公开(公告)号：US09556740B2

公开(公告)日：2017-01-31

申请号：US14361594

申请日：2012-11-22

Applicant: SNECMA

Inventor： Vincent Paul Gabriel Perrot ,  Damien Cellier ,  Alicia Lise Julia Dufresne ,  Philippe Pierre Marcel Marie Pelletrau ,  Jean-Francois Antoine Christian Rios ,  Laurent Christophe Francis Villaines

IPC: F01D5/14 ,  F01D5/34 ,  F04D29/32

CPC classification number: F01D5/141 ,  F01D5/34 ,  F04D29/324 ,  F05D2220/3216 ,  F05D2240/242 ,  F05D2240/303 ,  F05D2250/70 ,  F05D2250/71 ,  Y02T50/673

Abstract: A turbine engine blade comprising an airfoil extending axially between a leading edge and a trailing edge and extending radially between a root and a tip. The leading edge of the airfoil presents a sweep angle that is positive and that increases continuously from the root to a first radial height of the airfoil situated in the range 20% to 40% of the total radial height of the airfoil as measured from the root to the tip, and decreases continuously from this first radial height of the airfoil to the tip.

Abstract translation: 一种涡轮发动机叶片，包括在前缘和后缘之间轴向延伸并且在根部和尖端之间径向延伸的翼型件。 翼型的前缘呈现为正的扫掠角，并且从根部到第一径向高度连续增加，该翼型位于翼型的总径向高度的20％至40％的范围内，从根部测量 并且从翼型的第一径向高度到尖端连续地减小。

公开(公告)号：US10301941B2

公开(公告)日：2019-05-28

申请号：US14910586

申请日：2014-08-04

Applicant: SNECMA

Inventor： Damien Joseph Cellier ,  Alicia Lise Julia Dufresne ,  Philippe Pierre Marcel Marie Pelletrau ,  Vincent Paul Gabriel Perrot ,  Laurent Christophe Francis Villaines

IPC: F01D5/14 ,  F04D29/32 ,  F04D29/38

Abstract: A turbine engine rotor blade including an airfoil defined by plane airfoil sections stacked in a radial direction, each airfoil section being positioned radially at a height H, where height H is expressed as a percentage of the total height of the airfoil, and being identified by its sweep angle λ and its dihedral angle ν, wherein the sweep angle λ varies as a function of height H in such a manner that the sweep angle λ reaches a maximum at a height HλM, the value HλM lying in the range 5% to 40%, and the sweep angle λ increases from 0% to HλM, and wherein the dihedral angle ν varies as a function of H, the dihedral angle ν being a decreasing function of height H for heights H lying in the range 0% to Hν1, Hν1 lying in the range 10% to 40%.

公开(公告)号：US20140341749A1

公开(公告)日：2014-11-20

申请号：US14361594

申请日：2012-11-22

Applicant: SNECMA

Inventor： Vincent Paul Gabriel Perrot ,  Damien Cellier ,  Alicia Lise, Julia Dufresne ,  Philippe Pierre Marcel Marie Pelletrau ,  Jean-Francois Antoine Christian Rios ,  Laurent Christophe Francis Villaines

IPC: F01D5/14

CPC classification number: F01D5/141 ,  F01D5/34 ,  F04D29/324 ,  F05D2220/3216 ,  F05D2240/242 ,  F05D2240/303 ,  F05D2250/70 ,  F05D2250/71 ,  Y02T50/673

Abstract: A turbine engine blade comprising an airfoil extending axially between a leading edge and a trailing edge and extending radially between a root and a tip. The leading edge of the airfoil presents a sweep angle that is positive and that increases continuously from the root to a first radial height of the airfoil situated in the range 20% to 40% of the total radial height of the airfoil as measured from the root to the tip, and decreases continuously from this first radial height of the airfoil to the tip.

Abstract translation: 一种涡轮发动机叶片，包括在前缘和后缘之间轴向延伸并且在根部和尖端之间径向延伸的翼型件。 翼型的前缘呈现为正的扫掠角，并且从根部到第一径向高度连续增加，该翼型位于翼型的总径向高度的20％至40％的范围内，从根部测量 并且从翼型的第一径向高度到尖端连续地减小。