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 arrangement in a gas turbine engine to seal a gap between first and second turbine components is provided. The sealing arrangement includes a first arcuate feather seal connected to an anchoring assembly of the sealing arrangement affixed to the first turbine component. A second arcuate feather seal is affixed to the second turbine component. The first arcuate feather seal and the second arcuate feather seal are responsive to a pressure differential that develops across the gap to form a pressure-loaded sealing joint between respective sealing surfaces of the first arcuate feather seal and the second arcuate feather seal. The sealing arrangement provides substantial design flexibility since it can reliably provide appropriate sealing functionality while enabling multiple degrees of freedom, such as to accommodate radial and/or axial displacements that can develop between the first turbine component and the second turbine component.

Abstract: A transition duct support apparatus and a method to support an exit frame in a transition duct in a gas turbine engine are provided. A stiffener (24) may be arranged to provide support to an outer edge (27) of an exit frame (12) in a transition duct (14). Stiffener (24) may be configured to circumferentially extend between mutually opposed corners (30) of the exit frame of the transition duct. A brace (26) may be connected to a centrally-disposed section (20) and may extend to support respective end portions (32) of the stiffener. The support apparatus is effective to provide a respective tuned level of stiffness support with respect to one or more axes of the exit frame in the transition duct. The apparatus and method may be effective for distributing mechanical stresses on the exit frame of the transition duct and/or neighboring regions in the transition duct.

Abstract: A sealing arrangement in a gas turbine engine to seal a gap between first and second turbine components is provided. The sealing arrangement includes a first arcuate feather seal connected to an anchoring assembly of the sealing arrangement affixed to the first turbine component. A second arcuate feather seal is affixed to the second turbine component. The first arcuate feather seal and the second arcuate feather seal are responsive to a pressure differential that develops across the gap to form a pressure-loaded sealing joint between respective sealing surfaces of the first arcuate feather seal and the second arcuate feather seal. The sealing arrangement provides substantial design flexibility since it can reliably provide appropriate sealing functionality while enabling multiple degrees of freedom, such as to accommodate radial and/or axial displacements that can develop between the first turbine component and the second turbine component.

Abstract: A gas turbine engine has an outer ring (15) formed by integrated exit pieces (10) and surrounds an inner ring (16). A seal section (20) having an L-shaped cross-section is connected to and seals the outer ring (15) and the inner ring (16).

Abstract: A transition-to-turbine seal assembly is provided. Seal members (52, 58) may include one or more anchoring tabs (54, 60) affixed only to an associated transition (56) and not to a neighboring transition (57). Thus, seal members (52, 58) may be practically free from high stress levels due to differing motion that can arise between neighboring transitions (56, 57). Additionally, seal members (100, 120) may include articulating segments (106, 108, 126, 128) arranged to provide a respective degree of freedom along a desired direction so that the seal members may be practically free from high stress levels while providing an effective sealing functionality.

Abstract: A transition duct support apparatus and a method to support an exit frame in a transition duct in a gas turbine engine are provided. A stiffener (24) may be arranged to provide support to an outer edge (27) of an exit frame (12) in a transition duct (14). Stiffener (24) may be configured to circumferentially extend between mutually opposed corners (30) of the exit frame of the transition duct. A brace (26) may be connected to a centrally-disposed section (20) and may extend to support respective end portions (32) of the stiffener. The support apparatus is effective to provide a respective tuned level of stiffness support with respect to one or more axes of the exit frame in the transition duct. The apparatus and method may be effective for distributing mechanical stresses on the exit frame of the transition duct and/or neighboring regions in the transition duct.

Abstract: A combustion system for a gas turbine engine including a combustor assembly comprising a combustor basket having a downstream terminal end, and a transition duct extending downstream from the combustor basket and having an upstream end located adjacent to the downstream terminal end of the combustor basket. A coupling is provided comprising an inlet ring adapter including a cylindrical sleeve extending downstream of the upstream end of the transition duct in overlapping relation to an inner surface of the transition duct. A spring clip assembly is mounted to the terminal end of the combustor basket. The spring clip assembly extends into engagement with and forms a seal on the cylindrical sleeve.

Abstract: A combustion system for a gas turbine engine including a combustor assembly comprising a combustor basket having a downstream terminal end, and a transition duct extending downstream from the combustor basket and having an upstream end located adjacent to the downstream terminal end of the combustor basket. A coupling is provided comprising an inlet ring adapter including a cylindrical sleeve extending downstream of the upstream end of the transition duct in overlapping relation to an inner surface of the transition duct. A spring clip assembly is mounted to the terminal end of the combustor basket. The spring clip assembly extends into engagement with and forms a seal on the cylindrical sleeve.

Abstract: A transition-to-turbine seal (320) including an upstream portion (322) adapted to engage a flange (416) of a transition (400). The upstream portion (322) may be U-shaped in cross-sectional profile and include a primary wall (324) that includes a proximal section (325) and a distal section (326) relative to a hot gas path (170). The proximal section (325) includes a plurality of recesses (327) which are spaced apart and separated by intervening wall (328). In each recess (327) is provided one or more outlets (329) of cooling fluid holes (339). The outlets (329) communicate via the cooling fluid holes (339) with a supply of compressed cooling fluid, such as compressed air that is provided from the compressor. During operation the outlets (329) release this fluid into the respective recesses (327). The flow of cooling fluid provides for a more uniform cooling effect that includes impingement and convective cooling.

Abstract: One embodiment of a transition-to-turbine seal (300) comprises a first, flattened section (302) adapted to be received in a peripheral axial slot (320) of a transition (325), and a second, generally C-shaped section (301). The generally C-shaped section (301) comprises a flattened portion (305) near the first, flattened section (302), and a curved portion (306) extending to a free edge (307). A fiber metal strip component (309) may be attached to the flattened portion (305) to define a first engagement surface adapted to engage an upstream side (336) of an outer vane seal rail (337), and a second engagement surface 308, adjacent the free edge (307), provides an opposed wear surface adapted to engage a downstream side (338) of the outer vane seal rail (337). System embodiments also are described, in which such transition-to-turbine seal (300) is isolated from a hot gas path (350) by provision of a plurality of cooling apertures (327) in the transition (325).

Abstract: One embodiment of a transition-to-turbine seal (320) comprises an upstream portion (322) adapted to engage a flange (416) of a transition (400). The upstream portion (322) may be U-shaped in cross-sectional profile and comprises a primary wall (324) that comprises a proximal section (325) and a distal section (326) relative to a hot gas path (170). The proximal section (325) comprises a plurality of recesses (327) which are spaced apart and separated by intervening wall (328). In each recess (327) is provided one or more outlets (329) of cooling fluid holes (339). The outlets (329) communicate via the cooling fluid holes (339) with a supply of compressed cooling fluid, such as compressed air that is provided from the compressor. During operation the outlets (329) release this fluid into the respective recesses (327). The flow of cooling fluid through such outlets (329) in the respective recesses (327) provides for a more uniform cooling effect that includes impingement and convective cooling.

Abstract: One embodiment of a transition-to-turbine seal (300) comprises a first, flattened section (302) adapted to be received in a peripheral axial slot (320) of a transition (325), and a second, generally C-shaped section (301). The generally C-shaped section (301) comprises a flattened portion (305) near the first, flattened section (302), and a curved portion (306) extending to a free edge (307). A fiber metal strip component (309) may be attached to the flattened portion (305) to define a first engagement surface adapted to engage an upstream side (336) of an outer vane seal rail (337), and a second engagement surface 308, adjacent the free edge (307), provides an opposed wear surface adapted to engage a downstream side (338) of the outer vane seal rail (337). System embodiments also are described, in which such transition-to-turbine seal (300) is isolated from a hot gas path (350) by provision of a plurality of cooling apertures (327) in the transition (325).