Gas turbine engine combustor splash ring construction

Abstract

A combustor subassembly for a gas turbine engine, which includes a plurality of modular elements. Each modular element is generally annular and extends from a first axial portion to a second axial portion. The second axial portion is flared inwardly toward the geometric center line of the modular element. The modular elements are disposed in nested, substantially coaxial relationship with successive modular elements spaced axially along a substantially common center line. A plurality of the adjacent modular elements have respective first and second axial portions disposed in overlapping relationship. The overlapping of the modular elements define annular flow passages for directing cooling air into the combustor. Each of a plurality of modular elements include holes therein in the first axial portion at an axial portion thereof which overlaps the second axial portion of another modular element. In addition each of a plurality of the modular elements include holes therein in the second axial portion.

Dependencies are inferred from the claim text.