Abstract: A turbine engine rotor shaft includes at least one portion having an outer periphery having a determined diameter forming a free surface for heat exchange with the environment of said rotor. The outer periphery includes a plurality of irregularities which are designed to provide a heat exchange surface of the shaft of the rotor which is greater than a surface of the periphery of a cylinder having the same determined average diameter.
Abstract: A method for monitoring an aircraft engine during flight, which includes the steps of: for at least one characteristic frequency of the operation of the engine, measuring at least one synchronous vibration level value; for at least one module of the engine, estimating an out-of-balance value of the module in accordance with the one or more vibration level values measured and at least one sensitivity coefficient; estimating a balancing margin of the module in accordance with the out-of-balance value of said module and a maximum threshold; (d) estimating a remaining number of flights of the aircraft prior to balancing and/or a quality indicator of a preceding balancing operation in accordance with the one or more estimated balancing margins and data representing past balancing operations of the engine.
Type:
Grant
Filed:
May 4, 2016
Date of Patent:
May 14, 2019
Assignee:
Safran Aircraft Engines
Inventors:
Josselin Coupard, Ronan Louis Castrec, Rafik Zouari
Abstract: The invention relates to a method for connecting in rotation an output member (5) of an electric motor (1) and an element (2) that is to be driven in rotation, comprising the use of at least one fusible pin (11) that links the output member and the element that is to be driven, and that has at least one section that is prone to fail in shear when a torque transmitted by the fusible pin exceeds a predetermined threshold. The method comprises the step of interposing, between the pin and either the output member or the element that is to be driven, at least one elastic member (20) comprising a first travel with a first stiffness followed by a second travel with a second stiffness greater than the first stiffness.
Type:
Grant
Filed:
August 24, 2017
Date of Patent:
May 14, 2019
Assignee:
SAFRAN LANDING SYSTEMS
Inventors:
Sylvain Jaber, Vincent Bellenger, Nicolas Moretti, Gilles Eluard
Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
Type:
Grant
Filed:
December 29, 2016
Date of Patent:
May 14, 2019
Assignee:
SAFRAN AIRCRAFT ENGINES
Inventors:
Daniel Marius Man, Maxime Didier Delabriere, Pierre Hervé Marche, Pascal Pierre Routier
Abstract: An aircraft landing gear which includes a noise-inducing region and a cover. The cover comprises a cover portion arranged to enclose the noise-inducing region to inhibit an airflow negotiating the noise-inducing region when the landing gear is in use.
Type:
Grant
Filed:
March 21, 2013
Date of Patent:
May 14, 2019
Assignee:
SAFRAN LANDING SYSTEMS UK LTD
Inventors:
Stuart Lacy, Geoff Cumner, Peter Michaelides
Abstract: The present invention relates to a method for guiding an aircraft over an airport taxiway which is carried out by a data-processing device of a guiding system, wherein said method comprises the steps of determining (E1) at least one possible future path of the aircraft according to the topography of the taxiway in the vicinity of the aircraft, receiving (E2) at least one command relating to the path for the aircraft to follow, selecting (E3) a path to follow from said possible future paths that have been determined and, on the basis of said received command, guiding (E4) the aircraft along the selected path to follow.
Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
Type:
Grant
Filed:
December 29, 2016
Date of Patent:
May 14, 2019
Assignee:
SAFRAN AIRCRAFT ENGINES
Inventors:
Erwan Daniel Botrel, Maxime Didier Delabriere, Daniel Marius Man, Pierre Hervé Marche
Abstract: The invention relates to a method for the tamper-evident and traceable marking of an assembly of a first element and a second element, the marking method comprising steps of assembling the first element and the second element, placing a radio tag marker on a first surface of the first element, the first surface being facing a second surface of the second element, and applying a first layer of locking varnish to a third surface, the third surface comprising the first surface and the second surface, in order to cover the marker, the first layer of locking varnish, once dried, guaranteeing that the marking is tamper-evident and the radio tag marker affording tracing of the marking.
Abstract: A spool for a fuel circuit valve of an aircraft engine, extending along a longitudinal axis and including a narrowed intermediate section extending between two end cylindrical sections, a first end section being separated from the narrowed intermediate section by a shoulder having a surface arranged overall perpendicular to the longitudinal axis, the narrowed intermediate section also including, extending away from the shoulder, at least one cylindrical portion, and the shoulder is provided with a step extending away from the cylindrical surface of the first end section which, when the fuel flows along the first end section towards the narrowed intermediate section and the second end portion, generates a jet of fuel on the cylindrical portion of the narrowed intermediate section, a recirculation of fuel forming in an area in front of the shoulder.
Abstract: A ground testing device for a turbomachine, including an aircraft engine (12) extending axially from an air inlet to a nozzle, a shroud (20) having an axis of revolution (A) and surrounding at least partially the engine (12) so as to create an annular air flow between the engine (12) and the shroud (20) when the engine (12) is in operation, and a framework (22) allowing the shroud (20) to be supported.
Type:
Application
Filed:
November 8, 2018
Publication date:
May 9, 2019
Applicant:
SAFRAN AIRCRAFT ENGINES
Inventors:
Laurent Louis Robert BAUDOIN, Josselin David Florian Regnard
Abstract: Disclosed is a thrust reverser for a device receiving a propulsion element, such as a turbojet engine nacelle. The thrust reverser includes a stationary structure having a deflector deflecting at least a portion of the air flow that is to flow through the nacelle, a translatably movable cap that can be in a closed position in which the cap covers the deflector deflecting the air flow and an open position in which the cap opens the deflector deflecting the air flow, and at least one moving actuator configured to move the cap between the open and closed positions. The moving actuator includes a stationary portion designed to be attached to the stationary structure in a first securing position and a movable portion designed to be attached to the cap in a second securing position. An adjusting device adjusts the first securing position.
Abstract: A constant-volume combustion chamber for an aircraft turbine engine, including a compressed gas intake valve configured to adopt an open position and a closed position, and in the closed position blocking intake of compressed gas into the chamber, and a combusted gas exhaust valve configured to adopt a closed position, in the closed position blocking exhaust of combusted gas outside the chamber. At least one of the intake and exhaust valves includes at least one spherical plug.
Abstract: A slide for a fuel circuit valve of an aircraft engine extending along a longitudinal axis, and comprising a narrowed intermediate portion extending between two cylindrical end portions, a first end portion being separated from the narrowed intermediate portion by a shoulder having a surface arranged overall perpendicular to the longitudinal axis, the narrowed intermediate portion including in turn, as an extension of the shoulder, at least one cylindrical portion, the shoulder comprising at least one groove which extends radially from the cylindrical surface of the first end portion, towards the longitudinal axis, and which forms a fuel recirculation area which provides the generation of a jet of fuel on the cylindrical portion of the narrowed intermediate portion, when fuel flows along the first end portion towards the narrowed intermediate portion and the second end portion.
Abstract: To facilitate the removal of a bearing housed in an arm of a turbomachine casing, which bearing guides a transmission shaft of the turbomachine, a casing arm includes a body with a vertical portion and a base defining a portion of a shaft housing; an additional part removably attached to the body and defining a bearing housing opening in the shaft housing; and a removable shim inserted between the base and the additional part. A turbomachine including such a casing arm is also described, as well as a method for removing the bearing from such a turbomachine, including removing the shim and moving the additional part towards the base, thereby allowing access to the bearing.
Type:
Application
Filed:
April 27, 2017
Publication date:
May 9, 2019
Applicant:
SAFRAN AIRCRAFT ENGINES
Inventors:
Sebastien Nicolas JUIGNE, Kevin Michel Robert CONTAL, Mathieu GAILLOT, Francois Marie Paul MARLIN, Steve Marcel NICAISE
Abstract: The invention relates to an aircraft flight control column device (1) comprising: a casing (2) for attaching to an aircraft structure; an output shaft (3) for connecting to a flight control column (56), the output shaft (3) being mounted such that it rotates in relation to the casing (2); a primary group (4) comprising a first torque-generating body (7, 8) for applying a first torque to the output shaft (3); a secondary group (5) comprising a second torque-generating body (7, 8) for applying a second torque to the output shaft (3); and a clutch for selectively connecting the primary group (4) and the secondary group (5) to the output shaft (3).
Abstract: A method and a system for the vibration analysis of an engine, including acquiring vibration signals relating to the engine and in order to form at least one spectrogram that represents an operating state of the engine, selecting at least one zone of interest in at least one spectrogram, comparing each zone of interest with a set of corresponding comparison zones belonging to annotated spectrograms recorded in a reference database, and determining a subset of comparison zones that have vibration behaviors similar to those of the zone of interest, and displaying the subset of comparison zones and annotations associated with the subset of comparison zones.
Abstract: A device for recovering oil injected by centrifugal effect in a turbine engine, comprising a substantially circular ring around an axis, the ring comprising a first part forming a basin surrounding the axis and having an opening turned radially inward, so as to recover the oil injected radially across from the opening, and a second part forming a substantially toroidal chamber, radially open outward at a low point, so as to allow oil to escape, a passage being arranged between the basin and the chamber substantially over the entire circumference around the axis so as to cause the oil recovered by the basin to enter the chamber, wherein a rim is arranged between a radially inner bottom of the chamber and the passage, so as to contain the oil accumulating in this radially inner bottom of the chamber, and in some embodiments, at a high point.
Type:
Grant
Filed:
June 9, 2017
Date of Patent:
May 7, 2019
Assignee:
SAFRAN AIRCRAFT ENGINES
Inventors:
Jérémy Phorla Lao, Olivier Belmonte, Clémentine Charlotte Marie Mouton
Abstract: A device for guiding variable pitch stator vanes of a turbine engine is provided. The device includes a plurality of inner ring angular sectors arranged end-to-end in order to form an inner ring, each inner ring sector having chimneys passing radially through the inner ring sector, a plurality of cylindrical bushings, each being put into place in a chimney of the inner ring from the inside and each serving to receive a guide pivot of a stator vane, a plurality of reconstitution ring angular sectors arranged end-to-end in order to form a reconstitution ring and put into place radially from the inside against the inner ring, and a plurality of blocking elements passing axially through the inner and reconstitution rings in order to assemble the rings together.
Type:
Grant
Filed:
November 19, 2014
Date of Patent:
May 7, 2019
Assignee:
SAFRAN AIRCRAFT ENGINES
Inventors:
Clementine Charlotte Marie Mouton, Olivier Belmonte
Abstract: Passenger seat armrests and consoles have laterally translating armrest doors that open and close to allow for deployment and stowage of tray tables. The armrest doors may be guided through their translation by slides or a linkage that controls their motion. The armrest doors may also translate in two-dimensions, incorporating a vertical translation as well as a lateral translation. The resulting motion allows for better placement of the deployable tray tables within the armrest or console and a reduction in wasted space. The passenger seat armrests may also incorporate cocktail trays that can be integrated into the armrest doors or the armrest or console itself.
Type:
Grant
Filed:
April 2, 2015
Date of Patent:
May 7, 2019
Assignee:
Safran Seats USA LLC
Inventors:
Marc W. Kinard, Ty Parker, Raul G. Reyes, John D. Allen
Abstract: A hydraulic ram comprising a fixed support, a cylinder that is movable in translation relative to the support, a piston secured inside the cylinder delimiting two chambers with the cylinder and a device for supplying the chambers with hydraulic fluid upstream from the fixed support. The ram is characterized by the fact that the supply device comprises telescopic channels, each telescopic channel comprising two tubular elements sliding one into the other, a first tubular element being rigidly connected to the fixed support at one end and the second tubular element being rigidly connected to the cylinder at at least two points separated from each other along a generatrix of the cylinder. The invention is applicable to controlling the pitch of the blades of a turbine engine propeller.