INSERT FOR A COLLECTOR OF AN ACTIVE CLEARANCE CONTROL SYSTEM OF AN ENGINE OF AN AIRCRAFT

Aspects of the disclosure are directed to an active clearance control system (300) for an engine of an aircraft, comprising: a collector (318) that is configured to receive a cooling fluid (304), at least two manifolds (312a, b) coupled to the collector (318), where a first of the manifolds (312a) i...

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Bibliographic Details
Main Authors CHRISIKOS, James P, BARKER, Joseph E, GRIFFIN, David R, PHILBRICK, Graham R
Format Patent
LanguageEnglish
French
German
Published 10.05.2023
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
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Summary:Aspects of the disclosure are directed to an active clearance control system (300) for an engine of an aircraft, comprising: a collector (318) that is configured to receive a cooling fluid (304), at least two manifolds (312a, b) coupled to the collector (318), where a first of the manifolds (312a) is configured to receive at least a first portion of the cooling fluid (304) from the collector (318) and a second of the manifolds (312b) is configured to receive at least a second portion of the cooling fluid (304) from the collector (318), and an insert (330) coupled to the collector (318) and the manifolds (312a, b), where the insert (330) is configured to seal an interface between the collector (318) and the at least two manifolds (312a, b) over an operating range of the engine.
Bibliography:Application Number: EP20200186864