The present invention relates to a gas turbine engine (20) including a turbine section (28) having a vane assembly (76) including a radially outer platform (168), a radially inner platform (170) and a first airfoil (66) extending between the radially outer platform (168) and the radially inner platform (170). A rail (172) extends radially inward from the inner platform (170). The vane assembly (76) comprises a connected passage (191) mutually formed by and including an airfoil passage (192) within the first airfoil (66), a platform passage (193) located within the inner platform (170) and a rail passage (194) located within the rail (172). This structure allows for a specific control of relative cooling for the different section of the turbine vane and enables to form the connected passage by use of a single core (195).