公开(公告)号：US20170009781A1

公开(公告)日：2017-01-12

申请号：US15105359

申请日：2014-12-18

Applicant: SNECMA

Inventor： Vianney Christophe Marie MANIERE ,  Matthieu Jean Luc VOLLEBREGT ,  Gaetan Jean Marie LOUPY ,  Paul Henri Joseph MAUCLAIR

IPC: F04D29/66 ,  F04D29/68 ,  F04D29/54 ,  F04D29/32

Abstract: The present invention relates to a turbomachine component (1) or collection of components comprising at least a first and a second blade (3I, 3E) and a platform (2) from which the blades (3I, 3E) extend, characterized in that the platform (2), between the pressure face of the first blade (3I) and the suction face of the second blade (3E) has a non-axisymmetric surface (S) defining a plurality of fins (4) of substantially triangular section extending downstream of a leading edge (BA) of each of the blades (3I, 3E), each fin (4) being associated with a leading position and a trailing position on the surface (S), between which positions the fin (4) extends, such that: the leading position is situated at between 5% and 35% length relative to a chord of the blade (3I, 3E) extending from a leading edge (BA) to a trailing edge (BF) of the blade (3I, 3E);—the further a fin (4) is from the suction face of the second blade (3E), the further the leading position of said fin (4) is axially from the leading edge (BA) of the blades (3I, 3E).

Abstract translation: 本发明涉及涡轮机组件（1）或包括至少第一和第二叶片（3I，3E）和平台（2）的组件的集合，叶片（3I，3E）从该平台延伸，其特征在于， 平台（2）在第一叶片（3I）的压力表面和第二叶片（3E）的吸力面之间具有非轴对称表面（S），该​​非轴对称表面限定了在下游延伸的大致三角形截面的多个翅片（4） 每个叶片（3I，3E）的前缘（BA）中的每个翅片（4）与表面（S）上的前导位置和后方位置相关联，翅片（4）延伸的位置， 使得：引导位置相对于从叶片（3I，3E）的前缘（BA）延伸到叶片（3I，3E）的后缘（BF）的叶片（3I，3E）的弦线位于5％和35％之间 ）; - 另外一个翅片（4）来自第二叶片（3E）的吸力面，所述翅片（4）的引导位置进一步从轴向 叶片（3I，3E）的前缘（BA）。