公开(公告)号：US09926081B2

公开(公告)日：2018-03-27

申请号：US14892309

申请日：2014-05-21

Applicant: SNECMA

Inventor： Jonathan Vlastuin

IPC: B64C11/18 ,  B64D27/10 ,  F01D1/26 ,  F01D5/14 ,  F04D29/32 ,  B64C11/48 ,  F02K3/072 ,  F02C3/067 ,  B64D27/00

CPC classification number: B64D27/10 ,  B64C11/18 ,  B64C11/48 ,  B64D2027/005 ,  F01D1/26 ,  F01D5/141 ,  F02C3/067 ,  F02K3/072 ,  F04D29/324 ,  F05D2220/36 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2240/307 ,  F05D2260/96 ,  Y02T50/66 ,  Y02T50/673

Abstract: An aircraft turbopropeller includes two coaxial contra-rotating unducted propellers, upstream and downstream respectively, each propeller including an annular row of blades. The blades of the downstream propeller have a reverse sweep in relation to that of the blades of the upstream propeller. The leading edges of the blades of the downstream propeller extend radially outwards from downstream to upstream, at least over a radially outer portion of the blades.

公开(公告)号：US10415404B2

公开(公告)日：2019-09-17

申请号：US14771787

申请日：2014-02-27

Applicant: SNECMA

Inventor： Adrien Fabre ,  Adrien Laurenceau ,  Jonathan Vlastuin

IPC: F01D7/00 ,  B64C11/36 ,  F01D5/02 ,  F01D5/12 ,  B64D27/00

Abstract: A variable-pitch vane including a plurality of propeller blades (2). Each blade has a variable pitch according to a blade rotational axis (A1) and a root (201). A plurality of rotor connecting shafts (6), each shaft having a foot (602) and a head (601). The root (201) of each blade is mounted on the head (601) of a rotor connecting shaft via a pivot (8) in such a way as to allow each blade (2) to rotate according to the blade rotational axis (A1), in which each blade (2) has a blade pitch, such that the blade rotational axis (A1) is inclined relative to a radial axis (A2) passing through the foot (602) of the corresponding shaft.

公开(公告)号：US20160162629A1

公开(公告)日：2016-06-09

申请号：US14908399

申请日：2014-07-28

Applicant: SNECMA

Inventor： Cyril Verbrugge ,  Jonathan Vlastuin ,  Clement Dejeu ,  Anthony Louet

IPC: G06F17/50 ,  B64C11/18

CPC classification number: G06F17/5095 ,  B64C11/18 ,  B64D2027/005 ,  F01D5/141 ,  F04D27/001 ,  F04D29/324 ,  F05D2220/36 ,  F05D2260/81 ,  Y02T50/66 ,  Y02T50/673

Abstract: The present invention concerns a method for modelling at least a part of a blade (2) of a non-streamlined propeller (1), the part of the blade (2) having an offset (3), the method being characterised in that it comprises implementing, using data processing means (11) of a piece of equipment (10), steps of: (a) Parameterisation of at least one Bézier curve representing a deformation of said blade (2) characterising the offset (3), defined by: a. First and second end control points (PCU1, PCUK); b. At least one intermediate control point (PCU, iε[[2,k−1]] disposed between the end points (PCU1, PCUK), the parameterisation being implemented according to at least one deformation parameter and said cutting height in the blade (2), on the basis of which the abscissa of the intermediate control point (PCUi) and the ordinate of the second end point (PCUK) are expressed; (b) Determination of optimised values of the deformation parameter or parameters; (c) Outputting the values determined in this way to an interface (13) of said piece of equipment (10).

Abstract translation: 本发明涉及一种用于建模非流线型螺旋桨（1）的叶片（2）的至少一部分的方法，叶片（2）的部分具有偏移（3），该方法的特征在于它 包括实现使用一件设备（10）的数据处理装置（11）的步骤：（a）至少一个贝塞尔曲线的参数化，所述贝塞尔曲线表示所述叶片（2）的变形，其表征偏移（3） ： 一个。 第一和第二端控制点（PCU1，PCUK）; b。 设置在端点（PCU1，PCUK）之间的至少一个中间控制点（PCU，i＆egr; [[2，k-1]），参数化根据至少一个变形参数和刀片中的切割高度 2），基于此，中间控制点（PCUi）的横坐标和第二个终点（PCUK）的纵坐标表示;（b）确定变形参数或参数的优化值;（c）输出 以这种方式确定到所述设备（10）的接口（13）的值。

公开(公告)号：US10417378B2

公开(公告)日：2019-09-17

申请号：US14908399

申请日：2014-07-28

Applicant: SNECMA

Inventor： Cyril Verbrugge ,  Jonathan Vlastuin ,  Clement Dejeu ,  Anthony Louet

IPC: G06F17/50 ,  F01D5/14 ,  B64C11/18 ,  F04D27/00 ,  F04D29/32 ,  B64D27/00

Abstract: A method for modeling at least a part of a blade of a non-streamlined propeller, part of the blade having an offset. The method includes (a) Parameterization of at least one Bezier curve representing a deformation of the blade characterizing the offset, defined by: a. First and second end control points (PCU1, PCUK); b. At least one intermediate control point (PCUi, i∈[[2,K−1]]) disposed between the end points (PCU1, PCUK). The parameterization being performed according to at least one deformation parameter and the cutting height in the blade, on the basis of which the abscissa of the intermediate control point (PCUi) and the ordinate of the second end point (PCUK) are expressed. Optimized values of the deformation parameter or parameters are determined and then output.