Stacked ring combustor assembly

A combustor assembly for gas turbine engines comprising:

• a plurality of generally annular members having a common center line, each such member having at one end a first cylindrical portion having a cylindrical inner surface concentric about said center line, a second axially inwardly tapered portion at the other end, and a third step-shaped portion intermediate said first and second portions, each said step-shaped portion having a cylindrical first surface concentric about said center line and a second surface normal to said center line defining said step, said annular members being disposed in nested substantially coaxial relationship spaced axially along said center line with at lest a portion of said first cylindrical portions nested in said third step portions, said inner surfaces of said first portions facing said first surfaces, said first and second portions being disposed in overlapping relationship, said first cylindrical portions having holes therein which in combination with said overlapping first and second portions define airflow passages, said first and third portions defining a substantially smooth outer wall, each said first surface having a machined diameter just slightly less than the inside diameter of each said first cylindrical portion, one of said facing first portion inner surfaces and said first surfaces being upset to define at a plurality of different locations portions of said upset surface in contact with said inner surface;
• and
• brazing material disposed between and bonding said first portion inner surfaces and said first surfaces.