초록 ▼

A gas turbine includes an annular combustion chamber and an outer wall of an annular combustion chamber. A straining ring is arranged on the outer wall of the annular combustion chamber and enables oscillations of the outer wall to be damped via friction. The effects of combustion oscillations produ

A gas turbine includes an annular combustion chamber and an outer wall of an annular combustion chamber. A straining ring is arranged on the outer wall of the annular combustion chamber and enables oscillations of the outer wall to be damped via friction. The effects of combustion oscillations produced by damaging vibrations of the annular combustion chamber are thus reduced. A method is further for damping an oscillation of an outer wall of an annular combustion chamber.

대표청구항 ▼

What is claimed is: 1. A gas turbine, comprising: a compressor; an annular combustion chamber; and a turbine part, wherein the annular combustion chamber includes an outer wall with an outer surface, wherein the annular combustion chamber is surrounded on its outer surface by a tension ring th

What is claimed is: 1. A gas turbine, comprising: a compressor; an annular combustion chamber; and a turbine part, wherein the annular combustion chamber includes an outer wall with an outer surface, wherein the annular combustion chamber is surrounded on its outer surface by a tension ring that has no external supporting points, and wherein the tension ring includes a tension device that places a pretension on the tension ring to achieve a friction between the tension ring and the annular combustion chamber suitable for dissipating oscillation energy. 2. The gas turbine as claimed in claim 1, wherein the outer surface includes a cylindrical contact face, on which the tension ring is present. 3. The gas turbine as claimed in claim 2, wherein the cylindrical contact face is formed by a rib running in the circumferential direction. 4. The gas turbine as claimed in claim 3, wherein the tension ring includes a recess that lies on the rib. 5. The gas turbine as claimed in claim 1, wherein the tension ring is constructed from at least two tension ring segments along its circumferential direction. 6. The gas turbine as claimed in claim 5, wherein the tension ring segments are connected via the tension device. 7. The gas turbine as claimed in claim 6, wherein the tension device includes a pull rod, adapted to engage into a pull lug, and wherein a pretensioning force is set between the pull rod and the pull lug via a spring. 8. The gas turbine as claimed in claim 7, wherein the pull lug is arranged displaceably in long holes. 9. A method for the damping of oscillations of an annular combustion chamber of a gas turbine, comprising: providing a tension ring around an outer circumference of the annular combustion chamber, the tension ring having no external supporting points; and dissipating oscillation energy of the annular combustion chamber via friction between the tension ring and the annular combustion chamber by setting a tension force on the tension ring. 10. The method as claimed in claim 9, wherein the tension force is set so as to be tuned to a prevailing oscillation frequency. 11. An apparatus for the damping of oscillations of an annular combustion chamber of a gas turbine, comprising: a tension ring running around an outer circumference of the annular combustion chamber; wherein the tension ring has no external supporting points; and wherein the tension ring includes means for setting a tension force of the tension ring to achieve a dissipation of oscillation energy of the annular combustion chamber. 12. The apparatus as claimed in claim 11, wherein the tension force is set so as to be tuned to a prevailing oscillation frequency.