Abstract: A high temperature turbine nozzle with automatic regulation of flow of cooling air passing therethrough. Each of vanes includes a first sleeve drilled with holes and a second sleeve that is engaged in the first sleeve, drilled with corresponding holes, and made of a material possessing a coefficient of expansion different from that of the first sleeve.

Abstract: A turbine engine blade having a plurality of blade sections stacked along a radial axis between a root and a tip. Each section extends along a longitudinal axis between a leading edge and a trailing edge, and along a tangential axis between a pressure-side face and a suction-side face. Each section presents a camber line, a deviation defined for each section as the difference between an angle between the tangent to the camber line at the leading edge and the longitudinal axis, and an angle between the tangent to the camber line at the trailing edge and the longitudinal axis. The minimum deviation is at the root of the blade, and the maximum deviation is present at sections situated in the range 0.3H to 0.8H, where H is the height of the blade measured from its root to its tip.

Abstract: A device (1) for connecting a fixed turbine engine portion (2) and a distributor (3) foot (31) of a turbine engine turbine, comprising: a ring-shaped body (11) adapted so as to be connected and secured to the fixed turbine engine portion (2), and two ring-shaped upstream (12) and downstream (13) brackets secured to the body (11), both brackets (12, 13) being adapted so as to clamp the foot (31) of the distributor, characterized in that at least one bracket (12, 13) is interrupted by forming an expansion or retraction slot (121, 131), the slot (121, 131) allowing an expansion of the bracket (12, 13) tending to close the slot (121, 131) or retraction of the bracket (12, 13) tending to further open the slot (121, 131), under the effect of a difference in internal temperatures of the device.

Abstract: A turbine engine blade having a plurality of blade sections stacked along a radial axis between a root and a tip. Each section extends along a longitudinal axis between a leading edge and a trailing edge, and along a tangential axis between a pressure-side face and a suction-side face. Each section presents a camber line, a deviation defined for each section as the difference between an angle between the tangent to the camber line at the leading edge and the longitudinal axis, and an angle between the tangent to the camber line at the trailing edge and the longitudinal axis. The minimum deviation is at the root of the blade, and the maximum deviation is present at sections situated in the range 0.3 H to 0.8 H, where H is the height of the blade measured from its root to its tip.

Abstract: A high temperature turbine nozzle with automatic regulation of flow of cooling air passing therethrough. Each of vanes includes a first sleeve drilled with holes and a second sleeve that is engaged in the first sleeve, drilled with corresponding holes, and made of a material possessing a coefficient of expansion different from that of the first sleeve.

Abstract: 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.

Abstract: 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.

Abstract: A blade for a turbomachine bladed wheel, the blade including an airfoil and a platform with at least one air injection passage, the platform including 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 said downstream portion of the pressure side, at least one air injection passage being 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.