ASYMMETRIC RADIAL SPLINE SEAL FOR A GAS TURBINE ENGINE
A shroud apparatus for a gas turbine engine includes: an annular shroud segment (26) having an arcuate bottom wall (52) defining an arcuate inner flowpath surface(62), spaced-apart forward and aft walls (54, 56) extending radially outward from the bottom wall (52), and spaced-apart side walls (58) extending radially outward from the bottom wall (52) and between the forward and aft walls (54, 56), each side wall (58) defining an end face (74) which includes: an axial slot (76) extending in a generally axial direction along the end face (74); a first radial slot (78) extending in a generally radial direction along the end face (74), and intersecting the axial slot (76); an axial spline seal (82) received in the axial slot (76); and a first radial spline seal (84) having an L-shape with radial and axial legs (88, 90), the radial leg (88)being substantially longer than the axial leg (90), wherein the radial leg (88) is received in the first radial slot (78), and the axial leg is received in the axial slot (76).