A method of manufacturing a gas turbine engine turbine blade or vane component, comprising: providing a ceramic structure including a sacrificial ceramic core, the sacrificial ceramic core having a ceramic body corresponding to a cooling cavity of a heat exchanger segment, the ceramic body having an exterior surface comprising an outer surface and an inner surface interconnected to one another by a leading edge, a trailing edge, a tip facing edge and a base facing edge, the ceramic body defining a plurality of apertures extending between the outer surface and the inner surface, the plurality of apertures corresponding to a plurality of pedestals within the cooling cavity of the heat exchanger segment, the ceramic body including a trailing first pin and a leading first pin corresponding to a first inlet orifice and a second inlet orifice leading to the cooling cavity of the heat exchanger segment, the trailing first pin and the leading first pin extending away from the inner surface, the leading first pin spaced from the trailing first pin and in closer proximity to the leading edge than the trailing first pin, at least one of the trailing first pin and the leading first pin of the sacrificial ceramic core being obliquely angled relative to the inner surface; inserting the ceramic structure into a casting mold of the gas turbine engine turbine blade or vane component; introducing a component material into the casting mold; and removing the ceramic structure after the component material has solidified to a casted component, the casted component including the heat exchanger segment having the cooling cavity where the sacrificial ceramic core was disposed. providing a ceramic structure including a sacrificial ceramic core, the sacrificial ceramic core having a ceramic body corresponding to a cooling cavity of a heat exchanger segment, the ceramic body having an exterior surface comprising an outer surface and an inner surface interconnected to one another by a leading edge, a trailing edge, a tip facing edge and a base facing edge, the ceramic body defining a plurality of apertures extending between the outer surface and the inner surface, the plurality of apertures corresponding to a plurality of pedestals within the cooling cavity of the heat exchanger segment, the ceramic body including a trailing first pin and a leading first pin corresponding to a first inlet orifice and a second inlet orifice leading to the cooling cavity of the heat exchanger segment, the trailing first pin and the leading first pin extending away from the inner surface, the leading first pin spaced from the trailing first pin and in closer proximity to the leading edge than the trailing first pin, at least one of the trailing first pin and the leading first pin of the sacrificial ceramic core being obliquely angled relative to the inner surface; inserting the ceramic structure into a casting mold of the gas turbine engine turbine blade or vane component; introducing a component material into the casting mold; and removing the ceramic structure after the component material has solidified to a casted component, the casted component including the heat exchanger segment having the cooling cavity where the sacrificial ceramic core was disposed.