BELLOWS-ENABLED BLEED VALVE

A bleed valve for use in a gas turbine engine of an aircraft includes a high-pressure cavity coupled to a valve housing, which includes a valve seat configured to be sealed by a system poppet. The system poppet is operably coupled to a shaft that is itself coupled to a movable end of a bellows, whic...

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Bibliographic Details
Main Author ROMANO, Christopher M
Format Patent
LanguageEnglish
French
German
Published 08.04.2020
Subjects
ACTUATING-FLOATS
AIR INTAKES FOR JET-PROPULSION PLANTS
BLASTING
COCKS
COMBUSTION ENGINES
CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
DEVICES FOR VENTING OR AERATING
ENGINE PLANTS IN GENERAL
ENGINEERING ELEMENTS AND UNITS
GAS-TURBINE PLANTS
GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
LIGHTING
MACHINES OR ENGINES IN GENERAL
MECHANICAL ENGINEERING
NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES
STEAM ENGINES
TAPS
THERMAL INSULATION IN GENERAL
VALVES
WEAPONS
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Summary:A bleed valve for use in a gas turbine engine of an aircraft includes a high-pressure cavity coupled to a valve housing, which includes a valve seat configured to be sealed by a system poppet. The system poppet is operably coupled to a shaft that is itself coupled to a movable end of a bellows, which is positioned within the high-pressure cavity. The opening and closing of the valve is controlled by at least one cavity air port that is configured to inject a first fluid into the high-pressure cavity, thus compressing the bellows, and by a servo air port that is configured to inject a second fluid directly into the bellows, to expand it.
Bibliography:Application Number: EP20190200478