公开(公告)号：US20170122108A1

公开(公告)日：2017-05-04

申请号：US15104904

申请日：2014-12-08

Applicant: SNECMA

Inventor： Sami BENICHOU ,  Christian BARIAUD ,  Stéphanie DEFLANDRE ,  Sébastien DIGARD BROU DE CUISSART ,  Patrick Emilien, Paul, Emile HUCHIN

IPC: F01D5/14 ,  G06F17/50 ,  F01D5/22 ,  F01D5/02 ,  F01D5/30

CPC classification number: F01D5/147 ,  F01D5/02 ,  F01D5/143 ,  F01D5/225 ,  F01D5/3007 ,  F05D2220/30 ,  F05D2230/50 ,  G06F17/50

Abstract: A blade for a turbomachine bladed wheel, the blade comprising a root, an airfoil, and a tip. The root and the tip have respective platforms, each presenting a surface (15) on a side toward the airfoil, which surfaces are referred to respectively as the root platform wall and the tip platform wall.Each of these platform walls is constituted by a pressure side portion and a suction side portion situated respectively pressure side and on the suction side and meeting at a crest curve (45, 65).Fabrication of the blade is facilitated in particular by the fact that every point of a first surface selected from the pressure side and the suction side and every point of the root and tip platform wall portions situated on the same side as the first surface presents a normal forming an acute angle or a right angle relative to a direction referred to as the first fabrication direction.A method of modeling the blade.

公开(公告)号：US20160319676A1

公开(公告)日：2016-11-03

申请号：US15105406

申请日：2014-12-12

Applicant: SNECMA

Inventor： Sami BENICHOU ,  Christian BARIAUD ,  Stéphanie DEFLANDRE ,  Sébastien DIGARD BROU DE CUISSART ,  Patrick Emilien Paul Emile HUCHIN

IPC: F01D5/22 ,  F01D9/04 ,  F01D5/30

Abstract: A blade for a turbomachine bladed wheel having N blades.At one end, the blade presents a platform that is formed integrally with an airfoil of the blade.Over a portion of the axial extent of the blade, a section through the platform wall on a plane perpendicular to the axis (X) of the wheel is constituted mainly by two first straight line segments arranged respectively on the two sides of the airfoil.Each of these segments forms an angle of 90°-180° /N relative to the radial direction on either side of the airfoil.

Abstract translation: 这些段中的每一个相对于翼型两侧的径向方向形成90°-180°/ N的角度。