a portion of the gas turbine engine is shown in cross section in fig1 . a flow path 10 for the working medium gases of the engine extends axially through the portion of the engine shown . air and fuel are burned in a combustion chamber 12 to add thermal energy to the medium gases flowing therethrough . the effluent from the chamber is discharged in the downstream direction onto a turbine section 14 . the turbine section is formed of a stationary or stator assembly 16 and a rotating or rotor assembly 18 . the stator assembly has a case 20 which is located radially outward of the flow path and a plurality of stator vanes , as represented by the single vane 22 , which extend inwardly from the case and across the flow path . the rotor assembly includes a rotor disk 24 and a plurality of rotor blades , as represented by the single blade 26 , which extend outwardly across the flow path from the periphery of the disk . the fig2 cross sectional view of the vane 22 reveals the features of the internal and external structure . a leading edge 28 having incorporated therein a plurality of leading edge holes 30 is positioned at the upstream end of the vane with respect to the approaching flow 32 . a hollow cavity 34 is formed between a suction side wall 26 and a pressure side wall 38 . a plate - like , suction side baffle 42 is disposed within the cavity 34 and is spaced closely apart from the suction side wall . a multiplicity of impingement orifices 44 are incorporated within the baffle 42 . a plate - like , pressure side baffle 46 is disposed within the cavity 34 and is spaced closely apart from the pressure side wall . a multiplicity of impingement orifices 44 are incorporated within the baffle 46 . a sealing rib 48 separates the suction side baffle from the pressure side baffle . a multiplicity of stand - offs 50 hold the baffles apart from the cavity walls . a suction side chamber 52 is formed between the suction side baffle 42 and the suction side wall 36 . a pressure side chamber 54 is formed between the pressure side baffle 46 and the pressure side wall 38 . in the construction shown , a second hollow cavity 56 is formed between the suction side wall 36 and the pressure side wall 38 at a location downstream of the first hollow cavity 34 . within the cavity 56 a plate - like , suction side baffle 58 is spaced closely apart from the suction side wall and a plate - like , pressure side baffle 60 is spaced closely apart from the pressure side wall . a downstream suction side chamber 62 and a downstream pressure side chamber 64 are formed within the second hollow cavity 56 and correspond to the pressure side and suction side chambers of the first hollow cavity 34 . a first set of suction side holes 66 lead from the suction side chamber 52 and a second set of suction side holes 68 lead from the suction side chamber 62 . a first set of pressure side holes 70 lead from the pressure side chamber 54 and a second set of pressure side holes 72 lead from the pressure side chamber 64 . a third hollow cavity 74 having trailing edge holes 76 extending therefrom is shown at the trailing edge of the vane . during operation of the engine , cooling air is flowable to the hollow cavities for cooling the vane . the air which is directed through the orifices 44 to the respective chambers is accelerated to velocities at which the air impinges upon the opposing walls . at the zones of impinging flow the heat transfer characteristics between the walls and the cooling medium are improved when compared to conventional convective cooling systems . the baffles perform the additional function of confining the cooling medium to the wall region for convective cooling of the walls . the leading edge holes 30 , the suction side holes 66 and 68 , and the pressure side holes 70 and 72 are positioned about the vane so as to cause cooling air emitted therefrom to flow over the exterior of the suction side and pressure side walls . the holes and the impingement orifices 44 are sized and spaced so as to establish a substantially uniform pressure differential across the vane walls . at each cavity the pressure of the cooling air within the pressure side chamber is greater than the pressure of the cooling within the suction side chamber . similarly , the pressure within each successively downstream pressure side chamber is less than the pressure of the air within the upstream chamber . in this manner the pressure profile at the interior of the vane walls is made to conform to the pressure profile in the working medium flow path along the exterior of the vane . the extent of conformity depends in each individual engine upon the number of cavities utilized . in a construction wherein a particularly high degree of correspondence is required the number of cavities is increased . the concepts described in this section of the specification have been applied to a turbine vane . the concepts , however , are equally applicable to other coolable airfoils such as rotor blades . a particularly key element in implementing the concepts disclosed is the separation of the pressure side and suction side chambers . any leakage from the pressure to the suction chamber not only decreases the exuding velocities of the film cooling air over the pressure side surfaces but also increases the exuding velocity of the film cooling air over the suction side surface . this unpredicable deviation in pressure differential is substantially eliminated by the present construction . although the invention has been shown and described with respect to a preferred embodiment thereof , it should be understood by those skilled in the art that various changes and omissions in the form and detail thereof may be made therein without departing from the spirit and the scope of the invention .