Patent ID: 8167547

Claim:
A gas turbine engine comprising: a compressor section; a combustion section; a turbine section, said turbine section including at least one rotor for rotation about an axis, said rotor being provided with rotor blades, and said rotor being radially spaced from a static structure, knife edge seals extending close to a sealing surface to provide a seal, and said sealing surfaces having a plurality of sealing pockets associated with at least a plurality of said knife edge seals, said sealing pockets being defined by a radially inner surface spaced from a radially outer surface with said knife edge seals extending along a non-perpendicular angle relative to said axis, and with said sealing pockets being defined to have an angled surface extending between a radially inner sealing surface and a radially outer sealing surface at an angle that is non-perpendicular and non-parallel to said axis; said knife edge seals being associated with one of said rotor and said static structure, and said sealing surfaces being associated with the other; said knife edge seals and said angled surfaces are angled along a path towards said combustion section; and said knife edge seals each including a base and a tip, a thickness of said tip being less than a thickness of said base, the tip defined between opposed concave surfaces directly adjacent thereto, wherein a concave pocket is at least partially defined by said base, wherein said concave pocket and one of said opposed concave surfaces provides said knife edge seals with two concave surfaces disposed on a side thereof facing the combustion section.