Combustor transition

A combustor transition can be adapted to guide combustion gases in a hot gas flow path extending between a combustor and a first stage of a turbine in a gas turbine. The combustor transition includes a duct having an upstream end adapted for connection to the combustor and a downstream end adapted f...

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Bibliographische Detailangaben
Hauptverfasser:	Düsing Michael, Bothien Mirko Ruben
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 ENGINE PLANTS IN GENERAL 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 MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	A combustor transition can be adapted to guide combustion gases in a hot gas flow path extending between a combustor and a first stage of a turbine in a gas turbine. The combustor transition includes a duct having an upstream end adapted for connection to the combustor and a downstream end adapted for connection to a first stage of the turbine. The downstream end comprises an outer wall, an inner wall, a first side wall and a second side wall. At least one side wall has a side wall extension, which can extend in a downstream direction beyond the outlet. A gas turbine can be retrofitted with such a combustor transition and a gas turbine with such a combustor transition can also undergo a borescope inspection.