| 摘要 |
A gas turbine auxiliary power unit system (100:200:300:400:500) for an aircraft comprises an aircraft cabin (110) provided with a pressurised air supply (116), a gas turbine engine (120:220:320:420:520) comprising a compressor assembly (122:222:322:422:522), and a controller (130:230:330:430:530). The pressurised air supply (116) is provided to the aircraft cabin (110) through an aircraft cabin air inlet (112), and exhausted from the aircraft cabin (110) through an aircraft cabin air exhaust (114), while the gas turbine engine (120:220:320:420:520) is provided with an inlet air flow (124) from the aircraft cabin air exhaust (114). The controller (130:230:330:430:530) is operable to control a flow rate of a fuel supplied to the gas turbine engine (120:220:320:420:520) responsive to a power demand on the auxiliary power unit (100:200:300:400:500), and also to restrict an inlet air flow into the gas turbine engine (120:220:320:420:520), so as to maintain an air pressure inside the aircraft cabin (110) within a pre-determined range. |
