55 results about "Angel wing" patented technology

An abradable seal is provided to improve turbine performance by physically reducing the clearance between a flange portion of the nozzle and an opposed angel wing / seal plate member of the bucket. The provision of an abradable seal also mitigates angel wing / seal plate tooth or fin wear by providing for abradable contact without metal to metal hard rub.

The present application provides an angel wing seal for a turbine bucket. The angel wing seal may include a first wing with a sinusoidally-shaped outer edge and a number of wing teeth positioned thereon.

A turbine bucket includes a radially inner mounting portion, a shank radially outward of the mounting portion, a radially outer airfoil and a substantially planar platform radially between the shank, and the airfoil. At least one axially-extending angel wing seal flange is formed on a leading end of the shank forming a circumferentially extending trench cavity along the leading edge of the shank, radially between an underside of the platform leading edge and the angel wing seal flange. A plurality of substantially radially-extending purge air holes are formed in the angel wing seal flange, adapted to fluidly connect a turbine rotor wheel space cavity with the trench cavity and thereby supply purge air to the outer surface of the angel wing seal flange.

A cover plate adapted to axially overlie root or shank portions of one or more buckets or blades secured to a turbomachine wheel, includes an arcuate cover plate body adapted to be secured to the turbomachine wheel so as to cover a root portion of at least one of the turbine buckets or blades; and at least one arcuate angel-wing seal segment detachably secured to one side of the arcuate cover plate body.

A turbine bucket includes a radially inner mounting portion, a shank radially outward of the mounting portion, a radially outer airfoil and a substantially planar platform radially between the shank and the airfoil. At least one axially-extending angel wing seal flange is formed on a leading end of the shank thus forming a circumferentially extending trench cavity along the leading end of the shank, radially between an underside of the platform leading edge and the angel wing seal flange. A plurality of substantially radially grooves are formed on a radially outer surface of the angel wing seal flange and extend into the shank.

Embodiments of the invention relate generally to rotary machines and, more particularly, to the cooling of at least portions of a turbine bucket. In one embodiment, the invention provides a method of cooling at least a portion of a turbine bucket, the method comprising: during operation of a turbine, altering a swirl velocity of purge air beneath a platform lip extending axially from the platform, wherein altering the swirl velocity of the purge air includes interrupting a flow of the purge air with a plurality of voids disposed along a length of an angel wing extending axially from a face of a shank portion of the turbine bucket.

A gas turbine engine, including: a plurality of blades (60) assembled into an annular row of blades and partly defining a hot gas path (26) and a cooling fluid path (24), wherein the cooling fluid path extends from a rotor cavity (22) to the hot gas path; an angel wing assembly (99) disposed on a side (74) of a base (76) of the row of blades; and pumping features (130) distributed about the angel wing assembly configured to impart, at a narrowest gap (42) of the cooling fluid path, motion to a flow of cooling fluid flowing there through. The plurality of pumping features, the angel wing assembly, and the base of the row of blades are effective to produce a helical motion to the flow of cooling fluid as it enters the hot gas path.

A turbine bucket includes a radially inner mounting portion; a shank radially outward of the mounting portion; at least one radially outer airfoil having a leading edge and a trailing edge; a substantially planar platform radially between the shank and the at least one radially outer airfoil; at least one axially-extending angel wing seal flange on a leading end of the shank thus forming a circumferentially extending trench cavity along the leading end of the shank, radially between an underside of the platform leading edge and a radially outer side of the angel wing seal flange; and slash faces along opposite, circumferentially-spaced side edges of the platform. At least one of the slash faces is formed with a dog-leg shape, a leading end of the at least one of slash face terminating at a location circumferentially offset from the leading edge of the at least one radially outer airfoil.

A rotary turbomachine includes a rotor mounting at least one disk having an outer surface and at least one bucket extending radially from said outer surface. A stationary stator component is located adjacent the disk, and a seal plate extends from a portion of the stationary stator component. An angel wing seal extends from the bucket, thereby defining a clearance gap between the seal plate and the angel wing seal. An abradable seal element is disposed on the seal plate, and the abradable seal element and the seal plate are canted at an acute angle relative to a center axis of the rotor extending radially outwardly in a direction toward the angel wing seal.

Embodiments of the invention relate generally to rotary machines and, more particularly, to the control of wheel space purge air in gas turbines. In one embodiment, the invention provides a turbine bucket comprising: a platform portion; an airfoil extending radially outward from the platform portion; a shank portion extending radially inward from the platform portion; at least one angel wing extending axially from a face of the shank portion, the at least one angel wing including an angel wing rim extending radially upward toward the airfoil; and a plurality of voids disposed along the angel wing rim.

An outer rim seal arrangement (10), including: an annular rim (70) centered about a longitudinal axis (30) of a rotor disc (31), extending fore and having a fore-end (72), an outward-facing surface (74), and an inward-facing surface (76); a lower angel wing (62) extending aft from a base of a turbine blade (22) and having an aft end (64) disposed radially inward of the rim inward-facing surface to define a lower angel wing seal gap (80); an upper angel wing (66) extending aft from the turbine blade base and having an aft end (68) disposed radially outward of the rim outward-facing surface to define a upper angel wing seal gap (80, 82); and guide vanes (100) disposed on the rim inward-facing surface in the lower angel wing seal gap. Pumping fins (102) may be disposed on the upper angel wing seal aft end in the upper angel wing seal gap.

A seal in a turbine of a combustion turbine engine is described. The seal is formed within a trench cavity defined between a rotor blade and a stator blade. The stator blade includes a sidewall projection and the rotor blade includes an angel wing projection extending toward the stator blade. The side wall projection overhangs the angel wing projection. The seal include: a port disposed on an inboard surface of the stator projection; and deflecting structure disposed on the angel wing projection. The deflecting structure may be configured to receive the fluid expelled from the port and deflect the fluid toward an inlet of the trench cavity.

Embodiments of the invention relate generally to rotary machines and, more particularly, to the cooling of at least portions of a turbine bucket. In one embodiment, the invention provides a method of cooling at least a portion of a turbine bucket, the method comprising: during operation of a turbine, altering a swirl velocity of purge air beneath a platform lip extending axially from the platform, wherein altering the swirl velocity of the purge air includes interrupting a flow of the purge air with a plurality of voids disposed along a length of an angel wing extending axially from a face of a shank portion of the turbine bucket.

A turbomachine bucket may include an airfoil, a shank coupled to the airfoil, and an angel wing coupled to the shank, the angel wing having an axially extending tip sized to seal with a plurality of discouragers, each discourager having a different axial extent. Various methods for modifying an angel wing to accommodate different sized discouragers are also disclosed.