Gas turbine engine stator vane platform reinforcement

A gas turbine engine comprising:

• compressor and turbine sections;
• a combustor provided axially between the compressor and turbine sections;
• a turbine vane in the turbine section that is supported by static structure and includes:
• a first platform and a second platform radially spaced apart from one another;
• first and second airfoils circumferentially spaced from one another and interconnecting the first and second platforms;
• the first platform having a gas path side facing the airfoils and a non-gas path side opposite the gas path side, and a circumferentially extending rail provided on the first platform extending circumferentially from the first airfoil to the second airfoil and extending radially outward from the gas path side to the non-gas path side to form a radial extremity, and a pocket on the non-gas path side between the first platform and the rail;
• and
• a reinforcement comprises a circumferential width that is radially inward of the radial extremity, the reinforcement is arranged in the pocket and joining the first platform and the rail, the reinforcement contacting the first platform and the rail, the reinforcement includes a variable thickness in the circumferential direction and is arranged generally centrally between the first and second airfoils, wherein the thickness is largest at a point centered between the first and second airfoils.