| 摘要 |
Air (19, 119) captured from the tips (25, 125) of a compressor (10, 110) of a gas turbine engine is diverted from the engine core (22, 122) and can be collected for auxiliary uses. Gas path separation can be achieved using part-span shrouded compressor blades or using blade tip cut-outs (24) conforming to an airflow dividing annular shroud. In a preferred application for the present invention, the gas turbine engine is the auxiliary power unit of an aircraft. |
