| 摘要 |
A gas turbine engine (10) includes an axial compressor which includes a rotor assembly (102) including a first rotor segment (104b) with a first inner rim (112), a first sealing surface (122b), and a first aft engagement feature (116b), and a second rotor segment (104c) positioned aft of the first rotor segment (104b) and having a second inner rim (112), a second sealing surface (120c), and a second inner rim (112) with a second fore engagement feature (114c) that is complementary to the first aft engagement feature (116b). The first and second sealing surfaces (122b, 120c) are complementary to each other, and are bonded together via a transient liquid phase diffusion process. The first and second sealing surfaces (122b, 120c) are disposed on an outer rim (110). The first aft engagement feature (116b) may be a notch that is complementary to the second fore engagement feature (114c), which may be a shelf. |
