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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Bibliographische Detailangaben
Hauptverfasser:	STYBORSKI, Jeremy, ANDERSON, Corey D
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	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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Beschreibung
Zusammenfassung:	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.