Abstract: The invention relates to a turbomachine (24) of the «open rotor» type or a turboprop engine comprising a nacelle (26) defining an air inlet (28), a central hub (30) and an annular air intake section (32) surrounding the central hub (30) and opening into a air supply main section (34), with the central hub (30) comprising a central trap (36) having an aperture (38) for trapping the foreign objects in an air flow entering the turbomachine (24), and an air recovery channel (48) having a discharge end (48a), through which said air recovery channel (48) opens into the main section (34), provided on the central hub (30).
Type:
Application
Filed:
November 25, 2016
Publication date:
December 13, 2018
Applicant:
Safran Aircraft Engines
Inventors:
Romain Jean-Claude Ferrier, Romeo Brogna, Jackie Raymond Julien Prouteau, Nicolas Joseph Sirvin
Abstract: A gas turbine engine includes a device for providing sealing between one rotor section and one stator section. The device includes a coating made of an abradable material attached to the stator section. The device further includes a lip on a portion of the rotor section. The lip is configured to form a seal with the abradable material. The gas turbine engine further includes passages for a gaseous fluid and means for blowing such gaseous fluid. The passages open into the rotor section provided with the lip, so that blown gaseous fluid can be present in a zone radially located between the coating and the lip.
Type:
Application
Filed:
June 12, 2018
Publication date:
December 13, 2018
Applicant:
Safran Aircraft Engines
Inventors:
Cyrille Telman, Gaël Frédéric Claude Cyrille Evain, Olivier Arnaud Fabien Lambert, Mathieu Charles Jean Verdiere
Abstract: A device for controlling a propeller, having variable-pitch blades, of a turboprop engine, has a first hydromechanical device for controlling the pitch of the blades of the propeller and a second hydromechanical device for controlling the speed of rotation of the propeller. The device includes a single electromechanical actuator with a movable actuator member mechanically connected both to the first hydromechanical device for controlling the pitch, in order to manage the pitch setpoint, and to the second hydromechanical device for controlling the speed, in order to manage the speed setpoint.
Abstract: Electrical equipment of the type comprising calculation means or a data concentrator for connecting to a tachometer (2) via a cable (3) that comprises a measurement wire (36, 37) and a test wire (38), the electrical equipment having a measurement input (11, 12) to which the measurement wire can be connected and a test input (14) to which the test wire can be connected, measurement acquisition components (7) connected to the measurement input and arranged to acquire an electrical measurement signal present on the measurement wire and produced by the tachometer, test acquisition components (8) connected to the test input and arranged to detect whether the test wire is or is not open-circuit, and processor components (9) arranged to detect a break of the measurement wire if the test wire is open-circuit.
Abstract: An airplane propelled by a turbine engine having at least one fan, the turbine engine being integrated in the rear of a fuselage of the airplane, extending it rearwards, the airplane further including at least one acoustic baffle forming panel connected to the fuselage of the airplane and arranged below the turbine engine.
Type:
Application
Filed:
November 21, 2016
Publication date:
December 13, 2018
Applicant:
SAFRAN AIRCRAFT ENGINES
Inventors:
Norman Bruno Andre JODET, Jeremy Paul Francisco GONZALEZ, Herve ROLLAND
Abstract: An assembly including a compressor for a turbine engine, and a discharge system including a supply duct, one end of which is connected to the compressor, the duct being configured to collect therefrom a flow of air compressed by the compressor; and a pressure-reduction device including an inlet and an outlet, the inlet being connected to the other end of the supply duct, wherein the pressure reduction device includes a casing forming a volume between the inlet and the outlet, a porous material occupying the volume, and a device for holding the porous material within the casing, wherein the outlet has an open section allowing the upper air to pass through the open section of the inlet.
Type:
Application
Filed:
December 7, 2016
Publication date:
December 13, 2018
Applicant:
SAFRAN AIRCRAFT ENGINES
Inventors:
Josselin David Florian REGNARD, Laurent Louis Robert BAUDOIN
Abstract: A turbine engine having an annular combustion chamber formed by two coaxial annular shrouds, an inner shroud and an outer shroud relative to the axis of the turbine engine, which shrouds are arranged one inside the other and are connected together at their upstream ends by an annular chamber end wall that is fastened to an outer casing surrounding the outer annular shroud, the downstream ends of the inner and outer annular shrouds being connected to flanges fastened to an inner casing and to the outer casing, respectively. The upstream end of at least one of the inner and outer shrouds is centered by bearing radially against the annular chamber end wall and co-operates therewith in leaktight axial sliding.
Type:
Grant
Filed:
May 11, 2015
Date of Patent:
December 11, 2018
Assignee:
SAFRAN AIRCRAFT ENGINES
Inventors:
Romain Nicolas Lunel, Denis Jean Maurice Sandelis
Abstract: A system for reproducing a dry friction torque applied to an actuator on a valve of a hydraulic line including a disc coupled to a power transmission shaft; a disc brake including a caliper mounted on a frame and plates adapted to be put into contact with the disc; and an electric actuator configured to control the force of application of the plates onto the disc so as to apply a controlled resistive torque to the power transmission shaft, is provided.
Type:
Grant
Filed:
September 2, 2015
Date of Patent:
December 11, 2018
Assignee:
SAFRAN AIRCRAFT ENGINES
Inventors:
Olivier Faye, Anthony Caron, Philippe Nomerange, Serge Legonidec
Abstract: An assistance device for a free-turbine engine of an aircraft having at least two free-turbine engines, the device including an electrical starter machine for providing prolonged assistance to the gas generator of a first engine using energy produced by an electric generator machine driven by the second engine, the device further including at least one electricity storage member electrically connected to the electrical starter machine for providing a burst of assistance to the gas generator, wherein the electrical starter machine is powered by a first power converter enabling it to exchange energy with the storage member for providing the burst of assistance, and that transmits thereto the energy supplied by a second power converter for the prolonged assistance.
Type:
Grant
Filed:
March 26, 2015
Date of Patent:
December 11, 2018
Assignee:
SAFRAN HELICOPTER ENGINES
Inventors:
Vincent Poumarede, Thomas Klonowski, Fabien Mercier-Calvairac, Camel Serghine
Abstract: Described is a modular linear actuator for use in an aerospace application, comprising: a piston housing having a closed end and an open end; a piston rod slideable within an interior of the piston housing between an extended position and a compressed position, the piston rod having a first end proximal to the closed end of the piston housing and a second end distal to the closed end of the piston housing; an attachment mechanism for removably attaching a lug end to the closed end of the piston housing, the lug end for attaching the actuator to a first component; an attachment mechanism for removably attaching a rod end to the second end of the piston rod, the rod end for attaching the piston rod to a second component; and, a piston head removably attached to the first end of the piston rod, the piston head for providing a snubbing engagement with the closed end of the piston housing.
Type:
Grant
Filed:
February 13, 2014
Date of Patent:
December 11, 2018
Assignee:
Safran Landing Systems Canada Inc./ Safran Systèmes d'Atterrissage Canada Inc.
Inventors:
Marin Besliu, Chris Bryant, Howard Smith
Abstract: A field of lost pattern casting, and more particularly to a casting tree for lost pattern casting, and also to its method of assembly is provided. The casting tree includes at least one part support, at least one pattern, and at least one first male-female connection connecting the pattern to the part support. The first male-female connection includes an orifice, a peg at least partially inserted inside the orifice, and a film of meltable material interposed at least between an outside surface of the peg and an inside surface of the orifice.
Abstract: A turbojet of the unducted rotor type and an aircraft including such a turbojet, the turbojet comprising a gas generator (3-8), a first unducted propeller (21) connected to a shaft (81) of the gas generator (3-8) via first reduction gearing (23), and a second unducted propeller (91) connected to a shaft (81) of the gas generator (3-8) via second reduction gearing (93), wherein the first propeller (21) and the first reduction gearing (23) are mounted at the front of the gas generator (3-8), and wherein the second propeller (91) and the second reduction gearing (93) are mounted at the rear of the gas generator (3-8).
Type:
Application
Filed:
May 31, 2018
Publication date:
December 6, 2018
Applicant:
SAFRAN AIRCRAFT ENGINES
Inventors:
Thomas Julien NGUYEN VAN, Olivier BELMONTE, Jeremy Phorla LAO, Clementine Charlotte Marie MOUTON, Emmanuel Pierre Dimitri PATSOURIS, Didier Jean-Louis YVON
Abstract: A method for manufacturing a component of an axial turbine engine includes the following steps: (a) providing or producing a component with a temporary surface; (b) placing the component in a chamber containing particles; and (c) vibratory peening of the temporary surface using the particles. The chamber includes an abrasive paste mixed with the particles so as to polish the surface of the component during the peening step (c). Thus, at the end of the peening step (c), the surface becomes a polished surface with a surface compression stress or prestress. The present application is notably applicable to a one-piece bladed drum of an aircraft turbojet engine low-pressure compressor.
Abstract: A permanent magnet synchronous machine includes a permanent magnet rotor and a three-phase stator, the machine being associated with a control inverter for controlling the stator of the machine. A method of controlling the machine includes taking three simultaneous measurements by three respective Hall effect sensors arranged to have a central sensor and two lateral sensors, the two lateral sensors being placed at 120°/p mechanical relative to the central sensor about the rotation axis of the rotor, where p is the number of pairs of poles of the machine; determining the position of the rotor based on the three measurements; controlling the control inverter as a function of the determined position of the rotor; and prior to controlling the inverter, applying a time delay to the three measurement signals so that the control of the control inverter takes account of a variable desired lag angle.
Abstract: A low-pressure compressor for a turbine engine, such as an aircraft turbojet engine includes a rotor with two rows of rotor blades between which two annular ribs are positioned; and one annular row of stator blades between the rotor blades. An internal shroud is connected to the stator blades. The internal shroud includes abradable material collaborating with the annular ribs, and annular teeth made of an abradable material and which extend radially towards the rotor, so as to provide sealing. The system may be used in a method for manufacturing a bypass turbojet engine compressor.
Abstract: The invention relates to an assembly comprising: a movable blade (100) for a turbomachine comprising a root (130), a removable part (300) comprising an anti-wear material, configured to be attached removably to an edge of the root (130) to limit wear of the root (130).
Type:
Application
Filed:
May 24, 2018
Publication date:
December 6, 2018
Applicant:
Safran Aircraft Engines
Inventors:
Vijeay PATEL, Pragash DOUGLAS, Quentin Bruno Guy Andre Emile LIEVOUX, Pauline NAMVONG
Abstract: A turbomachine including an accessory drive case, connected to the engine shaft via a radial shaft, wherein the accessory drive case also includes: a primary shaft which is driven by the radial shaft via a bevel gearbox, and assemblies for mechanically driving accessories, driven by the primary shaft and configured such that the related accessories lie at the upper portion and on at least one of the side edges of the engine case.
Abstract: A fiber blank woven as a single piece by three-dimensional weaving to make a closed box-structure platform out of composite material for a turbine engine fan. In each plane of the fiber blank, a set of warp yarns interlinks layers of weft yarns in first, second, and third portions of the fiber blank, while leaving a closed non-interlinked zone separating the first and second portions over a fraction of the dimension of the fiber blank in the warp direction between an upstream non-interlinking limit and a downstream non-interlinking limit, and while leaving at least one open non-interlinked zone separating the second and third portions over a fraction of the dimension of the fiber blank in the warp direction from a non-interlinking limit to a downstream edge of the fiber blank. A method of fabricating a preform for the closed box-structure platform can use such a fiber blank.
Type:
Grant
Filed:
April 17, 2013
Date of Patent:
December 4, 2018
Assignee:
SAFRAN AIRCRAFT ENGINES
Inventors:
Yann Marchal, Matthieu Gimat, Dominique Coupe, Bruno Dambrine
Abstract: A method for monitoring an aircraft thrust reverser having stowable doors, the thrust reverser being a reverser having hydraulic actuators equipped with switches arranged to each return a data item on the position of the doors, the engine including a computer configured to make measurements of a representative parameter of the position of the switches based on the data returned by the switches, includes computation of one or a plurality of statistical indicators of the parameter measured and an analysis of the temporal progression of the statistical indicator(s) computed. The invention also applies to a computer program for the implementation of this method.
Abstract: A stator vane for a turbine machine includes a set of vane parts arranged relative to each other to define air flow stream paths between vane parts, and a mechanism circulating a fluid to be cooled by the air flow.