Flow sleeve with tabbed direct combustion liner cooling air

A combustion duct for a gas turbine engine comprising:

• a combustion liner to receive products of combustion, and deliver them downstream toward a turbine rotor;
• an outer housing positioned radially outwardly of said combustion liner;
• a flow sleeve positioned radially intermediate said outer housing and said combustion liner, said flow sleeve defining a chamber, radially outwardly of said flow sleeve, for receiving cooling air, and a plurality of holes through said flow sleeve to deliver cooling air against an outer periphery of said combustion liner;
• a plurality of tabs associated with at least some of said holes in said flow sleeve, said tabs being positioned to extend radially inwardly on a downstream side of said holes, and said tabs urging air that has passed through said holes back upstream;
• said plurality of tabs being associated with a ring that extends for more than 270° about a central axis of said flow sleeve;
• said ring having a cylindrical base within said flow sleeve, and said tabs extending radially inwardly for a greater distance than said base;
• said base having base holes to correspond with said holes in said flow sleeve;
• said flow sleeve and its plurality of holes being a separate part from said ring and said base holes;
• said base holes in said ring surrounding said holes in said flow sleeve;
• said plurality of tabs being circumferentially spaced;
• and
• there being spaces circumferentially intermediate said plurality of circumferentially spaced tabs.