Abstract: A sealing system is described for effecting a seal of a gap (G1; G2) in a turbomachine (1) between a first structural member (21; 23) and a second structural member (31). The sealing system includes a sealing apparatus comprising a sealing member (47; 77) comprising a first edge portion (49; 79) and a second edge portion (51; 81). The two edge portions are parallel to one another and the first edge portion (49; 79) forms a pivoting connection to the first structural member (21; 23). The first structural member (21; 23) further comprises a seat (55; 85) rotatably housing the first edge portion (49; 79) of the sealing member (47; 77). The second edge portion (51; 81) comprises a curved contact surface (51.1; 81.1), in sealing contact with a contact surface (67; 97) of the second structural member (31).

Abstract: A fuel nozzle comprising a stem and a first fuel feed channel extending inside the stem from an inlet end positioned at a proximal end of the stem to a first fuel inlet plenum. The fuel nozzle further comprises a first set of fuel injectors fluidly coupled to the first fuel inlet plenum. The fuel nozzle further includes a second fuel feed channel extending inside the stem from an inlet end, positioned at the proximal end of the stem, to a second fuel inlet plenum. A second set of fuel injectors are fluidly coupled to the second fuel inlet plenum. Each fuel injector comprises a centerbody and an outer sleeve surrounding the centerbody and extending along the axis of the centerbody. An annular premix chamber is provided between each outer sleeve and the respective centerbody.

Abstract: The gas compression system for a gas pipeline includes a reciprocating compressor arranged to compress the gas and a gas turbine engine arranged to drive the reciprocating compressor. The gas turbine engine has a turbine section with a high-pressure section and a low-pressure section, wherein only the low-pressure section is mechanically coupled through a mechanical connection to a reciprocating compressor arranged to compress the gas transported by the gas pipeline. The mechanical connection comprises a gearbox, an elastomeric coupling and a flywheel. The gas compression system is particularly suitable as a gas pipeline compression station using the gas transported by the gas pipeline as fuel. Advantageously, the gas turbine engine can reduce NOx formation during combustion by injecting diluent in the combustor, the diluent being advantageously demineralized water recovered from the inlet air of the gas turbine engine.

Abstract: A fuel injector comprises a fuel infeed chamber and a centerbody extending along a longitudinal axis from the fuel infeed chamber to a distal end of the centerbody. An outer sleeve surrounds the centerbody and forms an annular premix chamber between the outer sleeve and the centerbody. The centerbody comprises a distal tip projecting outside the annular premix chamber, beyond the distal end of the outer sleeve.

Abstract: A sealing system is described for effecting a seal of a gap (G1; G2) in a turbomachine (1) between a first structural member (21; 23) and a second structural member (31). The sealing system includes a sealing apparatus comprising a sealing member (47; 77) comprising a first edge portion (49; 79) and a second edge portion (51; 81). The two edge portions are parallel to one another and the first edge portion (49; 79) forms a pivoting connection to the first structural member (21; 23). The first structural member (21; 23) further comprises a seat (55; 85) rotatably housing the first edge portion (49; 79) of the sealing member (47; 77). The second edge portion (51; 81) comprises a curved contact surface (51.1; 81.1), in sealing contact with a contact surface (67; 97) of the second structural member (31).

Abstract: A gas turbine combustor is disclosed, comprising: a combustor liner; a combustor casing, at least partly housing the combustor liner, and a liner support arrangement. The liner support arrangement comprises individual support elements located between the combustor liner and the combustor casing. Each support element comprises a liner support member fixed to the combustor liner and a casing support member fastened to the combustor casing. Each casing support member comprises a casing stop seat fixed on the combustor casing and a replaceable casing stop, detachably coupled to the casing stop seat.

Abstract: A gas turbine combustor is disclosed, comprising: a combustor liner; a combustor casing, at least partly housing the combustor liner, and a liner support arrangement. The liner support arrangement comprises individual support elements located between the combustor liner and the combustor casing. Each support element comprises a liner support member fixed to the combustor liner and a casing support member fastened to the combustor casing. Each casing support member comprises a casing stop seat fixed on the combustor casing and a replaceable casing stop, detachably coupled to the casing stop seat.