УЗЕЛ КАМЕРЫ СГОРАНИЯ ГАЗОТУРБИННОГО ДВИГАТЕЛЯ (ВАРИАНТЫ) И УЗЕЛ ЖАРОВОЙ ТРУБЫ

摘要

A combustor assembly (14) for a turbine engine includes an aft open end (24) that communicates gas flow to a turbine assembly (18). The combustor assembly (14) includes a liner assembly (15) that terminates at a first fixed vane (18). A portion of the liner assembly extends an axial distance (37) into the first fixed vane portion (18). An inner surface (42) of the liner assembly (15) corresponds with inner surfaces (45) of the fixed vane portion (18) to provide a smooth transition from the inner surfaces (42) of the combustor assembly (14) to the turbine assembly (18).