REGULATED COMBUSTOR LINER PANEL FOR A GAS TURBINE ENGINE COMBUSTOR

REGULATED COMBUSTOR LINER PANEL FOR A GAS TURBINE ENGINE COMBUSTOR

A liner panel (72A, 74B; 74A, 74B) for use in a combustor of a gas turbine engine includes a perimeter rail (120a, 120b) and a multiple of intermediate rails (130a, 130b...130n). A combustor (26) for a gas turbine engine includes a support shell (78, 80) and a multiple of liner panels (72A, 72B; 74A...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser: ZELESKY, Mark F, McKINNEY, Randal G
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 liner panel (72A, 74B; 74A, 74B) for use in a combustor of a gas turbine engine includes a perimeter rail (120a, 120b) and a multiple of intermediate rails (130a, 130b...130n). A combustor (26) for a gas turbine engine includes a support shell (78, 80) and a multiple of liner panels (72A, 72B; 74A, 74B) mounted to the support shell (78, 80) via a multiple of studs (100), each of the multiple of liner panels (72A, 72B; 74A, 74B) having a multiple of intermediate rails (130a, 130b...130n) to form a multiple of circumferential cavities (106a, 106b...106n).