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. <EOS>