公开(公告)号：US09752610B2

公开(公告)日：2017-09-05

申请号：US14687120

申请日：2015-04-15

Applicant: SNECMA

Inventor： Alain Jean-Claude Rousseau

IPC: F16B39/10 ,  F16B39/12 ,  F01D5/02 ,  F01D5/06

CPC classification number: F16B39/12 ,  F01D5/026 ,  F01D5/027 ,  F01D5/066 ,  F05D2250/73 ,  F05D2260/36 ,  F16B39/10 ,  Y02T50/671

Abstract: The invention relates to a device for locking a nut (13) in a tightened position on a rotary shaft (12), said rotary shaft (12) being hollow at least at one end (14). The locking device comprises a plurality of outer notches (16) formed in a face of the nut (13), said outer notches (16) extending parallel to a longitudinal axis (X) of the nut (13), a plurality of inner notches (15) formed in the end (14) of the rotary shaft (12), said inner notches (15) extending parallel to a longitudinal axis (X) of the rotary shaft (12), and a ring (18) suitable for being installed inside said end (14) of the rotary shaft (12) and presenting at least one first radial finger (19) for being received both in one of the inner notches (15) and in one of the outer notches (16) with the nut (13) being in a tightened position and the two notches (15, 16) housing said first radial finger (19) being at least partially in alignment in a radial direction. In order to balance the ring about a central axis (X), the ring (18) presents an internal outline (21) arranged in such a manner that the barycenter (B) of said internal outline (21) is offset relative to said longitudinal axis (X) when the ring (18) is installed inside the end (14) of the rotary shaft (12).

公开(公告)号：US09752533B2

公开(公告)日：2017-09-05

申请号：US15029434

申请日：2014-10-16

Applicant: SNECMA

Inventor： Gabriel Allut ,  Mohamed Bozetine ,  Antoine Olivier François Colin ,  Barbara-Ann Piquet

IPC: F02K1/76 ,  F02K1/64

CPC classification number: F02K1/766 ,  F02K1/64 ,  F02K1/76

Abstract: A method for monitoring a locking system includes N locks, each lock being monitored by two locking sensors, each locking sensor being capable of indicating if the lock that it monitors is in a locked or unlocked state, each locking sensor being able to be in a valid or invalid status, the method including determining the state of the locking system on the basis of the state of the locks detected by the locking sensors; determining a reliability level associated with the state of the locking system on the basis of the number of valid locking sensors monitoring the locks that are in the same state as the locking system.

公开(公告)号：US09745051B2

公开(公告)日：2017-08-29

申请号：US14648051

申请日：2013-11-15

Applicant: SNECMA

Inventor： Nicolas Jerome Jean Tantot ,  Thierry Brichler

IPC: B64C11/44 ,  B64D31/06 ,  B64C11/30

CPC classification number: B64C11/44 ,  B64C11/305 ,  B64D31/06 ,  Y02T50/66

Abstract: An engine control device having a calculator for calculating a pitch setpoint for at least one propeller of the engine, the calculator taking account at least of a flight speed.

公开(公告)号：US09726033B2

公开(公告)日：2017-08-08

申请号：US14357113

申请日：2012-11-12

Applicant: SNECMA

Inventor： Alain Dominique Gendraud ,  Fabrice Marcel Noel Garin ,  Romain Nicolas Lunel

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

CPC classification number: F01D11/006 ,  F01D5/3007 ,  F01D5/3015 ,  F01D5/326 ,  F01D11/001 ,  F05D2240/55 ,  F05D2250/231 ,  F05D2250/232 ,  F05D2260/30 ,  Y02T50/672

Abstract: A rotor wheel for a turbine engine, such as an airplane turboprop or turbojet, the rotor wheel including a rotor disk including teeth at its outer periphery defining slots for axially mounting and radially retaining blade roots. An annular lip includes an annular rim extending axially downstream from and radially towards an inside of a radial retaining mechanism formed to project axially from an upstream face of the disk, and a sealing mechanism is arranged radially inside the annular lip and upstream ends of platforms of the blades.

公开(公告)号：US09709002B2

公开(公告)日：2017-07-18

申请号：US14178584

申请日：2014-02-12

Applicant: SNECMA

Inventor： Guillaume Pouyau ,  Nicolas Sirvin

IPC: F02K1/38

CPC classification number: F02K1/386 ,  F05D2260/2212 ,  Y02T50/675

Abstract: A method of mixing in a discharge conduit, in a turbine engine with two or more flows, of a primary flow and a secondary flow, the two flows emerging in the discharge conduit by two coaxial ducts, separated by an internal housing which has an end downstream relative to the flow direction of the flows, the two coaxial ducts each being defined between an internal wall and an external wall, upstream of the downstream end of the internal housing, and the secondary flow surrounding the primary flow, is provided. The method includes disposing a divergent radial deflection device in the primary duct, spaced apart from the walls of the primary duct. A turbine engine including the deflection device is also provided.

公开(公告)号：US09702259B2

公开(公告)日：2017-07-11

申请号：US14364475

申请日：2012-12-19

Applicant: SNECMA

Inventor： Roland Azalbert ,  Nicolas Claude Herve Lafond ,  Damien Guilmet

IPC: F01D9/04 ,  F01D25/24 ,  F04D29/54 ,  F04D29/66

CPC classification number: F01D9/04 ,  F01D25/246 ,  F04D29/542 ,  F04D29/668 ,  F05D2260/30

Abstract: A sectorized turbomachine compressor guide vanes assembly includes assembled sectors forming two concentric shell rings, one outer and one inner, between which vanes are arranged with their leading and trailing edges near transverse faces of the shell rings, and of which an outer shell ring externally includes an attachment mechanism to an external casing that houses the sectors. The attachment mechanism is axially offset from the rear transverse face of the shell ring to be located, in projection, in alignment with the vanes between the leading and trailing edges thereof.

公开(公告)号：US09683452B2

公开(公告)日：2017-06-20

申请号：US14134405

申请日：2013-12-19

Applicant: SNECMA

Inventor： Florent Pierre Antoine Luneau ,  Alain Dominique Gendraud ,  Patrick Joseph Marie Girard ,  Sebastien Jean Laurent Prestel

IPC: F01D11/12 ,  F01D11/00

CPC classification number: F01D11/122 ,  F01D11/001 ,  F05D2250/283

Abstract: A turbine for a gas turbine engine comprising at least one turbine stator and one turbine rotor, said turbine stator comprising at least one inner annular platform, said inner platform comprising a radial wall delimiting at least one cavity between the turbine stator and the turbine rotor, wherein the turbine rotor comprises at least one elongate element positioned substantially axially and defining a sealing baffle in said cavity, and in that the turbine stator comprises at least one element made of abradable material designed to engage with said elongate element of the turbine rotor so as to form a labyrinth seal.

公开(公告)号：US09671021B2

公开(公告)日：2017-06-06

申请号：US14351353

申请日：2012-10-11

Applicant: SNECMA ,  CENTRE NATIONAL D'ETUDES SPATIALES CNES

Inventor： Christelle Lea Branchet-Cohen ,  Karine Sandra Christel Lenain

IPC: F16L23/18 ,  F16J15/06 ,  F16J15/08

CPC classification number: F16J15/06 ,  F16J15/0887 ,  F16L23/18

Abstract: An arrangement of a biconical annular seal having a laid down V shaped cross-section, in an annular groove having a trapezoid shaped cross-section, a small base of the trapezoid corresponding to a cylindrical bottom of the groove and being radially inwardly open at a great base of the trapezoid. The seal includes a radially outer annular heel and two generally conical annular wings extending radially inwardly from the heel, an inner radial end of each wing being axially bearing against an associated wall of the groove. The seal is mounted in the groove such that the heel of the seal is located radially distal to a bottom of the groove.

公开(公告)号：US09637239B2

公开(公告)日：2017-05-02

申请号：US14786500

申请日：2014-04-24

Applicant: SNECMA

Inventor： Mathieu Ange Alexis Poisson ,  Julien Michel Patrick Christian Austruy ,  François Gallet ,  Mario Lambey

IPC: B64D27/10 ,  B64D27/26 ,  F02C7/20

CPC classification number: B64D27/10 ,  B64D27/26 ,  B64D2027/264 ,  B64D2027/266 ,  F02C7/20

Abstract: The invention provides a suspension structure for suspending a turboprop (10) having two unducted propellers on a structural element of an aircraft, the suspension structure comprising a cradle (18) for fastening to a structural element of the aircraft and having two lateral beams (22) connected to a main beam (20) extending parallel to a longitudinal axis (14) of the turboprop so as to form a V-shaped cradle structure, the cradle being fastened to the turboprop via two angle members (24) connecting each free end of the lateral beams of the cradle to the turboprop, via an axial link (28) connecting one end of the main beam of the cradle of the turboprop, and via at least one transverse link (30) situated in a plane extending transversely relative to the longitudinal axis of the turboprop and connecting the cradle to the turboprop.

公开(公告)号：US09631640B2

公开(公告)日：2017-04-25

申请号：US14363898

申请日：2012-12-14

Applicant: SNECMA

Inventor： Guillaume Roffi ,  Julien Tran

IPC: F04D29/66 ,  B64D33/02 ,  F02C7/045 ,  F01D25/32 ,  F04D19/00

CPC classification number: F04D29/668 ,  B64D33/02 ,  B64D2033/0206 ,  F01D25/32 ,  F02C7/045 ,  F04D19/002 ,  F04D29/663

Abstract: An acoustic protection device for a fan casing of an aircraft turbomachine, including an acoustic protection panel forming a ferrule sector centered on a center axis, and one or more vibration damping strips pressed on a first side to an external surface of the panel and on a second side to an internal surface of the casing, each damping strip including two opposite edges each including an upstream end and a downstream end spaced from each other along a direction of the center axis. At least one of both opposite edges of at least one of the damping strips is shaped such that liquid present on this edge can flow by gravity towards either or both of its upstream and downstream ends.