Combustor liner cooling system (USH0001380)
Original Publication Date: 1994-Dec-06
Included in the Prior Art Database: 2006-Mar-31
US Statutory Invention Registration (SIRs)
Related DocumentsPatent/Patent Application:
A gas turbine engine combustor cooling system for imperforate non-metallic combustor liners has a wall positioned adjacent to the liners forming therewith a cavity. The wall has a plurality of inlets for admitting cooling air into the cavity and a plurality of outlets for exhausting the cooling air into a separate passageway after it impinges the liners. The exhausted cooling air is transferred upstream of the liner where it is combined with fuel for burning rather than discharged downstream as cooling film.