摘要:
The invention relates to a damper arrangement for reducing combustion-chamber pulsations arising inside a gas turbine (1), having a combustion-chamber housing (8) which upstream comprises a front plate (2) with a plurality of individual burners (6) and damping elements (7, 7a, 7b) projecting through the front plate (2) and downstream is connected to a turbine stage (9) and is surrounded by a turbine housing (3) which comprises first openings (5a) which are adapted to the burners (6) and through which the burners (6) project upstream. The invention is characterized in that closable second openings (5b), through which it is possible to insert and tune the damping elements (7, 7a, 7b), are provided inside the turbine housing (9) adjacent to the first openings (5a) adapted to the burners (6).
摘要:
The invention relates to an annular combustor (13) for a gas turbine (10), into which combustor (13) burners (14, 15) open on an inlet side, and which combustor (13) extends in the axial direction from the inlet side to an outlet side (33) and is lined on the insides with cooled liner segments (16, 17) for protection from the hot gases.In such a combustor, increased mechanical stability and flexibility in design and also simplification in manufacture and fitting are achieved by the liner segments (16, 17) being subdivided in the axial direction into a plurality of parts (16, 17) arranged one behind the other.
摘要:
In a burner arrangement for the annular combustion chamber of a gas turbine, a plurality of burners are arranged above one another, in each case in pairs in the radial direction, on concentric rings. In a burner arrangement of this type, the mechanical integrity of the turbine casing is increased and operation of the combustion chamber is optimized by virtue of the two burners in a pair of burners being oriented out of the parallel position, in such a manner that their burner axes converge in the direction of flow.
摘要:
In a gas turbine (10) with a plurality of individual burners (B1, . . . , B6; Bn) which are connected to a fuel distribution system (21) and are supplied with fuel from a common fuel feed (28) via the fuel distribution system (21), there being provided, within the fuel distribution system (21), means by which the fuel mass flows to the individual burners (B1, . . . , B6; Bn) can be varied in order to improve the operating parameters of the gas turbine (10), an improvement in the operating parameters is achieved in a simple way in that a fixed throttle member, determining the fuel mass flow to at least one of the burners (B1, . . . , B6; Bn), is arranged in the fuel distribution system (21) upstream of the at least one burner, and in that the reduction in cross section of the throttle member is selected in such a way that existing inequalities in the fuel distribution system (21) as regards the fuel mass flows to the individual burners (B1, . . . , B6; Bn) are reduced.
摘要:
A combustion chamber of a combustion system has a combustion space, a support structure, a support element, and a heat shield. The heat shield has at least two segments, and each segment includes a liner element facing the combustion space and has an edge region, a gap communicating with the combustion space being formed between edge regions of adjacent segments, and a retaining device. The retaining device fixes the respective liner element on the support structure via the support element and forms a flange region that fits over the edge region of the respective liner element. The retaining device forms a first cooling passage with the support element and has at least one through-opening in the flange region. A cooling gas flows through the through.opening from the first cooling passage to the edge region.
摘要:
At least one Helmholtz damper is arranged at a combustion chamber for a gas turbine in order to damp thermoacoustic oscillations; the damping volume of this Helmholtz damper is in communication with the combustion chamber via a connecting passage. Optimum damping is achieved in a simple way by virtue of the Helmholtz damper being designed in such a manner that its damping frequency is adjustable.
摘要:
In a burner arrangement for the annular combustion chamber of a gas turbine, a plurality of burners are arranged above one another, in each case in pairs in the radial direction, on concentric rings. In a burner arrangement of this type, the mechanical integrity of the turbine casing is increased and operation of the combustion chamber is optimized by virtue of the two burners in a pair of burners being oriented out of the parallel position, in such a manner that their burner axes converge in the direction of flow.
摘要:
A ring segment is provided for a gas turbine engine includes a panel and a cooling system. Cooling fluid is provided to an outer side of the panel and an inner side of the panel defines at least a portion of a hot gas flow path through the engine. The cooling system is located within that panel and receives cooling fluid from the outer side of the panel for cooling the panel. The cooling system includes a plurality of cooling fluid passages that receive cooling fluid from the outer side of the panel. The cooling fluid passages each have a generally axially extending portion that includes at least one fork. The fork(s) divide each cooling fluid passage into at least two downstream portions that each receives cooling fluid from the respective axially extending portion.
摘要:
A combustion chamber of a combustion system comprises a combustion space, a support structure, a heat shield, and at least one through-opening. The heat shield has at least two segments, and each segment has an edge region, a gap communicating with the combustion space being formed between edge regions of adjacent segments, and a retaining device. The adjacent segments include a support element disposed in a bottom region of the gap. The retaining device fixes the respective liner element on the support structure via the respective support element. The at least one through-opening communicates with the gap so as to enable a cooling gas to flow through the through-opening. The at least one through-opening is disposed in at least one of the respective edge region and the support element at the bottom region of the gap.
摘要:
At least one Helmholtz damper is arranged at a combustion chamber for a gas turbine in order to damp thermoacoustic oscillations; the damping volume of this Helmholtz damper is in communication with the combustion chamber via a connecting passage. Optimum damping is achieved in a simple way by virtue of the Helmholtz damper being designed in such a manner that its damping frequency is adjustable.