Patent ID: 7249928

Claim:
A turbine assembly for a gas turbine engine, comprising: a nozzle segment comprising: an airfoil-shaped vane having a root, a tip, a leading edge, a trailing edge and opposed pressure and suction sides; and an arcuate inner band attached to said root of said vane, said inner band including an inner flowpath surface bounded at forward and aft ends thereof by a forward-facing surface and an aft-facing surface, respectively; a rotatably-mounted turbine blade disposed aft of and in flow communication with said nozzle segment, said turbine blade including an arcuate blade platform defining a second inner flowpath surface; and a purge cavity defined between said nozzle segment and said turbine blade, said purge cavity in flow communication with a secondary flowpath of said engine; wherein the juncture of said inner flowpath surface and said aft-facing surface of said inner band is contoured so as to induce swirling vane flow into said purge cavity.