Abstract: A seal for sealing a gap in a combustion apparatus of a gas turbine between a first side and an opposite second side. The seal includes a steel strap with a flat shape and a first metal web with a flat shape attached to the steel strap on the first side and a second metal web attached to the steel strap on the second side. Thereby the seal has a seal thickness with at least the steel strap plus the first metal web plus the thickness of the second metal web, wherein the seal thickness is at most 0.2-times of width of the seal. The new seal has an Omega shape of the second metal web, which is therefore attached on both sides with a flat shaped portion to the steel strap.

Abstract: A seal for sealing a gap in a combustion apparatus of a gas turbine between a first side and an opposite second side. The seal includes a steel strap with a flat shape and a first metal web with a flat shape attached to the steel strap on the first side and a second metal web attached to the steel strap on the second side. Thereby the seal has a seal thickness with at least the steel strap plus the first metal web plus the thickness of the second metal web, wherein the seal thickness is at most 0.2-times of width of the seal. The new seal has an Omega shape of the second metal web, which is therefore attached on both sides with a flat shaped portion to the steel strap.

Abstract: A sealing assembly positioned between a first component having a first interface and a second component having a second interface is provided. The sealing assembly includes a flat bracket fixedly attached to the first interface to define an extension and a floating seal including a body portion, a first U-shaped channel arranged to engage the extension, and a second U-shaped channel inhibiting movement of the floating seal in an axial direction while allowing movement in a radial direction, and the second U-shaped channel allowing movement in the axial direction and inhibiting movement in the radial direction.

Abstract: A sealing assembly positioned between a first component having a first interface and a second component having a second interface is provided. The sealing assembly includes a flat bracket fixedly attached to the first interface to define an extension and a floating seal including a body portion, a first U-shaped channel arranged to engage the extension, and a second U-shaped channel inhibiting movement of the floating seal in an axial direction while allowing movement in a radial direction, and the second U-shaped channel allowing movement in the axial direction and inhibiting movement in the radial direction.

Abstract: A system effective for dual utilization of cooling fluid in a gas turbine engine is provided. A cooling annulus is subject to a hot-temperature combustion flow received from a combustor basket and includes a liner including a feed channel to receive cooling fluid. A feed manifold is in fluid communication with feed channel to feed cooling fluid to a plurality of conduits in fluid communication with a plurality of exit orifices that is in fluid communication with a plurality of resonators. A distributor manifold includes a plurality of manifold sectors in fluid communication with a plurality of conduits arranged to convey cooling fluid. Some of the plurality of resonators operates with different amounts of cooling fluid. A group of the plurality of exit orifices is configured to supply an amount of cooling fluid appropriate for a resonator in fluid communication with the group of the plurality of exit orifices.

Abstract: A gas turbine engine has a resonator ring that is formed by two circumferentially extending rings. The first and second circumferentially extending rings have located within them baffles. Both the first ring and the second ring are able to mitigate acoustic frequencies generated by the gas turbine engine.

Abstract: A gas turbine engine has a resonator ring that is formed by two circumferentially extending rings. The first and second circumferentially extending rings have located within them baffles. Both the first ring and the second ring are able to mitigate acoustic frequencies generated by the gas turbine engine.

Abstract: A system effective for dual utilization of cooling fluid in a gas turbine engine is provided. A cooling annulus is subject to a hot-temperature combustion flow received from a combustor basket and includes a liner including a feed channel to receive cooling fluid. A feed manifold is in fluid communication with feed channel to feed cooling fluid to a plurality of conduits in fluid communication with a plurality of exit orifices that is in fluid communication with a plurality of resonators. A distributor manifold includes a plurality of manifold sectors in fluid communication with a plurality of conduits arranged to convey cooling fluid. Some of the plurality of resonators operates with different amounts of cooling fluid. A group of the plurality of exit orifices is configured to supply an amount of cooling fluid appropriate for a resonator in fluid communication with the group of the plurality of exit orifices.