Abstract: A lance of a gas turbine burner includes an inner duct having inner nozzles; an annular outer duct encircling the inner duct and having outer nozzles; and a spacer disposed between a terminal portion of the inner duct and a terminal portion of the outer duct, the spacer being fixed to both the inner duct and the outer duct.

Abstract: A seal for stemming leakage flows between adjacent components, especially of a gas turbine, has an elastically deformable, thin-walled sealing element and a thin-walled cover element which is U-shaped in cross section and between its legs and its base partially accommodates the sealing element. The legs of the cover element are arranged in the sealing arrangement, which features the seal, between two oppositely disposed walls of the other component in a movable manner relative to these walls which, together with the sealing surface of the other component, form a groove which is U-shaped in cross section. Forces, which act laterally upon the seal, are absorbed by the cover element and via the legs are diverted into the other component so that the integrity of the seal is maintained even in the case of lateral forces.

Abstract: A turbomachine with at least one combustion chamber and at least one turbine which lies downstream of it. The turbine has at least one support element and a lining element connected to the support element and formed as a heat shield. A gap sealed by means of a seal, is formed between the at least one combustion chamber and the turbine, an exchangeable insert is arranged in the gap on the end face on the support element and protects at least the support element against hot gases which penetrate into the gap, and against oxidation which is associated with it.

Abstract: A lance of a gas turbine burner includes an inner duct having inner nozzles; an annular outer duct encircling the inner duct and having outer nozzles; and a spacer disposed between a terminal portion of the inner duct and a terminal portion of the outer duct, the spacer being fixed to both the inner duct and the outer duct.

Abstract: A seal for stemming leakage flows between adjacent components (9, 20), especially of a gas turbine, has an elastically deformable, thin-walled sealing element (1) and a thin-walled cover element (13) which is U-shaped in cross section and between its legs (15) and its base (14) partially accommodates the sealing element (1). The legs (15) of the cover element (13) are arranged in the sealing arrangement, which features the seal, between two oppositely disposed walls (28) of the other component (9) in a movable manner relative to these walls (28) which, together with the sealing surface (8) of the other component (9), form a groove (27) which is U-shaped in cross section. Forces, which act laterally upon the seal, are absorbed by the cover element (13) and via the legs (15) are diverted into the other component (9) so that the integrity of the seal is maintained even in the case of lateral forces.

Abstract: A turbomachine with at least one combustion chamber and at least one turbine which lies downstream of it. The turbine has at least one support element and a lining element connected to the support element and formed as a heat shield. A gap sealed by means of a seal, is formed between the at least one combustion chamber and the turbine, an exchangeable insert is arranged in the gap on the end face on the support element and protects at least the support element against hot gases which penetrate into the gap, and against oxidation which is associated with it.

Abstract: A burner for a combustor of a turbogroup is provided. The burner includes a burner body, an outlet flange, and a plenum which is exposed, or can be exposed, to admission of cooling medium. In order to improve the cooling of the outlet flange, a flow passage and a supply passage are formed. The flow passage and the supply passage are arranged so that the cooling medium from the plenum enters the flow passage, is transferred from the flow passage into the supply passage, and is discharged from the supply passage through holes into a burner interior.