Abstract:
A system comprising a fuel nozzle. The fuel nozzle includes a mounting base and an inlet flow conditioner extending directly from the mounting base in a downstream direction. Moreover, the inlet flow conditioner structurally supports the fuel nozzle without a central support member extending directly from the mounting base inside the inlet flow conditioner.
Abstract:
An impingement shield assembly for a turbine includes a first impingement shield portion and a second impingement shield joined to the first impingement shield portion. The assembly also includes a first connection portion formed on the first impingement shield portion, a second connection portion formed on the first impingement shield portion and first and second wedge weld portions that mate with and hold the first and a second connection portions in a fixed relationship to one another.
Abstract:
Optical flame holding and flashback detection systems and methods are provided. Exemplary embodiments include a combustor including a combustor housing defining a combustion chamber having combustion zones, flame detectors disposed on the combustor housing and in optical communication with the combustion chamber, wherein each of the flame detectors is configured to detect an optical property related to one or more of the combustion zones.
Abstract:
In one embodiment, a turbine system, may include a fuel nozzle, that includes a plurality of fuel passages and a plurality of air passages offset in a downstream direction from the fuel passages. In the embodiment, an air flow from the air passages is configured to intersect with a fuel flow from the fuel passages at an angle to induce swirl and mixing of the air flow and the fuel flow downstream of the fuel nozzle.
Abstract:
Disclosed is a combustor including a baffle plate having at least one through baffle hole and at least one fuel nozzle extending through the at least one through baffle hole. At least one diluent shroud is affixed to the at least one baffle plate and is configured to guide a diluent flow toward a mixing chamber of the at least one fuel nozzle. Further disclosed is a method for introducing a diluent flow into a mixing chamber of a fuel nozzle including urging the diluent flow from a plenum through a baffle plate gap between a baffle plate and an outer surface of the fuel nozzle. The diluent flow is directed via at least one diluent shroud extending from the baffle plate toward a plurality of air swirler holes extending through a fuel nozzle tip. The diluent flow is flowed through the plurality of air swirler holes into the mixing chamber.
Abstract:
Disclosed is a combustor including a baffle plate having at least one through baffle hole and at least one fuel nozzle extending through the at least one baffle hole. A circumferentially adjustable collar is located at the at least one baffle hole between the baffle plate and the at least one fuel nozzle. A plurality of openings at the collar are configured to meter a flow of diluent between the baffle hole and the at least one fuel nozzle. Further disclosed is a method for providing diluent to a combustor including providing a plurality of openings disposed at a circumferentially adjustable collar between a baffle plate and at least one fuel nozzle extending through a through hole in the baffle plate. The diluent is flowed through the plurality of openings toward at least one airflow hole in the at least one fuel nozzle.