SPEED-CONTROLLED CONDITIONING VALVE FOR HIGH PRESSURE COMPRESSOR

A rotor (110) for a gas turbine engine (20) has: a first rotor disk (130A); an interstage flange (140) that extends from the first rotor disk (130A) to a flange end portion (160) that has an axial end surface (190) and first radial outer and inner surfaces (201A, 201B); a circumferential groove (210...

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Bibliographische Detailangaben
1. Verfasser:	KNORTZ, Christopher J
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 STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	A rotor (110) for a gas turbine engine (20) has: a first rotor disk (130A); an interstage flange (140) that extends from the first rotor disk (130A) to a flange end portion (160) that has an axial end surface (190) and first radial outer and inner surfaces (201A, 201B); a circumferential groove (210A), formed in the flange end portion (160) and extending from the axial end surface (190) toward the first rotor disk (130A); radial outer and inner slots (220A, 220B) formed in the first radial outer and inner surfaces (201A, 201B) along the circumferential groove (210A) and extend through the first radial outer and inner surfaces (201A, 201B) ; and a valve member (240) disposed within the circumferential groove (210A) and is secured within the circumferential groove (210A) when the flange end portion (160) is connected to a second rotor disk (130B), wherein the valve member (240) deflects from rotor rotational speeds to seal or unseal the radial outer slot (220A).