Patents by Inventor Eric Durocher

Eric Durocher 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).

  • Publication number: 20200095942
    Abstract: A multi-spool gas turbine engine comprises a low pressure (LP) spool and a high pressure (HP) spool independently rotatable about a central axis extending through an accessory gear box (AGB). The LP spool has an LP compressor, which is axially positioned between the HP compressor of the HP spool and the AGB. A tower shaft drivingly connects the HP spool to the AGB.
    Type: Application
    Filed: September 26, 2019
    Publication date: March 26, 2020
    Inventors: Eric DUROCHER, Keith MORGAN, Lazar MITROVIC, Jean DUBREUIL, Martin POULIN
  • Publication number: 20200080435
    Abstract: The turbine exhaust structure for a gas turbine engine includes a turbine exhaust duct and a bearing housing. The turbine exhaust duct includes annular inner and outer case portions radially spaced apart to define an annular gas path therebetween and a plurality of struts extending between and structurally interconnecting the inner and outer case portions. The struts are circumferentially spaced apart about within the annular gas path. The bearing housing is disposed within the inner case portion of the turbine exhaust duct. A plurality of structural ribs extend between the bearing housing and the inner annular case portion. The structural ribs are circumferentially spaced from one another and are circumferentially offset from the struts.
    Type: Application
    Filed: September 10, 2018
    Publication date: March 12, 2020
    Inventors: Eric DUROCHER, Ian A. MACFARLANE, John PIETROBON, Eric HO, Jamal ZEINALOV
  • Patent number: 10577118
    Abstract: A method of operating a twin engine helicopter power plant, the power plant comprising: two turboshaft engines each having an engine shaft with a turbine at a distal end and a one-way clutch at a proximal end; a gear box having an input driven by the one way clutch of each engine and an output driving a helicopter rotor; a bypass clutch disposed between the proximal end of each engine shaft and the input of the gear box; and power plant management system controls for activating the bypass clutch; the method comprising: detecting when a rotary speed of an associated engine shaft is less than a rotary speed of the gear box input; activating the bypass clutch to drive the associated engine shaft using the rotation of the gear box input; and starting an associated engine by injecting fuel when the bypass clutch is activated.
    Type: Grant
    Filed: January 23, 2017
    Date of Patent: March 3, 2020
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Lazar Mitrovic, Eric Durocher, Keith Morgan
  • Publication number: 20200047876
    Abstract: The turboshaft engine for a rotorcraft includes a low pressure spool having a low pressure compressor and a low pressure turbine section, and a high pressure spool having a high pressure compressor and a high pressure turbine section. The spools are independently rotatable relative to one another. The low pressure compressor section includes a mixed flow rotor. A set of variable guide vanes (VGVs) are disposed upstream of each of the low pressure and high pressure compressors, the VGVs being configured to be independently operable relative to one another.
    Type: Application
    Filed: August 8, 2019
    Publication date: February 13, 2020
    Inventors: Keith MORGAN, Eric DUROCHER
  • Publication number: 20200049025
    Abstract: A method of operating a multi-engine system of a rotorcraft includes, during a cruise flight segment of the rotorcraft, controlling a first engine to provide sufficient power and/or rotor speed demands of the cruise flight segment; and controlling a second engine to by providing a fuel flow to the second engine that is between 70% and 99.5% less than a fuel flow provided to the first engine. A turboshaft engine for a multi-engine system configured to drive a common load is also described.
    Type: Application
    Filed: August 8, 2019
    Publication date: February 13, 2020
    Inventors: Keith MORGAN, Stephen MAH, Philippe BEAUCHESNE-MARTEL, Eric DUROCHER
  • Patent number: 10480452
    Abstract: A mixer of a bypass turbine aeroengine according to one embodiment, includes circumferential inner and outer flow surfaces in a wavy configuration to form a plurality of lobes of the mixer. The mixer has an upstream end portion of sheet metal with a first thickness and a downstream end portion of sheet metal with a second thickness less than the first thickness.
    Type: Grant
    Filed: December 13, 2018
    Date of Patent: November 19, 2019
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, Guy Lefebvre
  • Patent number: 10465611
    Abstract: A multi-spool gas turbine engine comprises a low pressure (LP) spool and a high pressure (HP) spool independently rotatable about a central axis extending through an accessory gear box (AGB). The LP spool has an LP compressor, which is axially positioned between the HP compressor of the HP spool and the AGB. A tower shaft drivingly connects the HP spool to the AGB.
    Type: Grant
    Filed: November 15, 2016
    Date of Patent: November 5, 2019
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, Keith Morgan, Lazar Mitrovic, Jean Dubreuil, Martin Poulin
  • Patent number: 10328490
    Abstract: A method of manufacturing a turbine shroud segment for a gas turbine engine comprises: metal injection molding (MIM) a shroud segment body with a groove defined in a first lateral side thereof and with a flow restrictor projecting integrally from an opposite second lateral side thereof. The groove is oversized relative to the flow restrictor to provide for a clearance fit between the flow restrictor and the groove of adjacent turbine shroud segments when assembled together in a ring formation. The shroud segment body with the integrated flow restrictor are then subjected to debinding and sintering operations.
    Type: Grant
    Filed: June 12, 2015
    Date of Patent: June 25, 2019
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, Guy Lefebvre
  • Patent number: 10302140
    Abstract: A gas turbine shaft assembly comprises first and second axially mating shafts. The first shaft has a circumferential array of splines configured to mesh with a corresponding circumferential array of splines on the second shaft. The first shaft defines at least one axially extending slot aligned with one of the splines on the first shaft. The second shaft has at least one radial projection aligned with one of the splines on the second shaft. The engagement of the radial projection with the slot provides angular correspondence between the splines of the first and the second shafts prior to axial engagement of the splines.
    Type: Grant
    Filed: December 15, 2016
    Date of Patent: May 28, 2019
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Johnny Vinski, Eric Durocher
  • Publication number: 20190120170
    Abstract: A mixer of a bypass turbine aeroengine according to one embodiment, includes circumferential inner and outer flow surfaces in a wavy configuration to form a plurality of lobes of the mixer. The mixer has an upstream end portion of sheet metal with a first thickness and a downstream end portion of sheet metal with a second thickness less than the first thickness.
    Type: Application
    Filed: December 13, 2018
    Publication date: April 25, 2019
    Inventors: Eric DUROCHER, Guy LEFEBVRE
  • Patent number: 10190536
    Abstract: A mixer of a bypass turbine aeroengine according to one embodiment, includes circumferential inner and outer flow surfaces in a wavy configuration to form a plurality of lobes of the mixer. The mixer has an upstream end portion of sheet metal with a first thickness and a downstream end portion of sheet metal with a second thickness less than the first thickness.
    Type: Grant
    Filed: September 17, 2012
    Date of Patent: January 29, 2019
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, Guy Lefebvre
  • Publication number: 20180172078
    Abstract: A gas turbine shaft assembly comprises first and second axially mating shafts. The first shaft has a circumferential array of splines configured to mesh with a corresponding circumferential array of splines on the second shaft. The first shaft defines at least one axially extending slot aligned with one of the splines on the first shaft. The second shaft has at least one radial projection aligned with one of the splines on the second shaft. The engagement of the radial projection with the slot provides angular correspondence between the splines of the first and the second shafts prior to axial engagement of the splines.
    Type: Application
    Filed: December 15, 2016
    Publication date: June 21, 2018
    Inventors: Johnny VINSKI, Eric DUROCHER
  • Publication number: 20180135522
    Abstract: A gas turbine engine has an in-line mounted accessory gear box (AGB) and an accessory drivingly connected to the AGB, the accessory being oriented transversally to the engine centerline.
    Type: Application
    Filed: November 15, 2016
    Publication date: May 17, 2018
    Inventors: Lazar MITROVIC, Jean DUBREUIL, Eric DUROCHER, Keith MORGAN, Michel DESJARDINS
  • Publication number: 20180073428
    Abstract: A gas turbine engine has a first spool having a low pressure compressor section disposed forward of an air inlet along a direction of travel of the engine, and a low pressure turbine section disposed forward of the low pressure compressor section and drivingly engaged thereto. A second spool has a high pressure compressor section disposed forward of the low pressure compressor section, and a high pressure turbine section disposed forward of the high pressure compressor section and drivingly engaged thereto. The high pressure turbine section is disposed aft of the low pressure turbine section. An output drive shaft drivingly engages the low pressure turbine section and extends forwardly therefrom to drive a rotatable load. A method of operating a gas turbine engine is also discussed.
    Type: Application
    Filed: September 15, 2016
    Publication date: March 15, 2018
    Inventors: Keith MORGAN, Robert PELUSO, Ghislain PLANTE, Eugene GEKHT, Eric DUROCHER, Jean DUBREUIL
  • Publication number: 20180073438
    Abstract: A multi-spool gas turbine engine comprises a low pressure (LP) spool and a high pressure (HP) spool independently rotatable about a central axis extending through an accessory gear box (AGB). The LP spool has an LP compressor, which is axially positioned between the HP compressor of the HP spool and the AGB. A tower shaft drivingly connects the HP spool to the AGB.
    Type: Application
    Filed: November 15, 2016
    Publication date: March 15, 2018
    Inventors: Eric DUROCHER, Keith MORGAN, Lazar MITROVIC, Jean DUBREUIL, Martin POULIN
  • Publication number: 20170327241
    Abstract: A method of operating a twin engine helicopter power plant, the power plant comprising: two turboshaft engines each having an engine shaft with a turbine at a distal end and a one-way clutch at a proximal end; a gear box having an input driven by the one way clutch of each engine and an output driving a helicopter rotor; a bypass clutch disposed between the proximal end of each engine shaft and the input of the gear box; and power plant management system controls for activating the bypass clutch; the method comprising: detecting when a rotary speed of an associated engine shaft is less than a rotary speed of the gear box input; activating the bypass clutch to drive the associated engine shaft using the rotation of the gear box input; and starting an associated engine by injecting fuel when the bypass clutch is activated.
    Type: Application
    Filed: January 23, 2017
    Publication date: November 16, 2017
    Inventors: Lazar MITROVIC, Eric DUROCHER, Keith MORGAN
  • Patent number: 9683458
    Abstract: A bearing housing comprises a body having a partition wall delimiting the bearing housing from an environment and defining a bearing housing interior cavity configured to receive an oil feed. An inlet bore is in the partition wall in fluid communication with the bearing housing interior cavity. The inlet bore is configured to receive an end of an oil tube, the inlet bore comprising a contact surface configured for contacting the oil tube. A seal is between the inlet bore and the oil tube. An oil recuperation passage is defined in the partition wall in fluid communication with the inlet bore between the seal and at least a portion of the contact surface, the oil recuperation passage being in fluid communication with an oil recuperating cavity.
    Type: Grant
    Filed: August 20, 2015
    Date of Patent: June 20, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Guy Lefebvre, Eric Durocher
  • Publication number: 20170051632
    Abstract: A bearing housing comprises a body having a partition wall delimiting the bearing housing from an environment and defining a bearing housing interior cavity configured to receive an oil feed. An inlet bore is in the partition wall in fluid communication with the bearing housing interior cavity. The inlet bore is configured to receive an end of an oil tube, the inlet bore comprising a contact surface configured for contacting the oil tube. A seal is between the inlet bore and the oil tube. An oil recuperation passage is defined in the partition wall in fluid communication with the inlet bore between the seal and at least a portion of the contact surface, the oil recuperation passage being in fluid communication with an oil recuperating cavity.
    Type: Application
    Filed: August 20, 2015
    Publication date: February 23, 2017
    Inventors: Guy LEFEBVRE, Eric DUROCHER
  • Publication number: 20170022831
    Abstract: A turbine shroud segment is metal injection molded (MIM) about a low melting point material insert. The low melting point material is dissolved using heat during the heat treatment cycle required for the MIM material, thereby leaving internal cooling passages in the MIM shroud segment without extra manufacturing operation.
    Type: Application
    Filed: April 15, 2015
    Publication date: January 26, 2017
    Inventors: ERIC DUROCHER, GUY LEFEBVRE
  • Patent number: 9552661
    Abstract: A method, system and computer program product for distinguishing superimposed links to a node in a drawing area. Links connected to a side of a node involved in an editing interaction are identified. The order of the identified links to be connected to the side of the node is determined by sorting the identified links based on the coordinates of the links' bend point and/or opposite end point. The connection points of these identified links are repositioned based on this determined order. By only repositioning the connection points to the node involved in the editing interaction instead of rerouting all of the links in the diagram area, the processing time is improved. Furthermore, by repositioning the connection points that were superimposed so that they are spaced apart based on the coordinates of the links' bend point and/or opposite end point, it is easier to distinguish between the different links.
    Type: Grant
    Filed: August 30, 2010
    Date of Patent: January 24, 2017
    Assignee: International Business Machines Corporation
    Inventor: Eric Durocher