Patent application number | Description | Published |
20100229570 | BURNER FOR A GAS TURBINE AND METHOD FOR LOCALLY COOLING A HOT GASES FLOW PASSING THROUGH A BURNER - The burner ( | 09-16-2010 |
20100236246 | BURNER OF A GAS TURBINE - An exemplary burner of a gas turbine includes a tubular body with an inlet for an entrance of an air flow, downstream of inlet vortex generators, and a lance projecting into the tubular body and having a terminal portion extending along a longitudinal axis of the burner which is provided with nozzle groups for injecting fuel into the tubular body. The nozzle groups can lay in an injection plane perpendicular to the axis of the terminal portion of the lance. Downstream of the lance, the burner has an outlet. A ratio x/L between an axial distance x between the side trailing edge of the vortex generator and the injection plane, and the length L of the tubular body can be less than approximately 0.1052. | 09-23-2010 |
20140026586 | REHEAT BURNER AND METHOD OF MIXING FUEL/CARRIER AIR FLOW WITHIN A REHEAT BURNER - The invention refers to a reheat burner that includes a flow channel for a hot gas flow with a lance arranged along said flow channel, protruding into the flow channel for injecting a fuel over an injection plane perpendicular to a channel longitudinal axis, wherein the channel and lance define a vortex generation zone upstream of the injection plane and a mixing zone downstream of the injection plane in the hot gas flow direction. The mixing zone provides at least one axially region having different cross sectional areas along its longitudinal axis with continuously changing shape, or having non circular cross section areas which change location along its longitudinal axis by continuously rotation around the longitudinal axis. | 01-30-2014 |
20140109579 | COMBUSTOR TRANSITION - The disclosure relates 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 an 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. The combustor transition is, characterized in that at least one side wall has a side wall extension, which is extending in a downstream direction beyond the outlet. Besides the combustor transition a gas turbine includes 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. | 04-24-2014 |
20150101341 | METHOD FOR A PART LOAD CO REDUCTION OPERATION FOR A SEQUENTIAL GAS TURBINE - The invention concerns a method for a part load CO reduction operation and a low-CO emissions operation of a gas turbine with sequential combustion. The gas turbine essentially includes at least one compressor, a first combustor which is connected downstream to the compressor. The hot gases of the first combustor are admitted at least to an intermediate turbine or directly or indirectly to a second combustor. The hot gases of the second combustor are admitted to a further turbine or directly or indirectly to an energy recovery. At least one combustor runs under a caloric combustion path having a can-architecture, and wherein the air ratio (λ) of the combustion at least of the second combustor is kept below a maximum air ratio (λ | 04-16-2015 |