A blade includes a blade body having a cavity, an insert inserted in the cavity, a plurality of impingement holes formed in a circumferential wall of the insert, and a recovery path for recovering a cooling medium sprayed from the impingement holes The cooling medium can be recovered without being discharged into a main gas A gas turbine having this blade is used for a combined cycle power plant In this plant, steam is supplied as a cooling medium to the blade, and the steam recovered from the blade is supplied to a steam turbine

Cooled turbine blade and combined cycle power plant having gas turbine with this cooled turbine blade

A wall adapted for use in a gas turbine engine between a first and a hotter second fluid includes a first side over which is flowable the first fluid, and an opposite second side over which is flowable the second fluid. An elongate slot extends inwardly from the second side and is disposed in flow communication with a plurality of longitudinally spaced apart holes extending inwardly from the first side. The holes are disposed at a compound angle relative to the second side for discharging the first fluid obliquely into the slot and at a shallow discharge angle from the slot along the second side. In a preferred embodiment, the slot has an aft surface including a plurality of longitudinally spaced apart grooves extending from the holes to the wall second side.

Film cooled wall

Film coolant passages through the wall of a hollow airfoil for a gas turbine engine are oriented to direct coolant fluid therefrom at a substantial acute angle to the downstream direction and at a shallow angle to the surface of the airfoil. Each passage includes a metering portion at its inlet end and a four sided diffusing portion at its outlet end. The diffusing portion includes a pair of adjoining surfaces which are both parallel to a central axis of the passage, and another pair of adjoining surfaces which diverge from the central axis, the diverging pair of surfaces being located on the downstream side of the passage. With this configuration the coolant completely fills the diffusing section and exits as a wide film of coolant within the boundary layer downstream of the passage outlet.

Cross-flow film cooling passages

An article is described, including an inner surface which can be exposed to a first fluid; an inlet; and an outer surface spaced from the inner surface, which can be exposed to a hotter second fluid. The article further includes at least one row or other pattern of passage holes. Each passage hole includes an inlet bore extending through the substrate from the inlet at the inner surface to a passage hole-exit proximate to the outer surface, with the inlet bore terminating in a chevron outlet adjacent the hole-exit. The chevron outlet includes a pair of wing troughs having a common surface region between them. The common surface region includes a valley which is adjacent the hole-exit; and a plateau adjacent the valley. The article can be an airfoil. Related methods for preparing the passage holes are also described.

Articles which include chevron film cooling holes, and related processes

A wall in a gas turbine engine includes inner and outer surfaces having a row of compound chevron film cooling holes extending therethrough. The chevron holes diverge both longitudinally and laterally between an inlet at the wall inner surface and a chevron outlet at the wall outer surface.

Chevron film cooled wall

The electrode of an electrodischarge machining apparatus has a plurality of teeth which are substantially laterally tapered to increasing width toward the machine-held base end. Further, the plane of the tapered portions is inclined to that of the free end portions, which precede the tapered portions in application to the airfoil surface to be machined. As the tapered and inclined portions are inserted into the airfoil surface, a plurality of holes are formed which are diffused in both lateral directions and in one longitudinal direction to thereby provide a diffused hole with improved film cooling effectiveness.

Method and apparatus for forming diffused cooling holes in an airfoil

A hot gas turbine wheel shroud ring, for hot gas turbine engines, is adapted to be concentrically positioned around the periphery of a row of buckets or blades on the circumference of a turbine wheel to provide a predetermined small sealing and running clearance between the tips of the turbine blades and the ring. The shroud ring is characterized as incorporating certain opposite warping or deflection characteristics from those found in shroud rings under normal high temperature operating conditions.

Shroud means for turbine rotor blade tip clearance control

A gas turbine stator blade has a hollow profiled section through which cooling air passes. The profiled section has platforms (12, 14) at its inner and outer ends which have radial flanges (46, 48) by means of which it is held in the casing. A distributor plate (40, 42) is fixed outside each of the platforms (12, 14) between the projecting flanges (44, 46, 48, 50) of the platform to leave a space between the plate and the platform. The plate is perforated (80) and cooling air passes through the plate to flow over the blade platform. The air is discharged through passages (52) in the downstream platform flange (50, 46). The outlets of these passages are in line with the direction of flow of gas over the profiled section of the blade.

Stator guide blade used in gas turbine - has perforated plates over ends to direct cooling air over end platforms of blade

Electrode permettant l'usinage de trous ayant des surfaces de diffusion. Elle comprend au moins une dent 42 possedant une extremite orientee longitudinalement 43 et une base 44 qui relie cette extremite au corps 38, cette base possedant une surface biseautee qui fait avec l'axe de l'extremite orientee longitudinalement un angle tel que lorsqu'on approche cette dent de la piece et qu'on l'y fait penetrer, cette surface biseautee produit une erosion qui se traduit par un trou de diffusion. Application aux aubes de turbomachine.

Sidenstick James Edgar

Papers

Method and apparatus for forming diffused cooling holes in an airfoil

Shroud means for turbine rotor blade tip clearance control

Stator guide blade used in gas turbine - has perforated plates over ends to direct cooling air over end platforms of blade

Electrode perfectionnee pour l'usinage par etincelage de trous dans une piece

Mantelring fuer die spaltspielsteuerung einer turbinenrotorschaufel