Multiple Compartment Spring-Loaded Inserts for Cooling a Turbine Blade Airfoil.
DEPARTMENT OF THE AIR FORCE WASHINGTON DC
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An airfoil of a turbine blade or the like has a pair of inserts positioned therein for causing impingement of cooling air flow axially along the internal surfaces of the airfoil walls. The inserts each have longitudinally-extending radial ribs and transversely-extending cross ribs which intersect and form compartments. Selected contiguous compartments are interconnected by passages in the radial ribs for cooling air flow therethrough in several successive steps so as to tailor the pattern of cooling of the walls to the particular pressure gradient existing along the airfoil. Also, resilient springs are provided between the inserts for loading them against the airfoil walls. Also, wear pads are located at the regions of contact between the inserts and the airfoil walls. Author
- Hydraulic and Pneumatic Equipment
- Jet and Gas Turbine Engines