| 摘要 |
Disparities between optimum engine thrust for aircraft operation and power necessary to drive an ancillary machine such an electrical power generator can cause problems within a turbine engine. Clearly, it is necessary to continue developing sufficient electrical power for control and other systems within an aircraft despite aircraft thrust requirements. Previously, some compressed air flow has been bypassed in order to maintain compressor stability, but unfortunately such bypass systems within turbine engines can have a thrust recovery regime such that there is excess thrust in comparison with that actually necessary. In accordance with the present invention, a proportion of the compressed air flow is bled directly through a bleed path to an exhaust nozzle 104 of an engine such that the compressor core can continue to provide work to drive an ancillary machine whilst engine thrust is limited to that actually required, achieving a significant saving in terms of fuel consumption and wear and tear upon brakes, etc under low power operation.
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