A system comprising a gas turbine component (49,72) instrumented to provide a plurality of signals indicative of thermal measurements in a high temperature combustion environment of the gas turbine, the component comprising: a substrate; a thermal barrier coating deposited over at least a portion of the substrate; wherin the system further comprises a thermal imager having a field of view configured to sense infrared emissions from the turbine component, wherein an emissivity of a surface of the component being mapped is subject to variation in the combustion environment of the turbine; wherin the component further comprises at least one patch of a material having a sufficiently stable and known emissivity value to derive a temperature value when within the field of view of the thermal imager, said at least one patch disposed on an outer surface of the TBC; a first thermocouple leg disposed within a thickness of the component, wherein the first leg comprises a first material; at least two or more thermocouple legs (52, 53, 54, 55) comprising a different material relative to the first material, wherein said at least two or more legs is each electrically connected to the first leg to form individual thermocouple junctions (56, 57, 58, 59) along the first leg for conversion of respective thermal gradients to respective electrical signals, wherein the individual thermocouple junctions along the first leg collectively span a region of the component; and wherin the system further comprises a processor configured to process data indicative of the electrical signals from the thermocouple junctions relative to the temperature value of said at least one patch to calculate heat flux over the region of the component between the outer surface of the TBC and the thickness of the component. a substrate; a thermal barrier coating deposited over at least a portion of the substrate; wherin the system further comprises a thermal imager having a field of view configured to sense infrared emissions from the turbine component, wherein an emissivity of a surface of the component being mapped is subject to variation in the combustion environment of the turbine; wherin the component further comprises at least one patch of a material having a sufficiently stable and known emissivity value to derive a temperature value when within the field of view of the thermal imager, said at least one patch disposed on an outer surface of the TBC; a first thermocouple leg disposed within a thickness of the component, wherein the first leg comprises a first material; at least two or more thermocouple legs (52, 53, 54, 55) comprising a different material relative to the first material, wherein said at least two or more legs is each electrically connected to the first leg to form individual thermocouple junctions (56, 57, 58, 59) along the first leg for conversion of respective thermal gradients to respective electrical signals, wherein the individual thermocouple junctions along the first leg collectively span a region of the component; and wherin the system further comprises a processor configured to process data indicative of the electrical signals from the thermocouple junctions relative to the temperature value of said at least one patch to calculate heat flux over the region of the component between the outer surface of the TBC and the thickness of the component.