COMBUSTOR HEAT SHIELD AND METHOD OF COOLING SAME

A combustor (50) for a gas turbine engine includes an annular shell (52; 54), an annular bulkhead (60) connected to the shell (52; 54), and a heat shield panel (74). The heat shield panel (74) has a first surface (76) facing a combustion chamber (56) and a second surface (78) opposite the first surf...

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Bibliographische Detailangaben
Hauptverfasser:	LIENAU, Jeffrey J, SEN, Baris A, ICHIHASHI, Fumitaka, SNYDER, Timothy S
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 combustor (50) for a gas turbine engine includes an annular shell (52; 54), an annular bulkhead (60) connected to the shell (52; 54), and a heat shield panel (74). The heat shield panel (74) has a first surface (76) facing a combustion chamber (56) and a second surface (78) opposite the first surface (76). The heat shield panel (74) is mounted to the bulkhead (60) and defines a cooling chamber (98) between the bulkhead (60) and the heat shield panel (74). The heat shield panel (74) has a wall extending from the heat shield panel (74) toward the bulkhead (60) around at least a portion of a periphery of the heat shield panel (74). The wall includes a circumferential wall portion including at least one cooling air passage (136; 140) extending between the cooling chamber (98) and a cavity (132; 134) defined between the circumferential wall portion and the shell (52; 54). The at least one cooling air passage (136; 140)is configured to purge the cavity (132; 134) by directing a first cooling air stream (138; 142) from the cooling chamber (98) into the cavity (132; 134).