Methods and apparatus for directing airflow to a compressor bore

A gas turbine engine includes a compressor rotor assembly which directs air at a sufficient pressure and temperature to a compressor rotor bore. The compressor assembly includes a compressor (12, 14) including a plurality of rotors (32) joined with a plurality of couplings (34). Each of the rotors i...

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Bibliographische Detailangaben
Hauptverfasser:	BULMAN, DAVID EDWARD, CLEMENTS, JEFFREY DONALD, BURNS, CRAIG PATRICK, SEITZER, KENNETH EDWARD
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES NON-POSITIVE DISPLACEMENT PUMPS POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS PUMPS FOR LIQUIDS OR ELASTIC FLUIDS STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine engine includes a compressor rotor assembly which directs air at a sufficient pressure and temperature to a compressor rotor bore. The compressor assembly includes a compressor (12, 14) including a plurality of rotors (32) joined with a plurality of couplings (34). Each of the rotors includes a radially outer rim (40), a radially inner hub (42), and a web (44) extending therebetween. The web includes a flange (60) including a plurality of slots (104) which define a plurality of radial vanes (120) that are airfoil-shaped. The vanes effectively de-swirl bleed air (110) and re-direct the airflow to a compressor bore.