COMBUSTOR TRANSITION

The disclosure relates combustor transition (24) adapted to guide combustion gases in a hot gas flow path (15) extending between a can combustor (2) and a first stage of turbine (3) in a gas turbine (9). The combustor transition (24) comprises a duct having an upstream end adapted for connection to...

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Bibliographische Detailangaben
Hauptverfasser:	DUSING, MICHAEL, BOTHIEN, MIRKO RUBEN
Format:	Patent
Sprache:	eng ; fre
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:	The disclosure relates combustor transition (24) adapted to guide combustion gases in a hot gas flow path (15) extending between a can combustor (2) and a first stage of turbine (3) in a gas turbine (9). The combustor transition (24) comprises a duct having an upstream end adapted for connection to the can combustor (2) and an downstream end adapted for connection to a first stage of a turbine (3), wherein the downstream end comprises an outer wall (11), an inner wall (12), a first and a second side wall (21a, 21b). The combustor transition is, characterized in that at least one side wall (21a, 21b) has a side wall extension (20, 20a, 20b), which is extending in a downstream direction beyond the outlet (22). Besides the combustor transition (24) a gas turbine comprising such a combustor transition (24), a method for retrofitting a gas turbine (9) with such a combustor transition (24) as well as a method for borescope inspection of a GT with such a combustor transition are disclosed.