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）。

公开(公告)号：US20160375610A1

公开(公告)日：2016-12-29

申请号：US15195088

申请日：2016-06-28

Applicant: SNECMA

Inventor： Matthieu Jean Luc VOLLEBREGT ,  Patrick Emilien Paul Emile HUCHIN

IPC: B29C33/76 ,  F01D5/18

CPC classification number: B29C33/76 ,  B22C9/103 ,  F01D5/187 ,  F01D5/20 ,  F05D2230/21 ,  F05D2260/607 ,  Y02T50/671 ,  Y02T50/676

Abstract: A core for the moulding of a turbine engine blade, this blade including a vane extending along a spanwise direction and ending in a top, this core including a first core element to delimit a first internal cavity and a second core element of which at least one portion delimits a second internal cavity. The second cavity is situated between the first cavity and the top of the blade along the spanwise direction, and the portion of the second core element delimiting the second cavity includes a through hole, which emerges in line with an end face of the first core element to constitute a de-dusting conduit of the first cavity, this conduit traversing the second cavity from end to end while emerging in the top of the blade.

Abstract translation: 一种用于模制涡轮发动机叶片的芯，该叶片包括沿翼展方向延伸并终止于顶部的叶片，该芯包括限定第一内腔的第一芯元件和至少一个 部分界定第二内腔。 第二腔沿翼展方向位于第一腔和刀片的顶部之间，并且限定第二腔的第二芯体的部分包括通孔，其与第一芯体元件的端面对齐 以构成第一腔的除尘导管，该导管在出现在叶片顶部的同时从一端到另一端横过第二腔。