A turbine airfoil includes a body including a wall defining pressure and suction sides, and a leading edge extending between the pressure and suction sides. A cooling circuit inside the wall of the body includes at least one of: a) a suction side to pressure side cooling sub-circuit including a first cooling passage(s) extending from the suction side to the pressure side around the leading edge to a first plenum, and a plurality of first film cooling holes communicating with the first plenum and extending through the wall on the pressure side; and b) a pressure side to suction side cooling sub-circuit including second cooling passage(s) extending from the pressure side to the suction side around the leading edge to a second plenum, and a plurality of second film cooling holes communicating with the second plenum and extending through the wall on the suction side.

A vibration damping system for a turbine nozzle or blade includes a vibration damping element including a plurality of contacting members including a plurality of damper pins. Each damper pin includes a body. A wire mesh member surrounds the body of at least one of the plurality of damper pins. The wire mesh member has a first outer dimension sized for frictionally engaging within a body opening in the turbine nozzle or blade to damp vibration. Spacer members devoid of a wire mesh member may also be used. The damper pins can have different sizes to accommodate contiguous body openings of different sizes in the nozzle or blade. The body opening can be angled relative to a radial extent of the nozzle or blade.

A turbine assembly for use with a gas turbine engine includes a bladed wheel assembly and a vane assembly. The bladed wheel assembly is adapted to interact with gases flowing through a gas path of the gas turbine engine. The vane assembly is located upstream of the bladed wheel assembly and adapted to direct the gases at the bladed wheel assembly.

A turbine assembly for use with a gas turbine engine includes a bladed wheel assembly and a vane assembly. The bladed wheel assembly is adapted to interact with gases flowing through a gas path of the gas turbine engine. The vane assembly is located upstream of the bladed wheel assembly and adapted to direct the gases at the bladed wheel assembly.

A vane arc segment includes an airfoil piece that defines first and second platforms and a airfoil section that extends between the first and second platforms. The airfoil section has a trailing edge, a leading edge, a pressure side, and a suction side. The platforms each define first and second circumferential mate faces, forward and aft sides, a gaspath side, a non-gaspath side, and a radial flange that projects from the non-gaspath side. Each radial flange extends continuously and includes a first leg portion that extends adjacent the trailing edge, a second leg portion that extends from the first leg portion and curves around the suction side, and a third leg portion that extends from the second leg portion toward the forward side.

A combustor inlet mixing system (10) formed from a plurality of circumferentially spaced swirler vanes (38) extending radially outward from a nozzle hub. Each of the swirler vanes (38) may have a length (62) that extends downstream along at least a portion of the combustor inlet mixing system (10), and may further have a thickness (66) that extends along a circumference of the nozzle hub. At least one of the swirler vanes (38) may further have at least one slot (42) cut entirely through the thickness (66) of a portion of the swirler vane (38). The slot (42) may separate the swirler vane (38) from the nozzle hub along a portion of the length (62) of the swirler vane (38).

A stator vane arrangement for a turbomachine comprises a radially inner annular structure, a radially outer annular structure and a plurality of circumferentially spaced vanes extending radially between the inner annular structure and the outer annular structure. At least one of the vanes has a passage extending from the inner annular structure to the outer annular structure. The inner annular structure has at least one radially inwardly extending boss and each boss has a passage extending there-through. The passage in each boss is aligned with a corresponding passage in a vane. Each boss comprises a first portion having a first cross-sectional area and a second portion having a second cross-sectional area which is greater than the first cross-sectional area. The first portion of each boss is positioned between and interconnecting the second portion of the boss and the inner annular structure.

The invention relates to a turbine wheel (34) comprising a plurality of vanes connected to an annular platform (24) carrying annular lips (36, 38). According to the invention, one of the upstream lip (38) and the downstream lip (36) is of a first type or of a second type, with the first type corresponding to one lip (36) having the upstream face (36a) which is concave curved and the downstream face (36b) which is convex curved and the second type corresponding to a lip (38) having the upstream (38a) and downstream (38b) faces which are substantially flat and mutually parallel.

To provide a fuel nozzle for a gas turbine combustor, offering favorable durability and strength reliability. In a fuel nozzle for a gas turbine combustor, jetting fuel into a combustion chamber of the gas turbine combustor, the fuel nozzle is metallurgically and integrally bonded with a base plate that supports the fuel nozzle, and an interface between the fuel nozzle and the base plate includes a surface in which bonding is performed by a fusion joint or a brazing joint and an inside part in which bonding is performed by pressure bonding.

To provide a fuel nozzle for a gas turbine combustor, offering favorable durability and strength reliability. In a fuel nozzle for a gas turbine combustor, jetting fuel into a combustion chamber of the gas turbine combustor, the fuel nozzle is metallurgically and integrally bonded with a base plate that supports the fuel nozzle, and an interface between the fuel nozzle and the base plate includes a surface in which bonding is performed by a fusion joint or a brazing joint and an inside part in which bonding is performed by pressure bonding.