Patents by Inventor Philippe Bonniere
Philippe Bonniere 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).
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Patent number: 11125110Abstract: A multi-film oil damper has an annular damper cavity defined within a housing between a radially outward wall, a first radially extending side wall and a second radially extending side wall. Nested damper rings are disposed within the annular damper cavity for defining squeeze film annuli therebetween. The squeeze film annuli are fluidly connected in parallel to an inlet gallery.Type: GrantFiled: March 18, 2019Date of Patent: September 21, 2021Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Thomas Veitch, David Beamish, Philippe Bonniere
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Patent number: 10815825Abstract: A bearing arrangement rotatably supports a shaft of an aircraft engine. The bearing arrangement comprises a bearing having rolling elements disposed between inner and outer races. The inner race is affixed to the shaft. A decoupler normally structurally couples the outer race of the bearing to a stator structure of the engine. The decoupler is configured to release the bearing from the stator structure when subject to a predetermined critical load. A bumper is mounted to the stator structure and encircles the bearing. The bumper has a radially inwardly facing surface disposed in close proximity to a radially outer surface of the outer race of the bearing and defines therewith a radial gap to accommodate and constrain an orbiting motion of the rotor about the central axis of the engine after decoupling at the bearing.Type: GrantFiled: November 27, 2018Date of Patent: October 27, 2020Assignee: PRATT & WHITNEY CANADA CORP.Inventors: David Denis, Philippe Bonniere, Milica Kojovic, Oleg Korshikov, Lena Raykowski, Czeslaw Wojtyczka
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Publication number: 20200300120Abstract: A multi-film oil damper has an annular damper cavity defined within a housing between a radially outward wall, a first radially extending side wall and a second radially extending side wall. Nested damper rings are disposed within the annular damper cavity for defining squeeze film annuli therebetween. The squeeze film annuli are fluidly connected in parallel to an inlet gallery.Type: ApplicationFiled: March 18, 2019Publication date: September 24, 2020Inventors: Thomas VEITCH, David BEAMISH, Philippe BONNIERE
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Publication number: 20200284298Abstract: A multi-film oil damper suited for accommodating radial movement of a rotary shaft bearing relative to a bearing housing, the multi-film oil damper comprising: an annular damper cavity defined within the bearing housing between a radially outward wall and radially extending side walls; an inner damper ring; an outer damper ring disposed between the inner damper ring and the radially outward wall of the annular damper cavity; wherein the annular damper cavity has an oil inlet in communication with a source of pressurized oil; and wherein a radial thickness of the inner damper ring exceeds a radial thickness of the outer damper ring.Type: ApplicationFiled: March 4, 2019Publication date: September 10, 2020Inventors: Thomas VEITCH, David BEAMISH, Philippe BONNIERE
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Publication number: 20190218930Abstract: A bearing arrangement rotatably supports a shaft of an aircraft engine. The bearing arrangement comprises a bearing having rolling elements disposed between inner and outer races. The inner race is affixed to the shaft. A decoupler normally structurally couples the outer race of the bearing to a stator structure of the engine. The decoupler is configured to release the bearing from the stator structure when subject to a predetermined critical load. A bumper is mounted to the stator structure and encircles the bearing. The bumper has a radially inwardly facing surface disposed in close proximity to a radially outer surface of the outer race of the bearing and defines therewith a radial gap to accommodate and constrain an orbiting motion of the rotor about the central axis of the engine after decoupling at the bearing.Type: ApplicationFiled: November 27, 2018Publication date: July 18, 2019Inventors: DAVID DENIS, Philippe Bonniere, Milica KOJOVIC, Oleg KORSHIKOV, Lena RAYKOWSKI, Czeslaw WOJTYCZKA
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Patent number: 10156154Abstract: A bearing arrangement rotatably supports a shaft of an aircraft engine. The bearing arrangement comprises a bearing having rolling elements disposed between inner and outer races. The inner race is affixed to the shaft. A decoupler normally structurally couples the outer race of the bearing to a stator structure of the engine. The decoupler is configured to release the bearing from the stator structure when subject to a predetermined critical load. A bumper is mounted to the stator structure and encircles the bearing. The bumper has a radially inwardly facing surface disposed in close proximity to a radially outer surface of the outer race of the bearing and defines therewith a radial gap to accommodate and constrain an orbiting motion of the rotor about the central axis of the engine after decoupling at the bearing.Type: GrantFiled: August 31, 2017Date of Patent: December 18, 2018Assignee: PRATT & WHITNEY CANADA CORP.Inventors: David Denis, Philippe Bonniere, Milica Kojovic, Oleg Korshikov, Lena Raykowski, Czeslaw Wojtyczka
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Publication number: 20170362954Abstract: A bearing arrangement rotatably supports a shaft of an aircraft engine. The bearing arrangement comprises a bearing having rolling elements disposed between inner and outer races. The inner race is affixed to the shaft. A decoupler normally structurally couples the outer race of the bearing to a stator structure of the engine. The decoupler is configured to release the bearing from the stator structure when subject to a predetermined critical load. A bumper is mounted to the stator structure and encircles the bearing. The bumper has a radially inwardly facing surface disposed in close proximity to a radially outer surface of the outer race of the bearing and defines therewith a radial gap to accommodate and constrain an orbiting motion of the rotor about the central axis of the engine after decoupling at the bearing.Type: ApplicationFiled: August 31, 2017Publication date: December 21, 2017Applicant: PRATT & WHITNEY CANADA CORP.Inventors: David DENIS, Philippe BONNIERE, Milica KOJOVIC, Oleg KORSHIKOV, Lena RAYKOWSKI, Czeslaw WOJTYCZKA
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Patent number: 9777592Abstract: A bearing arrangement rotatably supports a shaft of an aircraft engine. The bearing arrangement comprises a bearing having rolling elements disposed between inner and outer races. The inner race is affixed to the shaft. A decoupler normally structurally couples the outer race of the bearing to a stator structure of the engine. The decoupler is configured to release the bearing from the stator structure when subject to a predetermined critical load. A bumper is mounted to the stator structure and encircles the bearing. The bumper has a radially inwardly facing surface disposed in close proximity to a radially outer surface of the outer race of the bearing and defines therewith a radial gap to accommodate and constrain an orbiting motion of the rotor about the central axis of the engine after decoupling at the bearing.Type: GrantFiled: December 23, 2013Date of Patent: October 3, 2017Assignee: PRATT & WHITNEY CANADA CORP.Inventors: David Denis, Philippe Bonniere, Milica Kojovic, Oleg Korshikov, Lena Raykowski, Czeslaw Wojtyczka
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Patent number: 9080461Abstract: A gas turbine engine having at least one spool assembly, the at least one spool assembly including a fan rotor, a compressor disposed downstream of the fan rotor, a turbine and a shaft connecting the fan rotor, compressor and turbine, a joint affixed to an upstream end of the shaft, and including a first link connecting the fan rotor to the shaft and a second link connecting the compressor to the shaft, the second link being less rigid then the first link.Type: GrantFiled: February 2, 2012Date of Patent: July 14, 2015Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Richard Ivakitch, Andreas Eleftheriou, Philippe Bonniere
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Publication number: 20150176427Abstract: A bearing arrangement rotatably supports a shaft of an aircraft engine. The bearing arrangement comprises a bearing having rolling elements disposed between inner and outer races. The inner race is affixed to the shaft. A decoupler normally structurally couples the outer race of the bearing to a stator structure of the engine. The decoupler is configured to release the bearing from the stator structure when subject to a predetermined critical load. A bumper is mounted to the stator structure and encircles the bearing. The bumper has a radially inwardly facing surface disposed in close proximity to a radially outer surface of the outer race of the bearing and defines therewith a radial gap to accommodate and constrain an orbiting motion of the rotor about the central axis of the engine after decoupling at the bearing.Type: ApplicationFiled: December 23, 2013Publication date: June 25, 2015Applicant: Pratt & Whitney Canada Corp.Inventors: DAVID DENIS, PHILIPPE BONNIERE, MILICA KOJOVIC, OLEG KORSHIKOV, LENA RAYKOWSKI, CZESLAW WOJTYCZKA
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Patent number: 8708656Abstract: The blade dovetails and associated dovetail slots of a gas turbine engine rotor assembly are shaped so that during windmilling the high stress regions of the blade dovetails are shielded from rubbing against the disk and vice versa. Bumper surfaces are provided in low stress regions of the dovetail assembly such that the windmilling contact points between the blade dovetails and the disk are in non-critical areas of the dovetail assembly.Type: GrantFiled: May 25, 2010Date of Patent: April 29, 2014Assignee: Pratt & Whitney Canada Corp.Inventors: Barry Barnett, Philippe Bonniere
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Publication number: 20130202442Abstract: A gas turbine engine having at least one spool assembly, the at least one spool assembly including a fan rotor, a compressor disposed downstream of the fan rotor, a turbine and a shaft connecting the fan rotor, compressor and turbine, a joint affixed to an upstream end of the shaft, and including a first link connecting the fan rotor to the shaft and a second link connecting the compressor to the shaft, the second link being less rigid then the first link.Type: ApplicationFiled: February 2, 2012Publication date: August 8, 2013Applicant: PRATT & WHITNEY CANADA CORP.Inventors: Richard IVAKITCH, Andreas ELEFTHERIOU, Philippe BONNIERE
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Patent number: 8197189Abstract: A retaining ring is mounted in frictional engagement with a static gas turbine engine part, such as a compressor shroud, in order to provide frictional damping.Type: GrantFiled: November 27, 2007Date of Patent: June 12, 2012Assignee: Pratt & Whitney Canada Corp.Inventors: Philippe Bonniere, Andreas Eleftheriou, Ignatius Theratil, Aldo Abate
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Publication number: 20110293429Abstract: The blade dovetails and associated dovetail slots of a gas turbine engine rotor assembly are shaped so that during windmilling the high stress regions of the blade dovetails are shielded from rubbing against the disk and vice versa. Bumper surfaces are provided in low stress regions of the dovetail assembly such that the windmilling contact points between the blade dovetails and the disk are in non-critical areas of the dovetail assembly.Type: ApplicationFiled: May 25, 2010Publication date: December 1, 2011Inventors: Barry Barnett, Philippe Bonniere
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Publication number: 20090136348Abstract: A retaining ring is mounted in frictional engagement with a static gas turbine engine part, such as a compressor shroud, in order to provide frictional damping.Type: ApplicationFiled: November 27, 2007Publication date: May 28, 2009Inventors: Philippe Bonniere, Andreas Eleftheriou, Ignatius Theratil, Aido Abate