Combustion liner seal with heat transfer augmentation

A combustion liner for a gas turbine engine, said combustion liner comprising:

• a centerline, a first liner end, a second liner end, a first portion proximate said first end, and a second portion fixed downstream to said first portion and extending to said second end, said second portion comprising:
• an inner liner wall;
• an outer liner wall;
• said second end being a downstream end of said liner;
• a plurality of first feed holes parallel to said centerline;
• a cooling ring in fixed relation to said outer liner wall and located radially outward of said outer liner wall to thereby form an annulus therebetween having an annulus height, said cooling ring having a cooling ring inner wall, a cooling ring outer wall, a first cooling ring end, and a second cooling ring end;
• a first spring seal overlapping said cooling ring outer wall and having a first length and a plurality of first axial slots, with each of said first axial slots having a first width;
• a second spring seal overlapping said first spring seal and having a second length and a plurality of second axial slots, with each of said second axial slots having a second width;
• a plurality of raised ridges extending into said annulus downstream said plurality of first feed holes, with each of said raised ridges comprising at least a first surface and a second surface;
• said first and second spring seals axially overlapping a region of said plurality of raised ridges;
• and,
• wherein said first feed holes terminate at said annulus.