Double flow compressor

Details Double flow compressor Double flow compressor

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 9/02 (2006.01) F01D 25/12 (2006.01) F02C 3/08 (2006.01) F02C 7/12 (2006.01)

Patent

CA 2729130

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. The gas turbine may be, for example, an auxiliary power unit of an aircraft. The compressor includes a radial outflow impeller downstream of the rotor and a stator interposed between the impeller and the rotor.

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