SPEED-CONTROLLED CONDITIONING VALVE FOR HIGH PRESSURE COMPRESSOR

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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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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creator KNORTZ, Christopher J
description 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).
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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).</description><language>eng ; fre ; ger</language><subject>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</subject><creationdate>2021</creationdate><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><linktohtml>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&amp;date=20211215&amp;DB=EPODOC&amp;CC=EP&amp;NR=3916204A3$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25563,76418</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&amp;date=20211215&amp;DB=EPODOC&amp;CC=EP&amp;NR=3916204A3$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>KNORTZ, Christopher J</creatorcontrib><title>SPEED-CONTROLLED CONDITIONING VALVE FOR HIGH PRESSURE COMPRESSOR</title><description>A rotor (110) for a gas turbine engine (20) has: a first rotor disk (130A); 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language eng ; fre ; ger
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subjects 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
title SPEED-CONTROLLED CONDITIONING VALVE FOR HIGH PRESSURE COMPRESSOR
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