Turbine Band Cooling System.
DEPARTMENT OF THE AIR FORCE WASHINGTON D C
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The patent application relates to gas turbines and specifically to a cooling system for the overhang of a stator band segment which includes a cooling passage in the overhang that is adjacent to a plenum chamber formed by a baffle assembly. Metering conduits allow the transfer of air through the stator into the plenum chamber and air holes in the plenum chamber pass air into the cooling passage. A convection conduit in the overhang allows air to pass from the passage and also permits further cooling. A slip joint is interposed between the baffle assembly and the air passage to allow for thermal expansion with the slip joint having holes in alignment with the baffle assembly holes.
- Jet and Gas Turbine Engines