Intercomponent seal for a gas turbine engine

A wall arrangement for a gas turbine engine, comprising:

• an annular wall comprising a plurality of circumferential wall segments, adjacent wall segments having opposing first and second end wall portions which define a separating gap therebetween,
• the gap including a saddle portion which faces radially outwards and comprises a first sealing face on the first end wall portion and a second sealing face on the second end wall portion;
• and,
• a longitudinal seal member having a curved sealing surface located within the saddle portion, wherein the curved sealing surface contacts the either or both first and second sealing faces along the length of the saddle portion in use
• wherein the seal member includes axially compressible portions which include localised reductions in the seal member thickness provided by a plurality of axially distributed slots or grooves which extend from an outer surface to a base within a body of the seal member and allow the seal member to bend longitudinally;
• wherein the base is a chord of an outer surface of the seal member or a curved surface within the seal member.