Snecma

Regis Grohens

Renaud Gabriel Constant Royan

Erwan Daniel Botrel

Renaud Gabriel Royan

A hollow blade including an airfoil extending along a longitudinal direction, a root, a tip, an internal cooling passage, and an open cavity defined by an end wall and a rim, together with cooling channels connecting the internal cooling passage to a pressure side. The cooling channels slope relative to the pressure side. A stack of airfoil sections of the blade at a level of the rim of the tip of the blade are offset towards the pressure side. The pressure side wall of the airfoil includes a projecting portion and cooling channels arranged in the projecting portion to open out into a terminal face of the projecting portion.

Gas turbine blade with tip sections offset towards the pressure side and with cooling channels

A turbine blade cooled by an automatically variable internal flow of cooling fluid. The blade includes orifices situated under the blade root via which the cooling fluid penetrates, and an adjustment plate including holes situated in register with the orifices, the adjustment plate having a coefficient of expansion that is different from the coefficient of expansion of the blade root.

Turbine blade equipped with means of adjusting its cooling fluid flow rate

A blade for a turbomachine bladed wheel is disclosed. The blade includes an airfoil and a platform with at least one air injection passage. The platform including includes a groove running along the pressure side of the airfoil at least in the vicinity of a downstream portion thereof, and formed between the pressure side and a ridge formed on the platform surface at a short distance from the downstream portion of the pressure side. At least one air injection passage is arranged in the groove. Because of the presence of the groove, the air stream injected via the air injection passage(s) is kept close to the pressure side and thus provides effective cooling of the downstream portion thereof.

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Tournan en Brie, France

Regis Grohens