INTERCOOLED TANGENTIAL AIR INJECTOR FOR GAS TURBINE ENGINES

A thermal management system (230) for a component of a gas turbine engine (20) is disclosed. In various embodiments, the thermal management system (230) includes a manifold (238) extending circumferentially about a longitudinal axis (A) and defining a plenum (240); a cooling fluid transfer tube (236...

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Bibliographic Details
Main Author DIBENEDETTO, Enzo
Format Patent
LanguageEnglish
French
German
Published 07.07.2021
Subjects
AIR INTAKES FOR JET-PROPULSION PLANTS
BLASTING
COMBUSTION ENGINES
CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
ENGINE PLANTS IN GENERAL
GAS-TURBINE PLANTS
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
WEAPONS
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Summary:A thermal management system (230) for a component of a gas turbine engine (20) is disclosed. In various embodiments, the thermal management system (230) includes a manifold (238) extending circumferentially about a longitudinal axis (A) and defining a plenum (240); a cooling fluid transfer tube (236) disposed within the plenum (240) and configured to transfer a component cooling fluid from a component cooling fluid source to the component; and a cooling fluid passageway (244) connected to the manifold (238) and configured to transfer a plenum cooling fluid from a plenum cooling fluid source to the plenum (240).
Bibliography:Application Number: EP20190204521