公开(公告)号：US09938000B2

公开(公告)日：2018-04-10

申请号：US14899010

申请日：2014-06-12

Applicant: SNECMA

Inventor： Sebastien Tajan ,  Adrien Jacques Philippe Fabre ,  Christophe Jacquemard ,  Adrien Laurenceau

IPC: B64C11/30 ,  B64C11/34 ,  F04D29/32 ,  F04D29/36 ,  B64C11/06 ,  B64D27/00

CPC classification number: B64C11/346 ,  B64C11/06 ,  B64D2027/005 ,  F04D29/323 ,  F04D29/366 ,  Y02T50/66

Abstract: A pivot for an air propeller blade, the pivot including a rotary support for mounting radially on a propeller hub while being suitable for pivoting about a pivot axis; and a blade support including a housing for receiving a blade root and at least one arm extending laterally relative to the pivot axis and carrying a flyweight forming a counterweight; the arm and its flyweight presenting the general geometrical shape of a spherical cap.

公开(公告)号：US09932897B2

公开(公告)日：2018-04-03

申请号：US14648745

申请日：2013-12-12

Applicant: SNECMA

Inventor： Georges Jean Xavier Riou ,  Norman Bruno Andre Jodet ,  Jacky Novi Mardjono

IPC: F01D25/04 ,  F02C7/045 ,  F01D25/24 ,  F02K1/82 ,  B64D33/02

CPC classification number: F02C7/045 ,  B64D2033/0206 ,  F01D25/04 ,  F01D25/24 ,  F01D25/246 ,  F02K1/827 ,  F05D2220/30 ,  F05D2230/60 ,  F05D2230/64 ,  F05D2230/644 ,  F05D2240/91 ,  F05D2250/34 ,  F05D2260/36 ,  F05D2260/37 ,  F05D2260/96 ,  Y02T50/672

Abstract: An acoustic panel intended to be fixed internally to a fan casing of a turbojet engine, including an exterior face and an interior face which are curved about an axis, and two axially opposed transverse faces, the exterior curved face having at least one first recess on the side of a first transverse face and at least one second recess on the side of the opposite transverse face, said recesses each an attachment, in which said recesses do not open onto the interior curved face of the panel. Also covered are the turbojet engine including these panels and the method of mounting them.

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：US09920638B2

公开(公告)日：2018-03-20

申请号：US14320911

申请日：2014-07-01

Applicant: SNECMA

Inventor： Son Le Hong ,  Gael Frédéric Claude Cyrille Evain ,  Didier Fabre ,  Philippe Picot

IPC: F01D5/30 ,  F04D29/02 ,  F04D29/26 ,  F04D29/32

CPC classification number: F01D5/3084 ,  F01D5/3023 ,  F01D5/3069 ,  F04D29/023 ,  F04D29/26 ,  F04D29/321 ,  F04D29/322 ,  F05D2230/22 ,  F05D2300/6033 ,  Y02T50/672 ,  Y02T50/673

Abstract: A turbine or compressor stage for a turbine engine is provided. The stage includes a disk including a metal material configured to be coupled to a shaft of the turbine engine, an airfoil including a ceramic matrix composite material, and an interface part that is distinct from the airfoil and that is configured to be fastened to the disk and to fasten the airfoil. The interface part includes a ceramic or a ceramic matrix composite material.

公开(公告)号：US09914527B2

公开(公告)日：2018-03-13

申请号：US15454787

申请日：2017-03-09

Applicant: SNECMA

Inventor： Sebastien Tajan ,  Adrien Jacques Philippe Fabre ,  Christophe Jacquemard ,  Adrien Laurenceau ,  Romain Boudier

IPC: B64C11/32 ,  B64C11/06 ,  B64C11/34 ,  B64D27/00 ,  F01D7/02 ,  F04D29/36

CPC classification number: B64C11/346 ,  B64C11/06 ,  B64C11/325 ,  B64D2027/005 ,  F01D7/02 ,  F04D29/366 ,  F05D2220/323 ,  F05D2260/70 ,  F05D2260/77 ,  F05D2260/78 ,  Y02T50/66 ,  Y02T50/672 ,  Y02T50/673

Abstract: The invention relates to the field of aerial propellers, in particular the field of variable-pitch propellers, specifically for unducted fans. More specifically, the invention relates to a pivot (15) for a blade (14) of a propeller (3a, 3b), the pivot including at least a proximal portion (15a) made of metal and suitable for being retained in a radial orifice of a propeller hub, while being capable of turning in said orifice about a longitudinal axis (Z) of the pivot (15), and a distal portion (15b) including a receptacle (20) suitable for retaining a blade root, and at least one arm (17) of organic matrix composite material extending laterally relative to said longitudinal axis (Z) and supporting a flyweight (16).

公开(公告)号：US09909447B2

公开(公告)日：2018-03-06

申请号：US14415183

申请日：2013-07-08

Applicant: SNECMA

Inventor： Timothee Elisseeff ,  Sylvain Corradini

IPC: F01D25/00 ,  F01D25/24 ,  B29C70/30 ,  F01D21/04 ,  B29K105/08 ,  B29K309/08

CPC classification number: F01D25/005 ,  B29C70/30 ,  B29C70/541 ,  B29K2105/08 ,  B29K2309/08 ,  F01D21/045 ,  F01D25/24 ,  F05D2230/31 ,  F05D2240/11 ,  F05D2260/95 ,  F05D2300/601 ,  F05D2300/6032

Abstract: A method for manufacturing a turbomachine casing from composite material including: creating a semi-rigid protective layer from dry glass fibers that protects against galvanic corrosion, arranging the protective layer on a profiled mandrel by applying the protective layer against the annular radial flange thereof, forming and densifying the fibrous reinforcement on the mandrel while covering the protective layer.

公开(公告)号：US09909444B2

公开(公告)日：2018-03-06

申请号：US14051749

申请日：2013-10-11

Applicant: SNECMA

Inventor： Stephane Rousselin ,  Jean-Francois Adnot ,  Patrick Marcellin

IPC: F01D5/02 ,  F01D21/00

CPC classification number: F01D21/003 ,  F01D5/02

Abstract: A turbomachine fitted with a device for gathering the information recorded during operation of the former by a strain gauge positioned on a fan blade borne by a fan disc of the turbomachine, the device including a hollow cylindrical pipe positioned inside one of the rotating shafts of the turbomachine in order to guide at least one wire for transmitting this information, wherein the device further includes a part for attaching the pipe to the rotating shaft.

公开(公告)号：US09903375B2

公开(公告)日：2018-02-27

申请号：US14430729

申请日：2013-09-18

Applicant: SNECMA

Inventor： Olivier Belmonte ,  Augustin Curlier

IPC: F04D19/02 ,  F04D27/00 ,  F04D19/00 ,  F04D29/32 ,  F02K3/072 ,  B64C11/06 ,  B64D27/00

CPC classification number: F04D19/024 ,  B64C11/06 ,  B64D2027/005 ,  F02K3/072 ,  F04D19/002 ,  F04D27/002 ,  F04D29/323 ,  Y02T50/66 ,  Y10T29/49321

Abstract: A fan including a system for holding blades having variable pitch, in which the bases of the blades are mounted onto radial shafts of a rotor of the fan by pivots, is provided. The system includes a main body capable of being attached onto the rotor; and at least one holding arm mounted onto the main body and capable of extending inside a pivot so as to engage with the pivot in order to lock the movement of the pivot along the axis of the shaft on which the holding arm is mounted.

公开(公告)号：US09897517B2

公开(公告)日：2018-02-20

申请号：US14432878

申请日：2013-09-27

Applicant: SNECMA

Inventor： Cedrik Djelassi

IPC: F01D21/00 ,  F02C9/28 ,  G05B17/02 ,  G01M15/14 ,  G01L5/13

CPC classification number: G01M15/14 ,  F01D21/003 ,  F02C9/28 ,  F05D2260/80 ,  F05D2260/81 ,  F05D2260/821 ,  F05D2270/335 ,  F05D2270/44 ,  G01L5/133 ,  G05B17/02

Abstract: A method for monitoring a thrust fault of a turbofan during a modification of the thrust setting of the turbofan, the method including a step of processing the thrust setting via a filtering function and a transient-phase model such as to obtain a modelled thrust, a step of comparing the modelled thrust to the actual thrust such as to determine a thrust difference, a step of comparing the thrust difference to an alarm threshold; and a step of emitting an alarm in the event of exceeding the alarm threshold, wherein at a given iteration, in which the prior modelled thrust is known, the transient-phase model provides a time constant in accordance with the prior modelled thrust, and the filtering function provides a modelled thrust in accordance with the time constant obtained, the prior modelled thrust and the thrust setting.

公开(公告)号：US09885315B2

公开(公告)日：2018-02-06

申请号：US14326160

申请日：2014-07-08

Applicant: SNECMA ,  Centre National De La Recherche Scientifique (CNRS) ,  UNIVERSITE DE POITIERS ,  ENSMA

Inventor： Alexandre Alfred Gaston Vuillemin ,  Maxime Koenig ,  Peter Jordan ,  Pierre Comte ,  Yves Gervais

IPC: F02K1/34 ,  F02K1/46

CPC classification number: F02K1/34 ,  F02K1/46 ,  F02K3/06 ,  F05D2250/411 ,  F05D2260/962 ,  Y02T50/671

Abstract: The invention relates to a rear casing for a turbine engine comprising a primary body generating a primary flow (10) to be ejected through a primary nozzle (6), said rear casing (7) being shaped so as to be positioned downstream from the primary body and to define, on the inside of the turbine engine, the path followed by the primary flow downstream from the primary nozzle (6). The tail cone is characterised in that it comprises a connection to a system for supplying a pressurised gas and at least one perforation (8) for injecting the pressurised gas through the perforation and into the primary flow. The casing preferably comprises at least one means for rotating same about the axis of rotation of the mobile elements of the primary body.