Blade outer air seal with compliant seal

A gas turbine engine comprising:

• a turbine section including,
• a core gaspath;
• a first row of vanes disposed in the core gaspath about an engine axis, a second row of vanes in the core gaspath and axially spaced from the first row of vanes, and a row of blades in the core gaspath axially between the first row of vanes and the second row of vanes, each vane of the first row of vanes including a platform with a radially-projecting flange;
• and
• a row of blade outer air seals axially between the first row of vanes and the second row of vanes and situated radially outwardly of the row of blades, each blade outer air seal including,
• a ceramic matrix composite body defining a core gaspath side facing the row of blades and bounding the core gaspath, a forward end, an aft end, and circumferential sides, the forward end abutting the radially-projecting flange of one of the vanes of the first row of vanes, the aft end including a radially inner wall and a radially outer wall defining radially therebetween a seal channel, the radially inner wall defining, opposite the seal channel, an aft portion of the core gaspath side, and the radially inner wall and the radially outer wall are of equal axial length, and
• a compliant seal disposed in the seal channel and sealing against at least one of the vanes of the second row of vanes.