公开(公告)号：US10002209B2

公开(公告)日：2018-06-19

申请号：US14784920

申请日：2014-04-16

Applicant: SNECMA

Inventor： Damien Joseph Cellier ,  Vincent Paul Gabriel Perrot

IPC: G06F17/50 ,  F01D9/04 ,  F01D5/14

CPC classification number: G06F17/50 ,  F01D5/14 ,  F01D5/141 ,  F01D9/041 ,  F05D2220/30 ,  F05D2260/81 ,  G06F17/5009 ,  Y02T50/673

Abstract: The present invention relates to a method for modelling a part (1), the method being characterized in that it comprises implementing, using data processing means (11) of a piece of equipment (10), steps of: (a) parameterizing a curve of class C1 representing the value of a physical quantity characterizing said part (1) as a function of a position along at least one portion of the part (1), the curve being defined by: a. two end points (PCU0, PCUK) defining the extent of said portion of the part (1); b. at least one intermediate point PCUi, i∈[[1,K−1]]) located between the two end points (PCU0, PCUK); c. at least two Bezier curves connected to said intermediate point; the parameterization being carried out using one or more parameters defining said intermediate point; (b) determining optimized values for said parameters of said curve; and (c) returning the determined values to an interface (13) of said piece of equipment (10).

公开(公告)号：US10001027B2

公开(公告)日：2018-06-19

申请号：US14876585

申请日：2015-10-06

Applicant: SNECMA

Inventor： Julien Fabien Patrick Becoulet ,  Alexandre Jean-Marie Tan-Kim

IPC: F01D21/00 ,  F01D21/04 ,  F01D5/12 ,  F01D5/30 ,  F01D9/02 ,  F01D5/02 ,  F02K3/06

CPC classification number: F01D21/04 ,  F01D5/02 ,  F01D5/025 ,  F01D5/12 ,  F01D5/30 ,  F01D9/02 ,  F01D21/006 ,  F01D21/045 ,  F02K3/06 ,  F05D2220/30 ,  F05D2220/36 ,  F05D2240/24 ,  F05D2260/902 ,  F05D2260/941 ,  Y02T50/671

Abstract: The invention relates to a turbine engine comprising a fixed structure (7), a fan (1) rotor (3), having an axis (XX) of rotation, and emergency braking means (12, 13) of the rotor (3), in particular in the event of the loss of a blade of the fan (1), characterized in that said emergency braking means (12, 13) comprise a first (18) and a second (22) member supported by the fixed structure (7), said members (18, 22) respectively being configured so as to interact frictionally with a first (20) element which is complementary to the rotor (3), by forming a stop of the rotor (3) towards the rear along the axis (XX), and a second (24) element which is complementary to the rotor (3), by forming a stop of the rotor (3) towards the front along the axis (XX), when the emergency braking means (12, 13) are active.

公开(公告)号：US09995176B2

公开(公告)日：2018-06-12

申请号：US15027666

申请日：2014-10-01

Applicant: SNECMA

Inventor： Olivier Belmonte ,  Jérémy Phorla Lao

IPC: F01D25/18 ,  F16H57/04 ,  F01D15/12 ,  B64C11/48 ,  F01D25/16 ,  F02C7/06 ,  F16C27/04 ,  F16C33/66 ,  F16C23/08 ,  F01M11/02 ,  F16N21/00 ,  F16C35/06 ,  F16C19/52

CPC classification number: F01D25/186 ,  B64C11/48 ,  F01D15/12 ,  F01D25/16 ,  F01D25/18 ,  F01M11/02 ,  F02C7/06 ,  F05D2220/32 ,  F05D2260/40311 ,  F05D2260/98 ,  F05D2300/43 ,  F05D2300/431 ,  F16C19/527 ,  F16C23/086 ,  F16C27/045 ,  F16C33/6659 ,  F16C35/061 ,  F16C2360/23 ,  F16H57/0426 ,  F16N21/00 ,  Y02T50/672

Abstract: The device (20) comprises two outer and inner concentric rings (22, 23), one of which is connected to an oil supply from one of the repositories, the other ring being connected to the other repository, the oil flowing between said rings, and bearings between the rings in order to change repositories between the two rings. According to the invention, the device (20) further comprises a flexible means (31) forming a shock absorber, provided between a first of said rings and an intermediate ring (41) that is separated from a second of said rings by said bearings (25), said flexible means (31) defining a deformable sealed chamber (32) in which oil travels between the two repositories.

公开(公告)号：US09982603B2

公开(公告)日：2018-05-29

申请号：US15106162

申请日：2014-11-26

Applicant: Snecma

Inventor： Pierre-François Simon Paul Pireyre ,  Francois Leglaye ,  David Gino Stifanic

IPC: F02C7/266 ,  H01T13/08 ,  F23R3/60 ,  F02C3/14 ,  F23R3/00 ,  F23R3/10 ,  F23R3/28

CPC classification number: F02C7/266 ,  F02C3/14 ,  F05D2220/32 ,  F05D2240/35 ,  F23D2207/00 ,  F23D2209/00 ,  F23D2211/00 ,  F23R3/002 ,  F23R3/10 ,  F23R3/28 ,  F23R3/60 ,  F23R2900/00005 ,  F23R2900/00012 ,  H01T13/08

Abstract: Assembly comprising, on a turbomachine:—a combustion chamber (30) having a longitudinal axis (30a) and comprising: internal and external longitudinal walls (90) having a first opening (90a) substantially transverse to said axis (30a), an outer casing (110) having a second opening (110a) likewise substantially transverse to said axis (30a),—a turbomachine sparkplug (150),—a device (130) for radially securing the sparkplug (150), which device (130) comprises a sparkplug adapter (160) fixed toward a first end to the outer casing (110), facing the second opening (110a) and through which adapter and casing the sparkplug (150) in question passes, and a sparkplug guide (190) kept in contact with the external longitudinal wall (90), facing the first opening (90a) and through which the sparkplug (150) passes to emerge in the combustion chamber (30), the sparkplug (150) and the sparkplug guide (190) each having a screw thread (103, 105), the screw threads (103, 105) being screwed together so as to stabilize the sparkplug (150) radially to the axis (30a) of the combustion chamber (30) with respect to said external longitudinal wall (90), and—in this condition, the sparkplug (150) and the sparkplug guide (190) are mounted freely with respect to the outer casing (110) in a direction substantially radial to the axis of the second opening (110a).

公开(公告)号：US09981751B2

公开(公告)日：2018-05-29

申请号：US14576694

申请日：2014-12-19

Applicant: SNECMA

Inventor： Jeremy Edmond Fert ,  Julien Pavillet

IPC: B64D29/06 ,  B64D27/10 ,  B64D33/08 ,  F01D25/24 ,  F02K3/04 ,  F02C7/18 ,  F02C7/32

CPC classification number: B64D29/06 ,  B64D27/10 ,  B64D33/08 ,  F01D25/24 ,  F02C7/18 ,  F02C7/32 ,  F02K3/04 ,  F05D2230/72 ,  F05D2260/213 ,  Y02T50/672 ,  Y02T50/676

Abstract: An aircraft propulsion unit comprising an engine and a nacelle including an axisymmetric casing (16) delimiting an air flow path, wherein this casing has at least two openings closed by removable and interchangeable panels (18), at least one of these panels carrying one component (24) of the propulsion unit.

公开(公告)号：US09976480B2

公开(公告)日：2018-05-22

申请号：US14566916

申请日：2014-12-11

Applicant: SNECMA

Inventor： Jackie Raymond Julien Prouteau ,  Pierrick Mouchoux

IPC: F02C1/00 ,  F02C7/04 ,  F02C7/18 ,  B60K11/08 ,  B64D13/00 ,  B64D33/02 ,  B64D33/08 ,  B60H1/30

CPC classification number: F02C7/04 ,  B60H1/30 ,  B60K11/08 ,  B60Y2200/50 ,  B60Y2200/51 ,  B64D13/00 ,  B64D33/02 ,  B64D33/08 ,  B64D2033/0213 ,  B64D2241/00 ,  F02C7/18 ,  Y10T137/0536

Abstract: A fluid intake system including a fluid collector scoop designed to be fastened on an inside surface of a wall in order to collect the fluid flowing on the outside of the wall; and an extraction duct suitable for directing the fluid from an inlet orifice into the duct to at least one outlet orifice from the duct, is provided. The scoop is arranged so as to direct the collected fluid towards the inlet orifice of the extraction duct. In this system, at least one outlet orifice is of substantially elliptical section with a ratio of the major diameter of the ellipse over its minor diameter being greater than 1.5.

公开(公告)号：US09970324B2

公开(公告)日：2018-05-15

申请号：US14397361

申请日：2013-05-02

Applicant: SNECMA

Inventor： Fabrice Tailpied ,  Michel Bertin ,  Jean-Michel Couture ,  Herve Dagron ,  Roland Manchon ,  Cedric Mustiere

IPC: B23P19/04 ,  F01D25/28 ,  B25B13/48 ,  F01D5/06 ,  B25B21/00

CPC classification number: F01D25/285 ,  B23P19/042 ,  B25B13/48 ,  B25B21/002 ,  F01D5/066 ,  F05D2230/70 ,  Y10T29/4932

Abstract: A method for unscrewing a link nut of an HP rotor of a twin-spool turbine, including a front fan, an intermediate casing, a HP module with a HP rotor, and a LP turbine module, the intermediate casing including a support bearing for the HP rotor, the rotor being retained in the bearing by the link nut, the method including: placing an unscrewing tool in front of the link nut after having removed the fan and released access to the nut from the front; with rotation of the HP rotor locked and the frontal unscrewing tool including a socket spanner including teeth having a shape that complements that of teeth of the link nut, attaching a mounting for the socket spanner to the intermediate casing, the socket spanner being rotatably mounted on the mounting, and applying an unscrewing torque to the socket spanner. An unscrewing tool implements the method.

公开(公告)号：US09969035B2

公开(公告)日：2018-05-15

申请号：US15106124

申请日：2014-12-09

Applicant: Snecma

Inventor： Patrick Emilien Paul Emile Huchin ,  Karine Deschandol ,  Sébastien Digard Brou De Cuissart ,  Serge Fargeas ,  Marc Soisson ,  Anthony Texier ,  Valéry Piaton

IPC: B22D25/02 ,  B22C9/22 ,  B23P15/02 ,  B22D13/06 ,  B22D27/15 ,  F01D5/28

CPC classification number: B23P15/02 ,  B22C9/22 ,  B22D13/06 ,  B22D13/066 ,  B22D25/02 ,  B22D27/15 ,  F01D5/28 ,  F05D2220/323 ,  F05D2230/10 ,  F05D2230/21 ,  F05D2240/30 ,  F05D2300/173 ,  F05D2300/174 ,  F05D2300/608

Abstract: The invention relates to a method for producing multiple metal turbine engine parts, comprising steps consisting in: a) casting a metal alloy in a mold in order to produce a blank (3); and b) machining the blank in order to produce the parts, characterized in that the blank obtained by casting is a solid polyhedron having first and second sides (30a, 30b) and third and fourth sides (30c, 30d), in which the third and fourth sides extend between the first and second sides, flaring apart from the first side towards the second side, first at a first angle and subsequently at a second larger angle, and said at least one part is machined in the blank.

公开(公告)号：US09957896B2

公开(公告)日：2018-05-01

申请号：US14361954

申请日：2012-12-04

Applicant: SNECMA

Inventor： Olivier Belmonte ,  Sebastien Jean Laurent Prestel

IPC: F01D11/08 ,  F02C7/20 ,  F01D11/12 ,  F01D25/24 ,  F01D25/28 ,  F02C7/28

CPC classification number: F02C7/20 ,  F01D11/122 ,  F01D25/246 ,  F01D25/28 ,  F02C7/28 ,  F05D2230/644 ,  F05D2240/11 ,  F05D2240/14 ,  F05D2250/312 ,  F05D2250/35 ,  F05D2250/70 ,  F05D2260/30

Abstract: A device for axially arresting a sealing ring made of an abradable material in contact with a periphery of an aircraft turbomachine module rotor, the device having a first reference central axis, and including: a support including a support opening defining a circular track centered on a second axis at a distance from the axis; and an axial stop part including an extraction passage centered on a third axis at a distance from the axis, and defining a complementary circular track around its periphery, cooperating with the track to allow the part to rotate about the axis, between an axial stop position for the sealing ring, and a position to extract the ring through the extraction passage.

公开(公告)号：US09951625B2

公开(公告)日：2018-04-24

申请号：US14931474

申请日：2015-11-03

Applicant: SNECMA

Inventor： Sébastien Serge Francis Congratel ,  Maurice Guy Judet

IPC: F01D5/10 ,  F01D5/22 ,  F01D11/00 ,  F01D5/30

CPC classification number: F01D5/10 ,  F01D5/22 ,  F01D5/3023 ,  F01D11/006 ,  F05D2260/30 ,  F05D2260/96 ,  Y02T50/671

Abstract: A turbine wheel for a turbine engine, comprising a disk carrying blades each having a platform, carrying an impeller connected by a stilt to a root. Each blade comprises an upstream radial wall and a downstream radial wall extending inwards from the platform of the blade. The roots of the blades are engaged into slots on the periphery of the disk, so that the radial walls of the blades and the platforms of the blades are circumferentially arranged end-to-end, and define inter-blade cavities radially inside the platforms, each accommodating an inter-blade sealing and vibration damping member. At least one member comprises an elastically deformable element configured so as to be elastically prestressed against the walls of a cavity in the member mounting position.