Patents by Inventor Alain Porte

Alain Porte has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Patent number: 11073081
    Abstract: An aircraft engine air inlet lip takes an annular form about a longitudinal axis and delimits an air inlet stream, and includes: a wall having a U-shaped profile having an outer face oriented towards outside of the air inlet lip and an inner face oriented towards interior of the air inlet lip, an inner wall extending inside the wall between two zones of the inner face, so as to close an inner chamber delimited between the wall and the inner wall and filled with a gas, the inner wall having an upstream face oriented towards and a downstream face oriented away from the inner chamber, a fan configured to move the gas contained in the inner chamber, and at least one pipeline fixed to the upstream face and extending all around the air inlet lip and configured to be fed with a heat transfer fluid heated by a heat source.
    Type: Grant
    Filed: September 28, 2018
    Date of Patent: July 27, 2021
    Inventors: Alain Porte, Vincent Rebeyrotte, Gregory Albet, Jonathan Carcone
  • Patent number: 11066994
    Abstract: An assembly including two juxtaposed acoustic panels. Resistive faces of the acoustic panels are in the continuation of one another. A first resistive face extends as far as the first end wall of a first panel. The first end wall is in contact with a second end wall of a second panel in the region of the first resistive face and of the second resistive face. A connecting piece is interposed between the first end wall and the second end wall over a part of the length thereof so that the connecting piece does not extend as far as the first and second resistive faces. That makes it possible to form an acoustic cladding that is continuous, exhibiting no non-acoustic zone or reduced-acoustic zone at the junction between the acoustic panels of which it is formed. A nacelle of an aircraft propulsion unit is one application.
    Type: Grant
    Filed: September 27, 2019
    Date of Patent: July 20, 2021
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Alain Porte, Jacques Lalane, François Pons
  • Patent number: 11027817
    Abstract: An acoustic treatment panel including a porous acoustically resistive structure which includes at least one external layer which is in contact with the external environment and which has through holes, internal strips including several openings which communicate with the inside of the cells of the panel and connecting canals, interposed between the external layer and the internal strips, which ensure that the floor-section openings communicate with at least one through hole of the external layer.
    Type: Grant
    Filed: April 24, 2018
    Date of Patent: June 8, 2021
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Alain Porte, Jacques Lalane, Maud Lavieille
  • Publication number: 20210107670
    Abstract: An anterior part of a nacelle of a propulsion assembly of an aircraft, having an air intake lip and a front frame disposed at the rear of the air intake lip that connects an outer part to an inner part of the air intake lip. A de-icing duct is formed in front of the front frame. The front frame is shaped so that the de-icing duct has a main cavity and a thermal transition region formed behind the main cavity between an internal face of the outer part of the air intake lip and the front frame. The thermal transition region extends over a longitudinal dimension greater than its average radial dimension, the front frame forming, with respect to the internal face of the outer part of the air intake lip, an angle, measured longitudinally, of between ?20° and +10° over the majority of the thermal transition region.
    Type: Application
    Filed: August 11, 2020
    Publication date: April 15, 2021
    Inventors: Alain PORTE, Frédéric VINCHES
  • Publication number: 20210107669
    Abstract: An anterior part of a nacelle of an aircraft propulsion assembly, which comprises an air intake lip, an outer panel extending an outer part of the air intake lip, an inner structure extending an inner part of the air intake lip, a front frame connecting the outer wall to the air intake lip or to the inner structure. The outer panel and the outer part of the air intake lip together form an outer wall of the anterior part. The front frame and the outer wall are connected to one another by assembly means located inside the anterior part. The anterior part constituted in this manner ensures laminar flow of the air on an outer surface of the anterior part and reduces drag. A nacelle of a propulsion unit, comprising an anterior part of this kind is also provided.
    Type: Application
    Filed: August 11, 2020
    Publication date: April 15, 2021
    Inventors: Alain PORTE, Jacques LALANE, Frédéric VINCHES, Gregory ALBET
  • Publication number: 20210107666
    Abstract: An anterior part of an aircraft propulsion assembly nacelle, having an air intake lip disposed at a front end and an outer panel, of which an outer face extends an outer part of the air intake lip. A front edge of the outer panel and a rear edge of the air intake lip are shaped so as to overlap radially and to nest so as to ensure a continuous surface between the outer surface of the outer part of the air intake lip and the outer face of the outer panel. Moreover, the front edge of the outer panel is connected to the rear edge of the air intake lip with no added rigid element. This permits a rigid connection while avoiding creating local irregularities on the outer surface of the nacelle, which irregularities might disrupt the flow of air around the nacelle, giving rise to additional drag.
    Type: Application
    Filed: August 11, 2020
    Publication date: April 15, 2021
    Inventors: Alain PORTE, Jacques LALANE, Frédéric VINCHES, Franck DOBIGEON
  • Publication number: 20210078717
    Abstract: An acoustic panel for an aircraft nacelle air intake comprising a resistive skin perforated by noise absorption holes and a core against which the resistive skin extends, wherein the resistive skin has a smooth visible face and a castellated rear face with alternating ribs and grooves. The noise absorption holes are formed exclusively in the grooves, i.e., in a zone where the skin is less thick, which enables the holes to have a diameter that is both greater than the thickness of the skin and small enough not to have any impact on drag. The mechanical strength of the resistive skin provided by the ribs ensures that the lesser thickness of the resistive skin in the grooves does not render the resistive skin overly flexible.
    Type: Application
    Filed: September 10, 2020
    Publication date: March 18, 2021
    Inventors: Alain PORTE, Jacques LALANE, Benoit PRZYBYLA, Thierry COLCOMBET, Franck COLCOMBET
  • Patent number: 10940935
    Abstract: An acoustic treatment panel in which each cell includes a plurality of conduits which extend from the porous acoustically resistive structure to the reflective layer of the acoustic treatment panel, each conduit including at least one opening set away from the porous acoustically resistive structure and configured to cause the inside and the outside of the conduit to communicate.
    Type: Grant
    Filed: April 24, 2018
    Date of Patent: March 9, 2021
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Alain Porte, Jacques Lalane, Maud Lavieille
  • Publication number: 20210040867
    Abstract: An anterior part of a nacelle of an aircraft propulsion unit. A rigidifying frame annular about a longitudinal axis of extension of the nacelle is at the rear end of the anterior part. An annular shield is in front of the rigidifying frame and connects an internal peripheral edge of the rigidifying frame to an internal structure. The shield has a portion extending towards the external panel beyond the internal peripheral edge of the rigidifying frame, the portion forming a non-zero angle with respect to the rigidifying frame to form a free space with respect to the rigidifying frame behind the portion. The shield can thus deform in the event of an impact of a foreign object entering through the air inlet lip, without the rigidifying frame itself being deformed, thereby absorbing all or some of the impact energy. A nacelle can have such an anterior part, and an aircraft can have such a nacelle.
    Type: Application
    Filed: August 5, 2020
    Publication date: February 11, 2021
    Inventors: Alain Porte, Julien Sentier, Clément Breton
  • Patent number: 10836503
    Abstract: An aircraft nacelle air intake structure including an air intake lip with a U-shaped section to ensure air is shared between an inner face and an outer face. An acoustic panel is on the intake lip rear on the side of the inner face level with a first assembly point. An outer panel is on the intake lip rear on the side of the outer face level with a second assembly point. A front reinforcing frame on the intake lip inside is fixed to the air intake lip on the side of the inner face level with a first fixing point and on the side of the outer face level with a second fixing point. The length of the chord between the stop point and each fixing point is between ? and ? of the total chord between the stop point and the assembly point.
    Type: Grant
    Filed: December 19, 2017
    Date of Patent: November 17, 2020
    Assignees: Airbus Operations (S.A.S.), Airbus (S.A.S.)
    Inventors: Alain Porte, Eric Haramburu, Patrick Oberle, Grégory Albet, Vincent Billerot, Frédéric Piard, Franck Oundjian
  • Patent number: 10676203
    Abstract: An air input structure includes an air input lip and a front reinforcement frame placed inside the air input lip. The front part of the air input lip has a plurality of segments distributed angularly along the leading edge of the air input lip, two adjacent segments being separated by an intermediate part having an excess thickness. Each segment has four edges, each having an excess thickness relative to the rest of the segment.
    Type: Grant
    Filed: December 7, 2017
    Date of Patent: June 9, 2020
    Assignees: Airbus Operations S.A.S., AIRBUS SAS
    Inventors: Alain Porte, Patrick Oberle, Gregory Albet
  • Patent number: 10655563
    Abstract: A nacelle has a fixed cowl and a mobile cowl, which is movable along a translation path between closing and opening positions, a window delimited by the fixed cowl and the mobile cowl and open between an airflow and exterior of the nacelle, a reverser flap rotatably mounted to move between closed and open positions, and a drive mechanism configured to control passage of the reverser flap between the closed and open positions as the mobile cowl moves between the closed and open positions. From the closing/closed positions, the drive mechanism assures a translation of the mobile cowl and a rotation of the reverser flap toward their respective opening/open positions. From the open/opening positions, the drive mechanism assures a rotation of the reverser flap and a translation of the mobile cowl toward their respective closed/closing position. In some embodiments, the nacelle further includes an additional, or second, flap.
    Type: Grant
    Filed: November 27, 2017
    Date of Patent: May 19, 2020
    Assignees: Airbus Operations (S.A.S.), Airbus (S.A.S.)
    Inventors: Thierry Surply, Alain Porte, Patrick Oberle, Eric Haramburu, Thomas Sauvalle, Benoit Letay, Frédéric Piard, Vincent Billerot, Franck Oundjian
  • Publication number: 20200122843
    Abstract: An anti-icing protection system for an aircraft engine nacelle, the nacelle comprising an inner shroud provided with at least one acoustic panel, an air intake lip forming a leading edge of the nacelle, the protection system comprising a heat exchanger device including at least one heat pipe configured to transfer heat emitted by a heat source to the acoustic panel or panels.
    Type: Application
    Filed: October 17, 2019
    Publication date: April 23, 2020
    Inventors: Alain PORTE, Jacques LALANE, Gregory ALBET, Maxime ZEBIAN, Arnaud BOURHIS
  • Publication number: 20200122844
    Abstract: An anti-icing protection system for an aircraft engine nacelle, the nacelle comprising an inner shroud, an air intake lip forming a leading edge of the nacelle, the protection system comprising a heat exchanger device including at least one heat pipe configured to transfer heat emitted by a heat source to the inner shroud.
    Type: Application
    Filed: October 17, 2019
    Publication date: April 23, 2020
    Inventors: Alain PORTE, François PONS, Gregory ALBET, Maxime ZEBIAN
  • Publication number: 20200122851
    Abstract: A forward part of an aircraft propulsion unit nacelle, comprising an air intake lip, an acoustic panel, and a rigid connection between the acoustic panel and the air intake lip. The acoustic panel has a resistive surface and a back skin, and the rigid connection is formed between the air intake lip and the back skin of the acoustic panel to form a propagation path for forces between the air intake lip and the back skin. This configuration gives freedom from design constraints, which enables an increase in the acoustic treatment region toward the front of the nacelle. An aircraft propulsion unit comprising a nacelle having such a forward part is also provided.
    Type: Application
    Filed: October 16, 2019
    Publication date: April 23, 2020
    Inventors: Alain PORTE, Jacques LALANE, Julien SENTIER
  • Patent number: 10618670
    Abstract: A propulsion system comprising a nacelle substantially tubular around a longitudinal axis, having an inner wall extending from a front to a rear of the nacelle and by an outer wall, external of the inner wall, extending from the front to the rear of the nacelle, a turbojet comprising a fan and situated internally of the inner wall of the nacelle, at least one tank containing an extinguishing fluid, and a network of pipes hydraulically connected to the tank. The propulsion system comprises each tank being located in the nacelle, around the inner wall and internally of the outer wall. Such a propulsion system makes it possible to shift the one or more tanks, which no longer occupy the space at the mast, and makes it possible to carry a large volume of extinguishing fluid so as to be able to accommodate future regulations.
    Type: Grant
    Filed: September 29, 2016
    Date of Patent: April 14, 2020
    Assignee: AIRBUS OPERATIONS SAS
    Inventors: Alain Porte, Jean Michel Rogero
  • Publication number: 20200102890
    Abstract: An assembly including two juxtaposed acoustic panels. Resistive faces of the acoustic panels are in the continuation of one another. A first resistive face extends as far as the first end wall of a first panel. The first end wall is in contact with a second end wall of a second panel in the region of the first resistive face and of the second resistive face. A connecting piece is interposed between the first end wall and the second end wall over a part of the length thereof so that the connecting piece does not extend as far as the first and second resistive faces. That makes it possible to form an acoustic cladding that is continuous, exhibiting no non-acoustic zone or reduced-acoustic zone at the junction between the acoustic panels of which it is formed. A nacelle of an aircraft propulsion unit is one application.
    Type: Application
    Filed: September 27, 2019
    Publication date: April 2, 2020
    Inventors: Alain Porte, Jacques Lalane, François Pons
  • Publication number: 20200101681
    Abstract: A method for manufacturing deicing acoustic skin for an aircraft acoustic panel, using a fiber spacing device. The manufacturing method includes at least one step for manufacturing a layer assembly having a deicing layer supplied with electrically conductive fibers embedded in a resin and two insulating layers arranged on either side of the deicing layer, and a baking step. The method provides for fitting, during baking, a spacing device on the layer assembly, the spacing device having pins passing through said layer assembly, perforations being produced at the locations of the pins after the withdrawal of the spacing device, the fitting of the spacing device making it possible to produce perforations with desired sizes and shapes, in a simple and effective manner, and with a reduced manufacturing duration.
    Type: Application
    Filed: September 26, 2019
    Publication date: April 2, 2020
    Inventors: Alain PORTE, Jacques LALANE, Hassan MENAY
  • Publication number: 20200101643
    Abstract: A method for manufacturing two soundproof panels of an aircraft nacelle including a duct. The manufacturing method includes a step of supplying a mold having, on a single face, a cavity for each soundproof panel, a step of producing, in the bottom of each cavity, an inner skin for being oriented towards the duct, and a curing step during which the elements present in the mold are cured in the mold. Such a method makes it possible to produce the two soundproof panels in the same mold, thus reducing the gaps between them after they have been positioned.
    Type: Application
    Filed: September 24, 2019
    Publication date: April 2, 2020
    Inventors: Alain PORTE, Jacques LALANE
  • Publication number: 20200070949
    Abstract: A sound-absorbing panel includes: an inner skin traversed by holes and intended to be oriented towards a channel in which a fluid flows, a heating mat formed by strips fixed to the inner skin on the side opposite to the channel and oriented in a first direction, wherein two adjacent strips are distant from each other in order to define a slot between them, a base fixed to the strips on the side opposite to the inner skin, wherein the base includes, on the strips side, grooves extending in a second direction different from the first direction and wherein the base has, between two successive grooves, a rib, a cellular core fixed to the base on the side opposite to the strips, and an outer panel fixed to the cellular core on the side opposite to the base.
    Type: Application
    Filed: August 29, 2019
    Publication date: March 5, 2020
    Applicant: Airbus Operations S.A.S.
    Inventors: Alain Porte, Jacques Lalane