Turbine Band Cooling System.
Abstract
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 15, 1976
- Accession Number
- ADD002966
Entities
People
- Craig H. Muhlhauser
Organizations
- United States Department of the Air Force