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US 2014/0109578 A1Published application
Combustor transition
AssigneeALSTOM Technology Ltd
InventorsMirko Ruben BOTHIEN, Michael Düsing
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AssigneeALSTOM Technology Ltd
InventorsMirko Ruben BOTHIEN, Michael Düsing
Estimating the term…
The disclosure relates to a combustor transition adapted to guide combustion gases in a hot gas flow path extending between a can combustor and a first stage of turbine in a gas turbine. The combustor transition includes a duct having an upstream end adapted for connection to the can combustor and a downstream end adapted for connection to a first stage of a turbine, wherein the downstream end comprises an outer wall, an inner wall, a first and a second side wall. At least one side wall has a side wall extension, which extends in a downstream direction beyond the outlet. The side wall extension at least partly encloses a first resonator volume and at least one side wall extension includes a resonator hole, which is configured as a neck of a Helmholtz-damper. Besides the combustor transition a gas turbine comprising such a combustor transition, a method for retrofitting a gas turbine with such a combustor transition as well as a method for borescope inspection of a GT with such a combustor transition are disclosed.
A combustor transition adapted to guide combustion gases in a hot gas flow path extending between a gas turbine combustion chamber and a first stage of turbine, the combustor transition comprising a duct having an inlet at an upstream end adapted for connection to the combustion chamber and an outlet at a downstream end adapted for connection to a first stage of a turbine, wherein the downstream end comprises an outer wall, an inner wall, a first side wall and a second side wall,
Dependencies are inferred from the claim text.