| 摘要 |
The disclosure concerns a gas turbine engine (52) comprising a compressor (54), a turbine (56) having one or more stages and a combustor, the combustor being located between the compressor and turbine. The gas turbine engine further comprises a bleed (62) from a core (50) defined by a core duct, the core duct surrounding and extending between the turbine and combustor at least. The bleed comprises at least one inlet located downstream of the combustor and upstream of at least one of the turbine stages. The turbine is arranged in use to drive the compressor. The bleed is arranged to be controllable in use to selectively bleed air from the core through the inlet and to thereby control the power delivered by the turbine to the compressor. |
