公开(公告)号：US10345094B2

公开(公告)日：2019-07-09

申请号：US14786724

申请日：2014-04-22

Applicant: SNECMA

Inventor： Sylvain Corradini ,  Richard Mathon ,  Jean-François Durand

IPC: G01B11/06 ,  B65H81/00 ,  B29B11/04 ,  B29C45/00 ,  B29C45/76 ,  G01B11/02 ,  B29C70/32 ,  B29C45/14 ,  B29C53/60 ,  B29C53/80 ,  B29K101/00 ,  B29K105/10 ,  B29L22/00 ,  B29L31/00

Abstract: A method of measuring the thickness of a fiber texture wound on an impregnation mandrel for fabricating an annular structural part of a turbine engine out of composite material, the method including, prior to winding the fiber texture, acquiring a reference distance between an outside surface of the impregnation mandrel and a distance sensor positioned facing the outside surface of the impregnation mandrel, while winding the fiber texture, acquiring at least one real distance between the distance sensor and the outside surface of the fiber texture wound on the impregnation mandrel, and calculating the real thickness of the fiber texture wound on the impregnation mandrel by subtracting the real distance from the reference distance.

公开(公告)号：US10336464B2

公开(公告)日：2019-07-02

申请号：US15100246

申请日：2014-12-22

Applicant: SNECMA

Inventor： Pierrick Charlemagne ,  Delphine Leroux

IPC: A62C3/08 ,  F02C7/12 ,  F02C7/25 ,  B64C7/02 ,  B64D29/00 ,  B64D45/00 ,  F01D25/24

Abstract: An aircraft propulsion assembly includes an engine, a nacelle surrounding the engine, and a system for extinguishing a fire that may occur in the engine and/or in the nacelle. The extinguishing system has means for supplying an extinguishant to at least one extinguishant distribution pipe which opens into a cavity of the engine and/or a cavity of the nacelle. The extinguishing system also includes means for supplying said at least one pipe with air so as to ventilate the or each cavity.

公开(公告)号：US10302470B2

公开(公告)日：2019-05-28

申请号：US14649411

申请日：2013-12-03

Applicant: SNECMA

Inventor： Arnaud Jean-Marie Pierrot ,  Serge René Morreale

IPC: G01F1/00 ,  F01D25/18 ,  F16N7/40 ,  F16N29/00

Abstract: A system for measuring an oil retention volume of a first member of an engine lubricating system, the injected oil flowing inside the first member mixed with a first air volume, the mixture forming a first fluid, the measuring system including an oil injector at the inlet of the lubricating system; a first flowmeter to measure a first oil flow rate at the inlet of the lubricating system; a second flowmeter at the outlet of the first member to measure a second flow rate of the first fluid at the outlet of the first member; a measuring device to calculate a first value representing a quantity of oil in a volume of the first fluid flowing inside the first member; a calculator to calculate a third oil flow rate at the outlet from the second flow rate of the first fluid measured and the first value calculated and the instantaneous oil retention volume in the first member from the comparison of the first oil flow rate with the third oil flow rate.

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：US10233798B2

公开(公告)日：2019-03-19

申请号：US14904206

申请日：2014-07-10

Applicant: Snecma

Inventor： Jean-Louis Muller ,  Pierre Charles Mouton

IPC: F02C6/08 ,  F01M5/00 ,  F01D25/12 ,  F02C7/06 ,  F02C7/14 ,  F01P1/00 ,  F01P11/12

Abstract: The invention relates to a device (11) for cooling oil for a turbine engine, such as an aircraft turbojet or turboprop engine, characterized in that it comprises a duct (12) for circulating a flow of cold air (F1), means (16) for injecting oil into the duct, and means (19) for extracting the oil mixed with the flow of cold air (F1), located in the duct (12), downstream from the injection means (16).

公开(公告)号：US10227881B2

公开(公告)日：2019-03-12

申请号：US14431294

申请日：2013-09-26

Applicant: SNECMA

Inventor： Francois Gallet

IPC: F01D5/30 ,  F01D5/26

Abstract: A turbine blade including an airfoil (31) extending above a platform (32) and a root (33) extending below the platform, the root of the blade having the form of a radially extending arm (34), being produced from composite material and including at least one cylindrical face (34). The direction of the generatrices which are oriented in the direction of the platform to allow a clamping piece (5) to slide towards the latter on the cylindrical face under the action of centrifugal force. The arm includes, at its lower end, a protuberance (35) forming a radial bearing point for engagement with an element for retaining the blade on a turbine disc (1). The root (33) is located entirely on the side of the protuberance with respect to the face.

公开(公告)号：US10216867B2

公开(公告)日：2019-02-26

申请号：US14903559

申请日：2014-07-07

Applicant: SNECMA

Inventor： Damien Joseph Cellier ,  Vincent Perrot ,  Matthieu Jean Luc Vollebregt ,  Nicolas Jean Fernand Pignier

IPC: G06F17/50

Abstract: A method for modeling at least part of a non-axisymmetric surface (5) of one portion (2) of a part (1). The portion (2) is bounded by first and second extremal planes (PS, PR). The method includes processing data from a device (10), by: (a) modeling at least two basic non-axisymmetric surfaces (Sk, SI, SE) making up the surface, each of the basic surfaces (Sk, SI, SE) extending between both extremal planes (PS, PR) of the portion (S); (b) constructing at least one connection curve (CR) tangential to the first and second surfaces; (c) locally modifying the first and second basic surfaces (Sk, SI, SE) to keep to the connection curve (CR) near a discontinuity; and (d) restoring, at least part of the obtained surface (5).

公开(公告)号：US20190009387A1

公开(公告)日：2019-01-10

申请号：US16067253

申请日：2016-12-27

Applicant: SNECMA MEXICO, S.A. DE C.V.

Inventor： Gumaro RODRIGUEZ ,  Jesus CAMARENA ,  Yohannes MARCELET ,  Jesus MURILLO ,  Allan PUENTE

IPC: B24C9/00 ,  B24C1/10

Abstract: A guard for a part to be shot-blasted and having an axis of revolution, the guard including: a cover and a chamber shaped for receiving the part to be shot-blasted; the chamber having at least one planar section with a shape matching at least one planar section of the cover; two side guards mounted on the part to be shot-blasted and having one degree of freedom relative to the chamber and the cover, wherein the cover, the chamber and the two side guards form a box for sealing the shot, the box including a window for projecting the shot, the surface of which matches a portion of a surface of the chamber.

公开(公告)号：US10167874B2

公开(公告)日：2019-01-01

申请号：US14906712

申请日：2014-07-11

Applicant: SNECMA

Inventor： François Danguy ,  Jean-Michel Nguyen Duc ,  Laurent Fabbri ,  Cëdric Sene

IPC: F04D29/08 ,  F02K9/48 ,  F01D25/18 ,  F01D25/16 ,  F01D3/04 ,  F04D29/22 ,  F04D29/043 ,  F04D29/046 ,  F04D1/00 ,  F04D29/42 ,  F01D5/02 ,  F02K9/46 ,  F04D7/02 ,  F04D13/04 ,  F04D29/041 ,  F04D29/10

Abstract: The invention relates to the field of centrifugal pumps, and in particular it relates to a centrifugal pump (303, 403) comprising at least: an impeller (303a, 403a); a rotary shaft (302, 402) secured to said impeller (303a, 403a); a casing (320, 420) having an axial admission passage (325, 425); at least one first bearing (305, 405) supporting said rotary shaft (302, 402) in said casing (320, 420); and at least one dynamic seal (311, 411) around the rotary shaft (302, 402), the impeller (303a, 403a) being situated between the at least one dynamic seal (311, 411) and the axial admission passage (325, 425) of the pump (303, 403). The centrifugal pump (303, 403) also comprises, between the impeller (303a, 403a) and at least one dynamic seal (311, 411), an axial force compensation disk (330, 430) secured to the shaft (302, 402) and presenting a diameter greater than 70% of a diameter of the impeller (303a, 403a). A front face (330a, 430a) of the disk (330, 430) faces towards the impeller (303a, 403a) and is connected to a branch connection for fluid under pressure taken downstream from the pump (303, 403), and a rear face (330b, 430b) faces towards the dynamic seals (311, 411) and presents fins (330c, 430c) that are oriented radially, at least in part.

公开(公告)号：US10167731B2

公开(公告)日：2019-01-01

申请号：US14922647

申请日：2015-10-26

Applicant: Snecma

Inventor： Augustin Marc Michel Curlier ,  Nicolas Maurice Herve Aussedat ,  Gwénolé Yann Le Pache

IPC: F01D15/10 ,  H02K7/18 ,  F01D11/02 ,  F01D25/16 ,  F01D25/18 ,  F01D25/24 ,  F16N7/36 ,  H02K9/19

Abstract: A turbomachine for an aircraft, comprising a rotor shaft, a turbomachine case, a lubricated bearing chamber, at least one bearing supporting the rotor shaft and being located in the bearing chamber, a lubrication device comprising oil injection means to inject oil into the bearing chamber, and oil supply means to supply oil to said oil injection means, and an electric current generator, comprising an armature driven by the rotor shaft and a field coil fixed to the turbomachine case. The generator has an orifice, which passes longitudinally through the generator from one end to the other, and the oil injection means pass through the orifice so that oil can circulate in the axial direction through the generator.