| 摘要 |
A gas turbine engine assembly 10 comprises a compressor having a first compressor rotor 22 and second compressor rotor 24 disposed downstream of the first, a turbine coupled to said compressor by a shaft (20, fig.1), an air directing assembly 100 coupled between first and second compressor rotors for selectively channelling airflow discharged from the first compressor rotor inwards through the shaft. Preferably the air flows through a gap 25 between the compressor rotors, then through the duct 30 in the shaft, bypassing the combustor and turbine. The flow may provide thrust and/or cooling. The air directing assembly preferably has a pair of rings 102, 104 with adjustable blades 106 (cross-section shown in hatched lines) extending between said rings. The internal bypass air duct 30 may comprise a butterfly valve for controlling the flow. Preferably the compressor is a high-pressure compressor while the turbine is a high-pressure turbine. |
