| 摘要 |
A gas turbine engine (20) includes a compressor section (24), a combustor (26) fluidly connected to the compressor section (28), and a turbine section fluidly connected to the combustor (21) and mechanically connected to the compressor section (24) via a shaft (240). Multiple rotors are disposed in one of the compressor section and the turbine section. Each of the rotors includes a rotor disk portion having a radially inward bore (216, 226), and is static relative to the shaft (240). Each rotor is axially adjacent at least one other rotor and a gap (270) is defined between each rotor and an adjacent rotor. A cooling passage (250) for a cooling flow is defined between the shaft (240) and the rotors, and a cooling flow redirection component (290) is disposed at the gap (270) and is operable to redirect the cooling flow in the cooling passage into the gap (270). |
