and airfoil without being supplemented with additional cooling fluids along the flow path application_number US 4923905 A description as shown in fig1 7 this invention is directed to a platform cooling system 10 usable to preheat cooling fluids in a turbine engine the platform cooling system 10 is particularly useful in composite airfoils 12 in which temperature gradients cause layers of the airfoil 12 to delaminate and bonds between adjacent layers to break in addition the platform cooling system 10 may be incorporated with an internal cooling system 14 in the airfoil 12 such that the airfoil is cooled with cooling air in a serial cooling manner such that cooling fluids passed through the platform cooling system 10 flow through the airfoil 12 without being supplemented by lower temperature cooling air while in the airfoil 12 the platform cooling system 10 may receive cooling fluids from a compressor not shown or other source increase the temperature of the cooling fluids and pass the cooling fluids on to a cooling system 14 in the airfoil 12 with a temperature that is greater than a temperature of the cooling fluids entering the platform cooling system 10 in at least one embodiment the cooling fluids which may be but are not limited to.