Patents by Inventor Aurelien Tingaud

Aurelien Tingaud 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: 10087774
    Abstract: A variable-nozzle turbocharger includes a variable vane mechanism that has an annular nozzle ring supporting an array of rotatable vanes, an insert having a tubular portion sealingly received into a bore of the turbine housing and having a nozzle portion extending radially out from one end of the tubular portion and being axially spaced from the nozzle ring with the vanes therebetween, and a plurality of two-piece self-centering spacer assemblies connected between the nozzle portion of the insert and the nozzle ring. Each spacer assembly comprises a tubular sleeve and a separate pin that passes through the through-passage of the sleeve, end portions of the pin being secured respectively to the nozzle ring and the nozzle portion. One end of each sleeve has a conical surface and engages in a corresponding conical countersink in the adjacent face of the nozzle ring or nozzle portion.
    Type: Grant
    Filed: September 29, 2014
    Date of Patent: October 2, 2018
    Assignee: Honeywell International Inc.
    Inventors: Pierre Barthelet, Nicolas Morand, Emmanuel Severin, Calogero Beltrami, Vincent Eumont, Francis Abel, Arnaud Gerard, Aurelien Tingaud, Jayavenkateshwaran Krishnamoorthy
  • Patent number: 9938894
    Abstract: A turbocharger includes a variable turbine nozzle defined between a nozzle ring and a pipe flange, and having a plurality of circumferentially spaced vanes rotatably mounted on the nozzle ring such that the vanes are pivotable. Each vane includes an airfoil section and a disk section rigidly affixed to an end of the airfoil section, the disk section being disposed against a face of the pipe flange, each disk section having a plurality of perforations extending axially therethrough. The pipe flange has a corresponding number of holes for each disk section of the vanes, the holes being positioned such that as each vane is rotated the perforations in the disk sections and the holes in the pipe flange of the insert become aligned in some positions of the vanes, allowing exhaust gas to pass between the nozzle and a space on an opposite side of the pipe flange from the nozzle.
    Type: Grant
    Filed: May 6, 2015
    Date of Patent: April 10, 2018
    Assignee: Honeywell International Inc.
    Inventors: Chris Groves, Damien Marsal, Stephane Sibille, Aurelien Tingaud, Alain Lombard
  • Patent number: 9932886
    Abstract: A turbocharger has an annular bypass valve disposed in an annular portion of a bypass passage of the turbine housing. The turbine housing defines an exhaust gas chamber having separate half-annular first and second scrolls, and a portion of the bypass passage is sector-divided by a pair of dividing walls that create two 180-degree bypass sectors respectively connected to the first and second scrolls. Each dividing wall has a through-hole. The valve rotor defines a pair of valve members that close the through-holes when the bypass valve is fully closed. When the valve rotor begins to rotate toward an open position, first the valve members open the through-holes to connect the two bypass sectors, and then the bypass flow passages begin to open.
    Type: Grant
    Filed: February 17, 2016
    Date of Patent: April 3, 2018
    Assignee: Honeywell International Inc.
    Inventors: Alain Lombard, Lionel Toussaint, Chris Groves, Aurelien Tingaud
  • Patent number: 9845723
    Abstract: A centrifugal compressor for a turbocharger includes an inlet-adjustment mechanism in an air inlet for the compressor, operable to move between an open position and a closed position in the air inlet. The inlet-adjustment mechanism includes a variable-geometry conical mechanism comprising a plurality of vanes that in the closed position collectively form a frusto-conical inlet member having a trailing edge inner diameter that is smaller than an inner diameter of the shroud surface of the compressor housing at the inducer portion of the compressor wheel such that an effective diameter of the air inlet at the inducer portion is determined by the trailing edge inner diameter of the variable-geometry conical mechanism. The vanes in the open position are pivoted radially outwardly so as to increase the trailing edge inner diameter of the inlet member and thereby increase the effective diameter of the air inlet at the inducer portion.
    Type: Grant
    Filed: November 24, 2014
    Date of Patent: December 19, 2017
    Assignee: Honeywell International Inc.
    Inventors: Hani Mohtar, Pascal Villemin, Stephane Pees, Aurelien Tingaud, Alain Lombard, Damien Marsal
  • Publication number: 20170234212
    Abstract: A turbocharger has an annular bypass valve disposed in an annular portion of a bypass passage of the turbine housing. The turbine housing defines an exhaust gas chamber having separate half-annular first and second scrolls, and a portion of the bypass passage is sector-divided by a pair of dividing walls that create two 180-degree bypass sectors respectively connected to the first and second scrolls. Each dividing wall has a through-hole. The valve rotor defines a pair of valve members that close the through-holes when the bypass valve is fully closed. When the valve rotor begins to rotate toward an open position, first the valve members open the through-holes to connect the two bypass sectors, and then the bypass flow passages begin to open.
    Type: Application
    Filed: February 17, 2016
    Publication date: August 17, 2017
    Applicant: Honeywell International Inc.
    Inventors: Alain Lombard, Lionel Toussaint, Chris Groves, Aurelien Tingaud
  • Patent number: 9708925
    Abstract: A centrifugal compressor for a turbocharger includes an inlet-adjustment mechanism in an air inlet for the compressor, operable to move between an open position and a closed position in the air inlet. The inlet-adjustment mechanism includes a variable-geometry orifice actuated by a rotatable actuator ring. In the closed position, the orifice's inner diameter is smaller than that of a shroud surface of the compressor housing and therefore dictates the effective inlet diameter for the compressor. In the open position the orifice no longer forms an inner diameter smaller than the shroud surface, so that the effective inlet diameter is determined by the shroud surface.
    Type: Grant
    Filed: December 17, 2014
    Date of Patent: July 18, 2017
    Assignee: Honeywell International Inc.
    Inventors: Hani Mohtar, Pascal Villemin, Stephane Pees, William Joseph Smith, Aurelien Tingaud, Lionel Toussaint
  • Patent number: 9683484
    Abstract: A centrifugal compressor for a turbocharger includes an inlet-adjustment mechanism in an air inlet for the compressor, operable to move between an open position and a closed position in the air inlet. The inlet-adjustment mechanism includes a variable-geometry conduit comprising a plurality of vanes that in the closed position collectively form a converging inlet member having a trailing edge inner diameter that is smaller than an inner diameter of the shroud surface of the compressor housing at the inducer portion of the compressor wheel such that an effective diameter of the air inlet at the inducer portion is determined by the trailing edge inner diameter of the variable-geometry conduit. The vanes in the open position are pivoted radially outwardly so as to increase the trailing edge inner diameter of the inlet member and thereby increase the effective diameter of the air inlet at the inducer portion.
    Type: Grant
    Filed: March 10, 2015
    Date of Patent: June 20, 2017
    Assignee: Honeywell International Inc.
    Inventors: Aurelien Tingaud, Damien Marsal, Chris Groves, Alain Lombard, Lionel Toussaint, Hani Mohtar
  • Publication number: 20160348524
    Abstract: A turbine assembly can include a turbine wheel, a shroud component, a turbine housing and a seal that includes a wall and a lower lip that that extends radially outwardly from the wall where the seal is disposed, at least in part, between an outer surface of the shroud component and an inner surface of the turbine housing and where the lower lip is in contact with the turbine housing.
    Type: Application
    Filed: May 30, 2016
    Publication date: December 1, 2016
    Inventors: Arnaud Gerard, Aurelien Tingaud, Shankar Pandurangasa Solanki, Mohan Javvadi
  • Publication number: 20160326951
    Abstract: A turbocharger includes a variable turbine nozzle defined between a nozzle ring and a pipe flange, and having a plurality of circumferentially spaced vanes rotatably mounted on the nozzle ring such that the vanes are pivotable. Each vane includes an airfoil section and a disk section rigidly affixed to an end of the airfoil section, the disk section being disposed against a face of the pipe flange, each disk section having a plurality of perforations extending axially therethrough. The pipe flange has a corresponding number of holes for each disk section of the vanes, the holes being positioned such that as each vane is rotated the perforations in the disk sections and the holes in the pipe flange of the insert become aligned in some positions of the vanes, allowing exhaust gas to pass between the nozzle and a space on an opposite side of the pipe flange from the nozzle.
    Type: Application
    Filed: May 6, 2015
    Publication date: November 10, 2016
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Chris Groves, Damien Marsal, Stephane Sibille, Aurelien Tingaud, Alain Lombard
  • Publication number: 20160265424
    Abstract: A centrifugal compressor for a turbocharger includes an inlet-adjustment mechanism in an air inlet for the compressor, operable to move between an open position and a closed position in the air inlet. The inlet-adjustment mechanism includes a variable-geometry conduit comprising a plurality of vanes that in the closed position collectively form a converging inlet member having a trailing edge inner diameter that is smaller than an inner diameter of the shroud surface of the compressor housing at the inducer portion of the compressor wheel such that an effective diameter of the air inlet at the inducer portion is determined by the trailing edge inner diameter of the variable-geometry conduit. The vanes in the open position are pivoted radially outwardly so as to increase the trailing edge inner diameter of the inlet member and thereby increase the effective diameter of the air inlet at the inducer portion.
    Type: Application
    Filed: March 10, 2015
    Publication date: September 15, 2016
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Aurelien Tingaud, Damien Marsal, Chris Groves, Alain Lombard, Lionel Toussaint, Hani Mohtar
  • Publication number: 20160177956
    Abstract: A centrifugal compressor for a turbocharger includes an inlet-adjustment mechanism in an air inlet for the compressor, operable to move between an open position and a closed position in the air inlet. The inlet-adjustment mechanism includes a variable-geometry orifice actuated by a rotatable actuator ring. In the closed position, the orifice's inner diameter is smaller than that of a shroud surface of the compressor housing and therefore dictates the effective inlet diameter for the compressor. In the open position the orifice no longer forms an inner diameter smaller than the shroud surface, so that the effective inlet diameter is determined by the shroud surface.
    Type: Application
    Filed: December 17, 2014
    Publication date: June 23, 2016
    Inventors: Hani Mohtar, Pascal Villemin, Stephane Pees, William Joseph Smith, Aurelien Tingaud, Lionel Toussaint
  • Patent number: 9353637
    Abstract: A turbine assembly can include a turbine wheel, a shroud component, a turbine housing and a seal that includes a wall and a lower lip that that extends radially outwardly from the wall at an obtuse angle where the seal is disposed, at least in part, between an outer surface of the shroud component and an inner surface of the turbine housing. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.
    Type: Grant
    Filed: February 25, 2013
    Date of Patent: May 31, 2016
    Assignee: Honeywell International Inc.
    Inventors: Arnaud Gerard, Aurelien Tingaud, Shankar Pandurangasa Solanki, Mohan Rao Javvadi
  • Publication number: 20160146099
    Abstract: A centrifugal compressor for a turbocharger includes an inlet-adjustment mechanism in an air inlet for the compressor, operable to move between an open position and a closed position in the air inlet. The inlet-adjustment mechanism includes a variable-geometry conical mechanism comprising a plurality of vanes that in the closed position collectively form a frusto-conical inlet member having a trailing edge inner diameter that is smaller than an inner diameter of the shroud surface of the compressor housing at the inducer portion of the compressor wheel such that an effective diameter of the air inlet at the inducer portion is determined by the trailing edge inner diameter of the variable-geometry conical mechanism. The vanes in the open position are pivoted radially outwardly so as to increase the trailing edge inner diameter of the inlet member and thereby increase the effective diameter of the air inlet at the inducer portion.
    Type: Application
    Filed: November 24, 2014
    Publication date: May 26, 2016
    Inventors: Hani Mohtar, Pascal Villemin, Stephane Pees, Aurelien Tingaud, Alain Lombard, Damien Marsal
  • Publication number: 20160090858
    Abstract: A variable-nozzle turbocharger includes a variable vane mechanism that has an annular nozzle ring supporting an array of rotatable vanes, an insert having a tubular portion sealingly received into a bore of the turbine housing and having a nozzle portion extending radially out from one end of the tubular portion and being axially spaced from the nozzle ring with the vanes therebetween, and a plurality of two-piece self-centering spacer assemblies connected between the nozzle portion of the insert and the nozzle ring. Each spacer assembly comprises a tubular sleeve and a separate pin that passes through the through-passage of the sleeve, end portions of the pin being secured respectively to the nozzle ring and the nozzle portion. One end of each sleeve has a conical surface and engages in a corresponding conical countersink in the adjacent face of the nozzle ring or nozzle portion.
    Type: Application
    Filed: September 29, 2014
    Publication date: March 31, 2016
    Inventors: Pierre Barthelet, Nicolas Morand, Emmanuel Severin, Calogero Beltrami, Vincent Eumont, Francis Abel, Arnaud Gerard, Aurelien Tingaud, Jayavenkateshwaran Krishnamoorthy
  • Publication number: 20130302185
    Abstract: A turbine assembly can include a turbine wheel, a shroud component, a turbine housing and a seal that includes a wall and a lower lip that that extends radially outwardly from the wall at an obtuse angle where the seal is disposed, at least in part, between an outer surface of the shroud component and an inner surface of the turbine housing. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.
    Type: Application
    Filed: February 25, 2013
    Publication date: November 14, 2013
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Arnaud Gerard, Aurelien Tingaud, Shankar Pandurangasa Solanki, Mohan Rao Javvadi