DESIGN AND MANUFACTURING PROCESS FOR DIRECTED IMPINGEMENT PUNCHED PLATES

A gas turbine engine component assembly including: a first component (400) having a first surface (410) and a second surface (420) opposite the first surface; and a second component (600) having a first surface (610), a second surface (620) opposite the first surface of the second component, and an...

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Bibliographic Details
Main Authors STYBORSKI, Jeremy, ANDERSON, Corey D
Format Patent
LanguageEnglish
French
German
Published 29.06.2022
Subjects
BLASTING
COMBUSTION APPARATUS
COMBUSTION PROCESSES
GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
HEATING
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
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Summary:A gas turbine engine component assembly including: a first component (400) having a first surface (410) and a second surface (420) opposite the first surface; and a second component (600) having a first surface (610), a second surface (620) opposite the first surface of the second component, and an impingement slot (500) extending from the second surface of the second component to the first surface of the second component, the second surface of the first component and the first surface of the second component defining a cooling channel (390) therebetween in fluid communication with the impingement slot, wherein the impingement slot is in fluid communication with the second surface of the first component, wherein the impingement slot includes a slot tab (502) configured to direct airflow into the cooling channel at least partially in a lateral direction (XI) parallel to the second surface of the first component such that a cross flow (590a) is generated in the cooling channel.
Bibliography:Application Number: EP20190177548