SEGMENTED TURBINE BLADE SQUEALER TIP AND COOLING METHOD

摘要

Gas turbine engine blade squealer tips incorporate cooling slots formed in the suction side rail downstream of the leading edge for directing cooling gas flow along an inside edge of the squealer tip pressure side rail. Some embodiments incorporate a tip fin on the suction side rail proximal a cooling slot. Segmented suction side rail embodiments abrade opposing turbine casing abradable surfaces prior to potential contact with the pressure side rail, reducing likelihood of pressure side rail friction heating. During turbine engine operation cooler pressure side rails reduce likelihood of squealer tip erosion.

主权项

1. A gas turbine engine blade squealer tip, comprising:
an airfoil planform tip plate having along its outer periphery downstream from its leading edge and upstream from its trailing edge opposed and laterally separated projecting concave pressure and convex suction rails respectively having inner and outer faces; an enclosed tip cavity defined between the tip plate and respective inner faces of the pressure and suction rails from the leading to trailing edges; and at least one slot formed through respective inner and outer faces of the suction rail downstream of the leading edge, the slot in communication with the tip cavity and oriented for directing cooling air flow there through and downstream along the pressure rail inner face.