tangential directions of the second region 2 may be selected to correspond with the location on the platform 16 expected to experience the highest temperatures during engine operation this may be determined by analysis or by testing after being used for convective cooling in the second region 2 the cooling air flows to the third region 3 the third region 3 may be provided with internal heat transfer enhancement features such as ribs fins pins or the like in the illustrated example it includes a plurality of spaced apart turbulence promoters or u201c turbulators u201d 46 the cooling air exits the third region 3 through a plurality of film cooling holes 48 best seen in fig2 the number size and location of the film cooling holes 48 is selected to discharge a protective film of cooling air over a portion of the platform 16 as used herein the term u201c film cooling hole u201d refers to a hole which is sized to discharge a film of cooling air over a surface so as to protect the surface from high temperature flowpath gases while the exact dimensions will vary with the specific design those skilled in the art will recognize a distinction between a u201c film cooling hole u201d and other types of holes such as u201c impingement cooling holes u201d and u201c purge holes u201d the film cooling holes 48 may be formed by known methods such as conventional drilling laser drilling or electrical discharge machining.