COMBUSTION SYSTEM AND METHOD OF ASSEMBLING THE SAME

PROBLEM TO BE SOLVED: To provide a combustion system for a gas turbine engine.SOLUTION: The combustion system includes: an inner casing structure 124; an outer casing structure 122; and a combustion chamber frame 200 mounted between the inner casing structure 124 and the outer casing structure 122 s...

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Bibliographische Detailangaben
Hauptverfasser:	GARDNER DONALD LEE, THOMPSON JAMES EDWARD, PATTERSON DAVID BRUCE, WIEHE GLENN EDWARD, YOUNG CRAIG DOUGLAS, BROWN DANIEL DALE, CORSMEIER DONALD MICHAEL
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION APPARATUS COMBUSTION ENGINES COMBUSTION PROCESSES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	PROBLEM TO BE SOLVED: To provide a combustion system for a gas turbine engine.SOLUTION: The combustion system includes: an inner casing structure 124; an outer casing structure 122; and a combustion chamber frame 200 mounted between the inner casing structure 124 and the outer casing structure 122 so that the combustion chamber frame is coupled to the inner casing structure and the outer casing structure. The combustion system further include an inner liner 134 and an outer liner 136 so as to be configured so that the inner and outer liners are coupled to the combustion chamber frame 200 to constitute a boundary in a radial direction of a combustion chamber 302 and the combustion chamber frame 200 constitutes a forward boundary of the combustion chamber 302.