公开(公告)号：US11460040B2

公开(公告)日：2022-10-04

申请号：US15548040

申请日：2016-02-04

Applicant: Safran Aircraft Engines

Inventor： Guillaume Olivier Vartan Martin ,  Alexandre Bernard Marie Boisson ,  Claire Marie Figeureu ,  Frederic Alain Edouard Allair ,  Thea Claire Lancien

IPC: F04D29/38 ,  F04D29/32 ,  F04D29/54 ,  F04D29/02 ,  F01D5/14 ,  F04D29/34 ,  F02K3/06

Abstract: A blade including at least one web and a vane having a leading edge and a trailing edge, wherein, for at least one aerofoil of the vane in the vicinity of the web, a maximum sweep angle associated with a position along a chord of the aerofoil extending from the leading edge to the trailing edge of the vane corresponding to a relative chord length of at least 50%.

公开(公告)号：US10787969B2

公开(公告)日：2020-09-29

申请号：US15775880

申请日：2016-11-14

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Kevin Morgane Lemarchand ,  Michel Gilbert Roland Brault ,  Guillaume Olivier Vartan Martin

IPC: F02K3/00 ,  F02C7/36 ,  F01D25/16 ,  F02K3/06 ,  F02C7/20 ,  F16H57/02 ,  F16H57/08

Abstract: A front part of an aircraft turbomachine of the bypass type including a single fan, a gas generator positioned downstream of the fan, a reducer interposed between the gas generator and the fan, a flow splitter and a structure with structural outlet guide vanes. The vanes each have a root arranged upstream of the flow splitter and the reducer is also arranged at least half upstream of the flow splitter.

公开(公告)号：US10670038B2

公开(公告)日：2020-06-02

申请号：US15982880

申请日：2018-05-17

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Thomas Alain De Gaillard ,  William Henri Joseph Riera ,  Guillaume Olivier Vartan Martin

IPC: F04D29/32 ,  F01D5/30 ,  F01D11/00

Abstract: Blade made of composite material, with an integrated platform, for an aircraft turbine engine, including a root connected to an aerofoil and having a connection platform between the root and the aerofoil, the root having a generally elongate shape along an axis (A) of elongation, the aerofoil having a curved cross-sectional shape and including a pressure face and a suction face, the platform including a first portion extending on the pressure-face side of the aerofoil and including a first longitudinal free edge and a second opposite longitudinal edge for connecting to the rest of the blade, the platform including a second portion extending on the suction-face side of the aerofoil and comprising a third longitudinal free edge and an opposite fourth longitudinal edge for connecting to the rest of the blade, wherein the first longitudinal free edge is concave and the third longitudinal free edge is convex, and, for any plane (P, P′) perpendicular to the axis of elongation and intersecting the platform, the distance (L1, L2; L1′, L2′) between the first and second edges, on the one hand, and the distance between said third and fourth edges, on the other hand, are identical in the plane considered.

公开(公告)号：US10676204B2

公开(公告)日：2020-06-09

申请号：US15351790

申请日：2016-11-15

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Kevin Morgane Lemarchand ,  Guillaume Olivier Vartan Martin

IPC: F02K1/70 ,  B64D33/04 ,  F01D17/16 ,  F04D29/54

Abstract: A variable-orientation stator vane of a turbine engine, comprising a wall that extends between a leading edge and a trailing edge forming a chord line. The chord line increases from a root end towards a tip end of said vane. This vane is fitted pivotably in a turbine engine casing so as to divert a flow of cold air circulating in an annular duct thereof.

公开(公告)号：US20170138371A1

公开(公告)日：2017-05-18

申请号：US15351790

申请日：2016-11-15

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Kevin Morgane Lemarchand ,  Guillaume Olivier Vartan Martin

IPC: F04D29/56 ,  F02K1/70 ,  F04D29/52 ,  B64D33/04 ,  F04D29/54

CPC classification number: B64D33/04 ,  F01D17/162 ,  F02K1/70 ,  F04D29/542 ,  F04D29/544 ,  F05D2220/32 ,  F05D2250/71 ,  F05D2260/50 ,  Y02T50/671

Abstract: A variable-orientation stator vane of a turbine engine, comprising a wall that extends between a leading edge and a trailing edge forming a chord line.The chord line increases from a root end towards a tip end of said vane. This vane is fitted pivotably in a turbine engine casing so as to divert a flow of cold air circulating in an annular duct thereof.