| 摘要 |
A combustor assembly (100) for a gas turbine engine is provided. The combustor assembly (100) generally includes an annular dome (116, 118) and a liner (102, 108) . The liner (102, 108) at least partially defines a combustion chamber (114) and includes the forward end (106, 112) received within a slot (121, 123) defined by the annular dome (116, 118). Additionally, a heat shield (142) is provided. The heat shield (142) includes an end (144, 146) also received within the slot (121, 123) defined by the annular dome (116, 118). A mounting assembly (148, 150) attaches the forward end (106, 112) of the liner (102, 108) and the end of the heat shield (142) to the annular dome (116, 118), such that the forward end (106, 112) of the liner (102, 108) and the end (144, 146) of the heat shield (142) are co-mounted within the slot (121, 123) defined by the annular dome (116, 118). |
