Patent ID: 6286317
Filing Date: 2001-09-11
Classification: F23R,Y02T

Abstract:
A liner for a gas turbine engine combustor, said liner comprising:(a) a first section including a cavity, said cavity further comprising;(1) an aft wall;(2) a forward wall; and(3) all intermediate wall connected to said aft wall at one end and said forward wall at the other end;(b) a second section oriented substantially perpendicular to said aft wall of said first section; and(c) an annular cooling nugget joining said first and second liner sections for providing mechanical stiffness at a junction of said first and second liner sections, said cooling nugget further comprising:(1) a first portion connected to said aft wall of said first liner section;(2) a second portion connected to said second liner section; and(3) a third portion joining said first and second cooling nugget portions at a first end, said third cooling nugget portion extending radially from said first end with respect to a longitudinal axis through said gas turbine engine;wherein said cooling nugget is in flow communication with a cool air supply and is configured to provide a starter film of cooling air along respective surfaces of said first liner section and said second liner section.