A mid-turbine frame (11; 57) comprising a plurality of vanes , each vane comprising: an airfoil (59; 186) extending between a leading edge and a trailing edge and being generally hollow; a radially outer platform and a radially inner platform ; and a rib (14; 190) on said radially outer platform , said rib (14; 190) being adjacent said trailing edge of said airfoil (59; 186), wherein said rib (14; 190) is on an outer surface of said outer platform , said rib (14; 190) is spaced beyond said trailing edge relative to said leading edge , said airfoil (59; 186) has a trailing edge at an inner surface of said outer platform , and said rib is aligned with a fillet merging into said trailing edge at said inner surface, wherein a width (d 3 ) of said rib (14; 190) is defined in a direction between said leading edge and said trailing edge , and a nominal wall thickness (d 1 ) of the inner and outer surfaces of said outer platform is defined, and a ratio of said nominal wall thickness (d 1 ) to said width (d 3 ) is between 1.1 and 6.0, wherein said rib (14; 190) has a height (d 2 ) extending radially outwardly that is greater than surrounding nominal wall portions, wherein said height (d 2 ) of said rib (14; 190) is defined from the inner surface of said outer platform to a radially outermost face of said rib (14; 190), and the nominal wall thickness (d 1 ) of said outer platform is defined between said inner surface and the outer surface of said outer platform , and a ratio of said nominal wall thickness (d 1 ) to said height (d 2 ) is between 1.1 and 6.0, wherein said rib (14; 190) is circumferentially discontinuous, and there are gaps between rib portions (14; 190). an airfoil (59; 186) extending between a leading edge and a trailing edge and being generally hollow; a radially outer platform and a radially inner platform ; and a rib (14; 190) on said radially outer platform , said rib (14; 190) being adjacent said trailing edge of said airfoil (59; 186), wherein said rib (14; 190) is on an outer surface of said outer platform , said rib (14; 190) is spaced beyond said trailing edge relative to said leading edge , said airfoil (59; 186) has a trailing edge at an inner surface of said outer platform , and said rib is aligned with a fillet merging into said trailing edge at said inner surface, wherein a width (d 3 ) of said rib (14; 190) is defined in a direction between said leading edge and said trailing edge , and a nominal wall thickness (d 1 ) of the inner and outer surfaces of said outer platform is defined, and a ratio of said nominal wall thickness (d 1 ) to said width (d 3 ) is between 1.1 and 6.0, wherein said rib (14; 190) has a height (d 2 ) extending radially outwardly that is greater than surrounding nominal wall portions, wherein said height (d 2 ) of said rib (14; 190) is defined from the inner surface of said outer platform to a radially outermost face of said rib (14; 190), and the nominal wall thickness (d 1 ) of said outer platform is defined between said inner surface and the outer surface of said outer platform , and a ratio of said nominal wall thickness (d 1 ) to said height (d 2 ) is between 1.1 and 6.0, wherein said rib (14; 190) is circumferentially discontinuous, and there are gaps between rib portions (14; 190). <EOS>