Patents by Inventor Marc Lavoie
Marc Lavoie 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: 11852073Abstract: An orifice pack is provided for delivering pressurized air to a compressor bleed valve of a gas turbine engine. The orifice pack has a diffusion chamber in serial flow communication with a tapering passage and a first outlet passage for venting a first portion of the pressurized air from the diffusion chamber. A second outlet passage branches off from the diffusion chamber at an axial location between the inlet and the tapering passage. The second outlet passage is fluidly connected to the compressor bleed valve for directing a second portion of the pressurized air from the diffusion chamber to the compressor bleed valve.Type: GrantFiled: July 30, 2021Date of Patent: December 26, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Martin Dobson, Oleg Iskra, Michael Fryer, Marc Lavoie, Ivan Sidorovich Paradiso, Louis Duranleau-Hendrickx, Domenico Di Florio, Tibor Urac
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Publication number: 20230407766Abstract: An assembly is provided for a gas turbine engine. This gas turbine engine assembly includes a case, a housing, a component and a spring element. The case includes an aperture that extends axially along an axis through the case. The housing is attached to the case with a cavity formed by and axially between the housing and the case. The component includes a base and a projection. The base is disposed within the cavity and axially engages the case. The projection projects out from the base and axially through the aperture. The spring element is disposed within the cavity. The spring element is compressed axially between and engages the base and the housing.Type: ApplicationFiled: May 31, 2022Publication date: December 21, 2023Inventors: Michael Fryer, Martin Dobson, Oleg Iskra, Marc Lavoie, Ivan Sidorovich Paradiso, Louis Duranleau-Hendrickx, Domenico Di Florio
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Patent number: 11802509Abstract: Methods and systems for filtering pressurized air used to control a compressor bleed valve of a gas turbine engine are provided. One method comprises receiving the pressurized air in a conduit via an inlet of the conduit, releasing a first portion of the pressurized air out of the conduit via an outlet of the conduit, releasing a second portion of the pressurized air from the conduit via a port disposed between the inlet and the outlet of the conduit, directing the second portion of the pressurized air from the port to a filter along an upward flow path, filtering the second portion of the pressurized air using the filter, and directing the second portion of the pressurized air from the filter toward the compressor bleed valve.Type: GrantFiled: June 25, 2021Date of Patent: October 31, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Martin Dobson, Oleg Iskra, Michael Fryer, Marc Lavoie, Ivan Sidorovich Paradiso, Louis Duranleau-Hendrickx, Domenico Di Florio
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Patent number: 11780561Abstract: There is provided a blade angle feedback assembly for a propeller of an aircraft engine. The propeller is rotatable about an axis and has propeller blades rotatable about respective spanwise axes to adjust a blade angle thereof. The blade angle feedback assembly comprises a feedback ring having a plurality of position markers disposed thereon, at least one sensor configured to provide feedback on the blade angle of the propeller blades by detecting a relative movement between the feedback ring and the at least one sensor, and at least one shielding element provided between the feedback ring and the propeller, the at least one shielding element configured to shield the feedback ring from electromagnetism.Type: GrantFiled: May 21, 2021Date of Patent: October 10, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Joseph Ernesto Marone, Ella Yakobov, Ian Farrell, Olivier Basse, Martin Dobson, Martin Clermont, Marc Lavoie
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Patent number: 11639689Abstract: The gas turbine engine can have a pneumatic actuator; an intake device secured to a gas path wall delimiting the gas path, the intake device having a tubular body protruding from the gas path wall into the gas path and an inlet aperture formed in the tubular body, the inlet aperture spaced-apart from the gas path wall and facing downstream relative a flow orientation of the gas path, the intake device having an internal conduit extending from the inlet aperture, along the tubular body, to an outlet across the gas path wall; and a fluid line fluidly connecting the outlet of the intake device to the pneumatic actuator.Type: GrantFiled: September 17, 2021Date of Patent: May 2, 2023Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Martin Dobson, Oleg Iskra, Michael Fryer, Marc Lavoie, Ivan Sidorovich Paradiso, Louis Duranleau-Hendrickx, Domenico Di Florio, Tibor Urac
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Publication number: 20230093292Abstract: The gas turbine engine can have a pneumatic actuator; an intake device secured to a gas path wall delimiting the gas path, the intake device having a tubular body protruding from the gas path wall into the gas path and an inlet aperture formed in the tubular body, the inlet aperture spaced-apart from the gas path wall and facing downstream relative a flow orientation of the gas path, the intake device having an internal conduit extending from the inlet aperture, along the tubular body, to an outlet across the gas path wall; and a fluid line fluidly connecting the outlet of the intake device to the pneumatic actuator.Type: ApplicationFiled: September 17, 2021Publication date: March 23, 2023Inventors: Martin DOBSON, Oleg ISKRA, Michael FRYER, Marc LAVOIE, Ivan Sidorovich PARADISO, Louis DURANLEAU-HENDRICKX, Domenico DI FLORIO, Tibor URAC
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Publication number: 20230029960Abstract: An orifice pack is provided for delivering pressurized air to a compressor bleed valve of a gas turbine engine. The orifice pack has a diffusion chamber in serial flow communication with a tapering passage and a first outlet passage for venting a first portion of the pressurized air from the diffusion chamber. A second outlet passage branches off from the diffusion chamber at an axial location between the inlet and the tapering passage. The second outlet passage is fluidly connected to the compressor bleed valve for directing a second portion of the pressurized air from the diffusion chamber to the compressor bleed valve.Type: ApplicationFiled: July 30, 2021Publication date: February 2, 2023Inventors: Martin DOBSON, Oleg ISKRA, Michael FRYER, Marc LAVOIE, Ivan SIDOROVICH PARADISO, Louis DURANLEAU-HENDRICKX, Domenico DI FLORIO, Tibor URAC
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Publication number: 20220412259Abstract: Methods and systems for filtering pressurized air used to control a compressor bleed valve of a gas turbine engine are provided. One method comprises receiving the pressurized air in a conduit via an inlet of the conduit, releasing a first portion of the pressurized air out of the conduit via an outlet of the conduit, releasing a second portion of the pressurized air from the conduit via a port disposed between the inlet and the outlet of the conduit, directing the second portion of the pressurized air from the port to a filter along an upward flow path, filtering the second portion of the pressurized air using the filter, and directing the second portion of the pressurized air from the filter toward the compressor bleed valve.Type: ApplicationFiled: June 25, 2021Publication date: December 29, 2022Inventors: Martin DOBSON, Oleg ISKRA, Michael FRYER, Marc LAVOIE, Ivan SIDOROVICH PARADISO, Louis DURANLEAU-HENDRICKX, Domenico DI FLORIO
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Patent number: 11279465Abstract: A blade angle feedback ring assembly for an aircraft engine propeller having adjustable angle blades is provided. The feedback ring assembly comprises a feedback ring coupled to rotate with the propeller, the engine configured such that a first electrically-conductive path is defined between the propeller and the engine via the feedback ring, and an electric current conduction element provided between the propeller and the engine to define a second electrically-conductive path between the propeller and the engine in parallel to the first path, the second electrically-conductive path configured with a lower electrical resistance to conduction between the propeller and the engine than the first electrically-conductive path.Type: GrantFiled: July 16, 2018Date of Patent: March 22, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Joseph Ernesto Marone, Olivier Basse, Martin Dobson, Martin Clermont, Marc Lavoie
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Publication number: 20210284322Abstract: There is provided a blade angle feedback assembly for a propeller of an aircraft engine. The propeller is rotatable about an axis and has propeller blades rotatable about respective spanwise axes to adjust a blade angle thereof. The blade angle feedback assembly comprises a feedback ring having a plurality of position markers disposed thereon, at least one sensor configured to provide feedback on the blade angle of the propeller blades by detecting a relative movement between the feedback ring and the at least one sensor, and at least one shielding element provided between the feedback ring and the propeller, the at least one shielding element configured to shield the feedback ring from electromagnetism.Type: ApplicationFiled: May 21, 2021Publication date: September 16, 2021Inventors: Joseph Ernesto Marone, Ella Yakobov, Ian Farrell, Olivier Basse, Martin Dobson, Martin Clermont, Marc Lavoie
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Patent number: 11046422Abstract: A blade angle feedback ring assembly for an aircraft propeller rotatable about a longitudinal axis and having an adjustable blade angle is provided. A feedback ring is coupled to the propeller to rotate therewith and to move along a longitudinal axis with adjustment of the blade angle. A plurality of rods are coupled to the feedback ring and extending along a direction substantially parallel to the longitudinal axis, the rods configured to support the feedback ring for longitudinal sliding movement along the longitudinal axis with adjustment of the blade angle. At least one shielding element is provided between the feedback ring and the propeller for shielding the feedback ring from electromagnetism.Type: GrantFiled: July 16, 2018Date of Patent: June 29, 2021Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Joseph Ernesto Marone, Ella Yakobov, Ian Farrell, Olivier Basse, Martin Dobson, Marc Lavoie
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Publication number: 20200017195Abstract: A blade angle feedback ring assembly for an aircraft engine propeller having adjustable angle blades is provided. The feedback ring assembly comprises a feedback ring coupled to rotate with the propeller, the engine configured such that a first electrically-conductive path is defined between the propeller and the engine via the feedback ring, and an electric current conduction element provided between the propeller and the engine to define a second electrically-conductive path between the propeller and the engine in parallel to the first path, the second electrically-conductive path configured with a lower electrical resistance to conduction between the propeller and the engine than the first electrically-conductive path.Type: ApplicationFiled: July 16, 2018Publication date: January 16, 2020Inventors: Joseph Ernesto MARONE, Olivier BASSE, Martin DOBSON, Martin CLERMONT, Marc LAVOIE
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Publication number: 20200017234Abstract: A blade angle feedback ring assembly for an aircraft propeller rotatable about a longitudinal axis and having an adjustable blade angle is provided. A feedback ring is coupled to the propeller to rotate therewith and to move along a longitudinal axis with adjustment of the blade angle. A plurality of rods are coupled to the feedback ring and extending along a direction substantially parallel to the longitudinal axis, the rods configured to support the feedback ring for longitudinal sliding movement along the longitudinal axis with adjustment of the blade angle. At least one shielding element is provided between the feedback ring and the propeller for shielding the feedback ring from electromagnetism.Type: ApplicationFiled: July 16, 2018Publication date: January 16, 2020Inventors: Joseph Ernesto Marone, Ella Yakobov, Ian Farrell, Olivier Basse, Martin Dobson, Marc Lavoie
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Patent number: 6699839Abstract: Mutacin are bactericidal substances of proteinaceous natures produced by Streptococcus mutans. Lantibiotics are antibacterial substances containing posttranslationnally modified amino acids such as lanthionine. The present invention teaches a simple method of purifying mutacin B-Ny266 from Streptococcus mutans strain Ny266 to homogeneity. The present invention further teaches the primary amino acid sequence of mutacin B-Ny266 as well as its proposed modified structure. Further, the present invention teaches compositions comprising mutacin B-Ny266 as well as methods for the treatment and/or prophylaxy of bacterial infections comprising an administration of a suitable dose of composition comprising mutacin B-Ny266.Type: GrantFiled: October 19, 2000Date of Patent: March 2, 2004Assignee: Universite LavalInventors: Marc Lavoie, Marilaine Mota-Meira, Christophe Lacroix, Gisèle Lapointe
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Patent number: 6218362Abstract: Mutacin are bactericidal substances of proteinaceous natures produced by Streptococcus mutans. Lantibiotics are antibacterial substances containing posttranslationnally modified amino acids such as lanthionine. The present invention teaches a simple method of purifying mutacin B-Ny266 from Streptococcus mutans strain Ny266 to homogeneity. The present invention further teaches the primary amino acid sequence of mutacin B-Ny266 as well as its proposed modified structure. Further, the present invention teaches compositions comprising mutacin B-Ny266 as well as methods for the treatment and/or prophylaxy of bacterial infections comprising an administration of a suitable dose of composition comprising mutacin B-Ny266.Type: GrantFiled: September 8, 1997Date of Patent: April 17, 2001Assignee: Universite LavalInventors: Marc Lavoie, Marilaine Mota-Meira, Christophe Lacroix, Gisèle LaPointe