| 摘要 |
A gas turbine engine (20) includes a fan section (22), a compressor section (24) aft of the fan section (22), a combustor (36) fluidly connected to the compressor section (24) and a turbine section (28) fluidly connected to the combustor (56). The turbine section (28) includes at least a first turbine (46) and a second turbine (54) that operates at a higher pressure than the first turbine (46). A shaft (150) is connected to the first turbine section (142) such that the first turbine section (142) is operable to drive rotation of the shaft (150). The shaft (150) is a rotational input for a split gear (160) that is connected to the fan (22) and at least one of a multiple of compressors (122). |
