body. a platform; an airfoil body extending from the platform and having a leading edge, a trailing edge, a pressure side, and a suction side; and a partitioned baffle (400;500;600;700) installed within the airfoil body, the partitioned baffle comprising: a baffle body defining a first cavity, the baffle body having a first inlet (410;510;710) and at least one first impingement hole (414;514;614;714) arranged for flow to pass through the first cavity from the first inlet to the at least one first impingement hole; and a partitioned channel (404;504;604;704) installed within the baffle body and defining a second cavity (408;508;608;708) that is fluidly separate from the first cavity, wherein the partitioned channel has a second inlet (412;512;712) and at least one second impingement hole (416;516;616;716) extending through the baffle body, wherein a flow through the second cavity flows from the second inlet to the at least one second impingement hole, wherein the baffle body is configured to receive cooling air from a first source and the partitioned channel is configured to receive cooling air from a second source, wherein the first source is different from the second source; wherein the at least one second impingement hole (416;516;616;716) is arranged proximate a hot spot of the airfoil body. a baffle body defining a first cavity, the baffle body having a first inlet (410;510;710) and at least one first impingement hole (414;514;614;714) arranged for flow to pass through the first cavity from the first inlet to the at least one first impingement hole; and a partitioned channel (404;504;604;704) installed within the baffle body and defining a second cavity (408;508;608;708) that is fluidly separate from the first cavity, wherein the partitioned channel has a second inlet (412;512;712) and at least one second impingement hole (416;516;616;716) extending through the baffle body, wherein a flow through the second cavity flows from the second inlet to the at least one second impingement hole, wherein the baffle body is configured to receive cooling air from a first source and the partitioned channel is configured to receive cooling air from a second source, wherein the first source is different from the second source; wherein the at least one second impingement hole (416;516;616;716) is arranged proximate a hot spot of the airfoil body.