TURBINE AIRFOIL WITH AMBIENT COOLING SYSTEM

摘要

A turbine airfoil usable in a turbine engine and having at least one ambient air cooling system is disclosed. At least a portion of the cooling system may include one or more cooling channels configured to receive ambient air at about atmospheric pressure. The ambient air cooling system may have a tip static pressure to ambient pressure ratio of at least 0.5, and in at least one embodiment, may include a tip static pressure to ambient pressure ratio of between about 0.5 and about 3.0. The cooling system may also be configured such that an under root slot chamber in the root is large to minimize supply air velocity. One or more cooling channels of the ambient air cooling system may terminate at an outlet at the tip such that the outlet is aligned with inner surfaces forming the at least one cooling channel in the airfoil to facilitate high mass flow.

主权项

1. A turbine airfoil, comprising:
a generally elongated hollow airfoil formed from an outer wall, and having a leading edge, a trailing edge, a pressure side, a suction side, a root at a first end of the airfoil and a tip at a second end opposite to the first end, and an ambient air cooling system positioned within interior aspects of the generally elongated hollow airfoil; at least one cooling channel of the ambient air cooling system in the generally elongated hollow airfoil extending radially outward from an inlet at a proximal end of the root; wherein the ambient air cooling system has a tip static pressure to ambient pressure ratio of at least 0.5.