Assembly for maintaining and retaining a gas turbine engine component

A gas turbine engine, comprising:

• a turbine section disposed about an engine axis, the turbine section including a ring comprising an inner ring and an outer ring that define a gas path therebetween, at least one of the inner ring or the outer ring include two or more rings;
• at least one vane disposed in the gas path and supported by the inner ring and the outer ring, the at least one vane includes an inner platform, an outer platform, and an airfoil section disposed therebetween,
• wherein a first inner ring of the two or more inner rings or a first outer ring of the two or more outer rings include a fore end designed to axially abut an opposing flange defined by the outer platform, and either a contact surface designed to radially abut an opposing contact surface defined by the outer platform, or an angled contact surface designed to abut an opposing angled contact surface defined by the inner platform or both the contact surface designed to radially abut the opposing contact surface defined by the outer platform and the angled contact surface designed to abut the opposing angled contact surface defined by the inner platform.