Flowpath assembly for gas turbine engine

A gas turbine engine comprising:

• a section including an array of blades rotatable in a gas path about a longitudinal axis;
• an end wall including an array of arc segments arranged circumferentially about the array of blades relative to the longitudinal axis, each of the arc segments including a main body extending in an axial direction between a first end portion and a second end portion relative to the longitudinal axis to establish a seal face that bounds the gas path, the seal face dimensioned to establish a clearance gap with the blades, and each of the arc segments including a first attachment portion fixedly attached to a static structure at a first attachment point such that the first end portion of the arc segment is cantilevered from the first attachment point;
• an array of vanes adjacent to the array of blades, wherein the vanes extend inwardly from the seal face of a respective one of the arc segments and at least partially across the gas path;
• and
• an array of spar members fixedly attached to the static structure, wherein each of the spar members extends at least partially through an inner cavity of a respective one of the vanes.