Patents Assigned to Turbomeca
  • Compressor impeller blade with variable elliptic connection
    Patent number: 8721287
    Abstract: A compressor impeller including at least one blade connected to an impeller hub via a junction of curved shape, the blade extending along a defined chord between a leading edge and a trailing edge of the blade. The junction presents the shape of an ellipse that varies along the chord.
    Type: Grant
    Filed: May 14, 2009
    Date of Patent: May 13, 2014
    Assignee: Turbomeca
    Inventors: Geoffroy Louis-Henri Marie Billotey, Pierre Biscay, Gilles Cazenave-Larroche, Jean-Philippe Ousty
  • Turbine wheel with an axial retention system for vanes
    Patent number: 8721293
    Abstract: A turbine wheel includes: a plurality of blades, a rotor including a disk having the blades mounted at a periphery thereof, each blade including an airfoil with a foot secured to a platform carrying an attachment member engaged in a housing that opens into the periphery of the disk and that extends axially between two opposite side faces of the disk, the housings being spaced apart from one another by portions of the disk that form teeth, and an axial retention plate retaining the blades on the disk and including a retention plate situated on one side of the disk.
    Type: Grant
    Filed: December 16, 2009
    Date of Patent: May 13, 2014
    Assignee: Turbomeca
    Inventors: Jean-Baptiste Arilla, Michel Beaucoueste, Denis Chanteloup, Michel Clastre
  • Compressor cover for turbine engine having axial abutment
    Patent number: 8721261
    Abstract: A centrifugal compressor for a turbine engine, including a cover with an upstream end and a downstream end; a casing presenting an upstream edge and a downstream edge; and a bladed impeller mounted to rotate in the casing. The cover covers the blades of the impeller to define an outside surface of a gas-flow passage extending between the upstream and downstream edges of the casing, while being fastened to the upstream edge of the casing via its upstream end while its downstream end remains free. The cover further includes an abutment limiting axial movement of its downstream end relative to the downstream edge of the casing while the compressor is in operation.
    Type: Grant
    Filed: May 20, 2009
    Date of Patent: May 13, 2014
    Assignee: Turbomeca
    Inventors: Philippe Denis Joubert, Patrice Laborde, Yann Mouze, Philippe Perot
  • AIR CONDITIONING SYSTEM FOR AN AIRCRAFT PASSENGER COMPARTMENT
    Publication number: 20140124160
    Abstract: An air conditioning system for an aircraft passenger compartment, the system including: an air supply circuit connecting at least one external air inlet to at least one air distribution outlet which opens into the compartment, an auxiliary power unit mounted in the supply circuit and configured to compress an air stream in the supply circuit, the supply circuit including a heating first branch that connects the auxiliary power unit to the air distribution outlet, and in which a heating mechanism is mounted, a cooling second branch that connects the auxiliary power unit to the air distribution outlet, and a switching mechanism configured to distribute the air stream between the heating first branch and the cooling second branch.
    Type: Application
    Filed: May 29, 2012
    Publication date: May 8, 2014
    Applicant: TURBOMECA
    Inventors: Laurent Houssaye, Laurent Minel
  • CENTRIFUGAL COMPRESSOR IMPELLER
    Publication number: 20140127023
    Abstract: An impeller of a centrifugal compressor, the impeller including a web and blades secured to the web on a front face of the web. A point of intersection between a trailing edge and a blade root is at least one half-thickness of the web further forward than the blade root at an intermediate diameter of the impeller, and a point of intersection between the trailing edge and the blade tip is also further forward than the blade tip at an intermediate diameter of the impeller.
    Type: Application
    Filed: May 14, 2012
    Publication date: May 8, 2014
    Applicant: TURBOMECA
    Inventors: Mathieu Herran, Laurent Pierre Tarnowski
  • A METHOD OF STARTING A TURBOMACHINE WHILE REDUCING THERMAL UNBALANCE
    Publication number: 20140123673
    Abstract: A method of starting a turbomachine, performed by an electronic unit, the turbomachine including a gas turbine engine including at least one rotor and a starter to drive the rotor in rotation, the method including: receiving an order to start the turbomachine, and executing in response to receiving the order to start: a primary acceleration during which the starter is operated to increase speed of rotation of the rotor; a thermal homogenization during which the starter is operated to keep the speed of rotation of the rotor constant or to decrease it until a predetermined condition is satisfied; after the predetermined condition is true, a secondary acceleration in which the starter is operated to increase the speed of rotation of the rotor; and an ignition in which ignition of the engine is ordered.
    Type: Application
    Filed: June 29, 2012
    Publication date: May 8, 2014
    Applicant: TURBOMECA
    Inventors: Yann Mouze, Frederic Ferdinand Jacques Batlle, Edgar Haehner, Frederic Segura
  • METHOD FOR INJECTING FUEL INTO A COMBUSTION CHAMBER OF A GAS TURBINE, AND INJECTION SYSTEM FOR IMPLEMENTING SAME
    Publication number: 20140116384
    Abstract: An air/fuel mixer system of a combustion chamber of a gas turbine includes at least one compressed air intake swirler, the swirler having a central axis of symmetry, and a fuel injector including an injection head having an axis of symmetry. Each injector is mounted in the corresponding swirler with aid of a guide mechanism, so that the axis of symmetry of the injection head is off-center with respect to the central axis of symmetry of the swirler. The system can reduce, or even eliminate, combustion instabilities, by injecting the fuel along a particular axis which is off-center relative to the axis of the air/fuel mixer system, inducing a flow of fuel which is no longer perfectly axially symmetrical.
    Type: Application
    Filed: June 19, 2012
    Publication date: May 1, 2014
    Applicant: TURBOMECA
    Inventors: Nicolas Savary, Claude Berat, Hubert Hippolyte Vignau, Christophe Nicolas Henri Viguier
  • ANNULAR COMBUSTION CHAMBER OF A TURBOMACHINE
    Publication number: 20140109595
    Abstract: An annular combustion chamber for a turbomachine presenting an axial direction, a radial direction, and an azimuth direction, the combustion chamber including a first annular wall and a second annular wall, each annular wall defining at least a portion of an enclosure of the combustion chamber. The first annular wall and the second annular wall present complementary assembly mechanisms that co-operate by engagement in azimuth.
    Type: Application
    Filed: June 4, 2012
    Publication date: April 24, 2014
    Applicant: TURBOMECA
    Inventors: Bernard Carrere, Nicolas Savary
  • A TWO-SPOOL DESIGN FOR A TURBOSHAFT ENGINE WITH A HIGH-PRESSURE COMPRESSOR CONNECTED TO A LOW-PRESSURE TURBINE
    Publication number: 20140112756
    Abstract: A turboshaft engine including a low-pressure compressor, a high-pressure compressor, a low-pressure turbine, a high-pressure turbine, and a regulator for regulating a speed of rotation of the low-pressure turbine to a speed that is substantially constant. The low-pressure turbine is coupled by a first shaft to the high-pressure compressor, while the high-pressure turbine is coupled by a second shaft to the low-pressure compressor.
    Type: Application
    Filed: June 7, 2012
    Publication date: April 24, 2014
    Applicant: TURBOMECA
    Inventor: Remy Princivalle
  • Gas-guiding pipe comprising a noise-attenuating covering with variable porosity
    Patent number: 8701822
    Abstract: A noise-attenuating covering configured for example for a pipe for guiding gases along a gas path. The covering includes a wall defining the gas path and at least one resonance cavity, the wall being pierced with holes for fluid communication between the gas path and the resonance cavity to attenuate noise. The holes have substantially identical diameters and, since the pipe is arranged to guide the gases in the downstream direction, a number of the openings per wall surface unit decreases continuously along the gas path in the downstream direction, such as to confer on the wall substantially constant acoustic resistance along the gas path, for which the noise attenuation is optimized along the gas path.
    Type: Grant
    Filed: February 11, 2011
    Date of Patent: April 22, 2014
    Assignee: Turbomeca
    Inventors: Eric Jean-Louis Bouty, Pierre-Luc Regaud, Antoine Yvan Alexandre Vallon
  • GAS TURBINE DIFFUSER BLOWING METHOD AND CORRESPONDING DIFFUSER
    Publication number: 20140105723
    Abstract: A diffuser of a compressor of centrifugal or mixed type includes two end plates which enclose a plurality of regularly distributed circumferential blades, and at least one transverse upstream passage produced in lower or upper surfaces of the blades. An injection/withdrawal coupling is achieved by a recirculation of a stream in an air passage of the diffuser on the basis of injection of air from at least one point in a leading edge zone of an upstream side of the diffuser. Blowing of air is then effected in at least one groove formed along a lateral flank of each blade by withdrawal of the air stream in a region of a trailing edge. Thereby, effectively separation of the air in a boundary layer in a gas turbine compressor diffuser is realized by re-energizing the boundary layer with air at a higher pressure by a suction/re-injection coupling.
    Type: Application
    Filed: May 15, 2012
    Publication date: April 17, 2014
    Applicant: TURBOMECA
    Inventors: Jérôme Yves Félix Gilbert Porodo, Laurent Pierre Tarnowski
  • Device for filtering the intake air of an internal combustion engine having ventilation means
    Patent number: 8685126
    Abstract: A device for filtering intake air of an internal combustion engine, including at least one filtering element including an inlet for air being treated, a first clean air outlet toward the engine, and a second air outlet toward the outside, and a ventilation mechanism driving the air from the second air outlet. The ventilation mechanism includes a fan wheel driven by a turbine set into motion by a gas flow taken from the engine.
    Type: Grant
    Filed: October 14, 2010
    Date of Patent: April 1, 2014
    Assignee: Turbomeca
    Inventor: Olivier Pierre Descubes
  • METHOD FOR RATIONALISING A CHAIN OF ELECTRICAL COMPONENTS OF AN AIRCRAFT, IMPLEMENTATION ARCHITECTURE AND CORRESPONDING AIRCRAFT
    Publication number: 20140084677
    Abstract: A chain of components for transmitting electric power of an aircraft includes an auxiliary power unit (APU), main engines and end consumer systems via power networks and electronic connections controlled by a unit. The APU supplies power to a shaft by a connection to at least one energy converter unit, via a transmission unit, each converter unit comprising only one convertible electromechanical component. The transmission of power is effected by a direct connection to the transmission unit and to the end consumer system. The connection between a converter unit and the APU is provided by connecting the shaft of the APU to the shaft of the starter/generator (SG) via a directional transmission of power operating in one direction only from the shaft of the APU to the shaft of the SG.
    Type: Application
    Filed: May 15, 2012
    Publication date: March 27, 2014
    Applicant: TURBOMECA
    Inventor: Jean-Michel Haillot
  • METHOD AND DEVICE FOR SUPPLYING A LUBRICANT
    Publication number: 20140075916
    Abstract: A device and method feeding turbomachines with lubricant, the turbomachine including a first set of bearings and a second set of bearings. Both the first and the second sets of bearings are fed with lubricant, and the second set of bearings operate at a temperature higher than the first set. The second set of bearings is fed with lubricant at a temperature higher than the first set.
    Type: Application
    Filed: January 10, 2012
    Publication date: March 20, 2014
    Applicant: Turbomeca
    Inventor: Philippe Alain François Augros
  • Turbine engine including a reversible electric machine
    Patent number: 8657566
    Abstract: A turbine engine, for example for a helicopter, the engine including a gas generator and a free turbine driven in rotation by a gas stream generated by the gas generator, the turbine engine further including a reversible electric machine for coupling to the gas generator, the reversible electric machine configured to set the gas generator into rotation during a stage of starting the turbine engine. To generate electricity, the reversible electric machine is also configured to be coupled to the free turbine after the turbine engine has started.
    Type: Grant
    Filed: March 24, 2009
    Date of Patent: February 25, 2014
    Assignee: Turbomeca
    Inventors: Olivier Bedrine, Monique Fos, Jean-Luc Frealle, Gerald Senger
  • MECHANICAL PROTECTION DEVICE
    Publication number: 20140045599
    Abstract: A mechanical protection device including: a transmission shaft having a main axis of rotation and an element that is frangible under a torsional overload; a movable member secured to the transmission shaft to rotate about the main axis and configured to move radially outwards relative to the main axis from a first position to a second position; a spring urging the movable member towards the first position; and a tangential abutment configured to stop rotation of the movable member about the main axis when the movable member is in the second position. The movable member and the spring are calibrated so that from a predetermined trigger angular speed the movable member moves from the first position to the second position under effect of centrifugal force greater than prestress of the spring.
    Type: Application
    Filed: April 12, 2012
    Publication date: February 13, 2014
    Applicant: TURBOMECA
    Inventors: Olivier Pierre Descubes, Olivier Bedrine, Isabelle Germaine, Claude Ladeveze, Jean-Michel Pierre, Claude Py
  • Hollow turbine wheel vane comprising a rib and associated wheel and turbomachine
    Patent number: 8647071
    Abstract: A turbine blade extends radially between a blade root and a blade tip having an open cavity referred to as a bathtub formed therein, which cavity is defined by a closed end wall and a side rim. The side rim of the cavity carries at least one rib extending between a leading edge and a trailing edge of the blade.
    Type: Grant
    Filed: July 21, 2009
    Date of Patent: February 11, 2014
    Assignee: Turbomeca
    Inventors: Lorenzo Pons, Laurence Vial
  • Diffuser having blades with apertures
    Patent number: 8641373
    Abstract: A diffuser for a mixed flow or centrifugal compressor of a gas turbine. The diffuser includes at least one vane presenting a pressure side, a suction side, and a first flank. The vane includes a plurality of orifices opening out into the suction side and/or the pressure side and communicating with at least one cavity formed in the vane, the cavity extending transversely relative to the vane and opening out into its first flank. The cross section of the cavity varies in the transverse direction of the vane, the cross section increasing towards the first flank.
    Type: Grant
    Filed: October 15, 2009
    Date of Patent: February 4, 2014
    Assignee: Turbomeca
    Inventors: Jérôme Porodo, Laurent Tarnowski, Hubert Vignau
  • TURBOMACHINE COMPRISING A PRIVILEGED INJECTION DEVICE AND CORRESPONDING INJECTION METHOD
    Publication number: 20140000276
    Abstract: A turbomachine including: a combustion chamber, with a fuel injection device in the combustion chamber; a supply mechanism supplying fuel to the fuel injection device; a mechanism determining instantaneous variation of fuel flow rate of the supply mechanism; and a regulation mechanism regulating the fuel flow rate of the injection device according to the instantaneous variation of the fuel flow rate of the supply mechanism determined by the determination mechanism.
    Type: Application
    Filed: February 17, 2012
    Publication date: January 2, 2014
    Applicant: TURBOMECA
    Inventors: Eric Royer, Philippe Jean, Rene, Marie Benezech, Pascal Rupert
  • METHOD FOR CALIBRATING A TORSION TORQUEMETER
    Publication number: 20130327119
    Abstract: A method for calibrating a torsion torquemeter including: placing a torsion torquemeter in a first state; performing first measurements determining first and second angular offsets, and measuring torque output by the power shaft using a reference torquemeter; placing the torsion torquemeter in a second state; performing second measurements determining the first and second angular offsets, and measuring torque output by the power shaft; placing the torquemeter in a third state; performing third measurements determining the first and second angular offsets, and measuring the torque output by the power shaft; placing the torquemeter in a fourth state; performing fourth measurements determining the first and second angular offsets, and measuring the torque output by the power shaft; calibrating the calculation unit based on the first, second, third, and fourth measurements.
    Type: Application
    Filed: February 23, 2012
    Publication date: December 12, 2013
    Applicant: TURBOMECA
    Inventor: Edgar Haehner