Patents by Inventor Domenico Di Florio
Domenico Di Florio 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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Publication number: 20240102395Abstract: A stator vane for a gas turbine stator vane stage is provided that includes an airfoil having leading and trailing edges, a vane tip, suction and pressure side surfaces, and at least one aero passage. The leading and trailing edges are chordwise spaced apart. The vane tip is spanwise spaced apart from a radial base end. The suction side surface extends chordwise between the leading and trailing edges, and extends spanwise between the radial base end and the vane tip. The pressure side surface extends chordwise between the leading and trailing edges, and extends spanwise between the radial base end and the vane tip. The at least one aero passage extends through the airfoil between the suction and pressure side surfaces, and is disposed proximate and spanwise separated from the vane tip. The stator vane is configured to be cantilevered with the vane tip being unsupported.Type: ApplicationFiled: September 27, 2022Publication date: March 28, 2024Inventors: Nicola Houle, Domenico Di Florio
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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: 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: 11199096Abstract: A turbomachine airfoil element comprises an airfoil having: an inboard end; an outboard end; a leading edge; a trailing edge; a pressure side; and a suction side. A span between the inboard end and the outboard end is 1.75-2.20 inches. A chord length at 50% span is 1.05-1.35 inches. At least two of: a first mode resonance frequency is 2400±10% Hz; a second mode resonance frequency is 4950±10% Hz; a third mode resonance frequency is 7800±10% Hz; a fourth mode resonance frequency is 8700±10% Hz; and a fifth mode resonance frequency is 12500±10% Hz.Type: GrantFiled: January 15, 2018Date of Patent: December 14, 2021Assignee: Raytheon Technologies CorporationInventors: Michael Leslie Clyde Papple, David A. Niezelski, Daniel Lecuyer, XingYun Haggard, Domenico Di Florio, Francois Caron, John R. Battye, Panagiota Tsifourdaris, Ghislain Plante, Timothy J. Jennings, Rene Paquet
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Patent number: 10767565Abstract: A system comprises a pipe defining a fluid passage, the pipe having a first rate of thermal expansion. A housing defines an opening for receiving an end of the pipe for fluid circulation between the fluid passage and an interior of the housing, the housing having a second rate of thermal expansion lesser than the first rate of thermal expansion, at least one annular gap defined between a periphery of the opening and the end of the pipe when the system is below a safety condition threshold temperature. Seal(s) seal the annular gap, wherein the pipe and the housing are configured and the first and second rates of thermal expansion are selected so that, when the system exceeds the safety condition threshold temperature, the end of the pipe contacts the periphery of the opening by thermal expansion to seal the annular gap independent of the at least one seal.Type: GrantFiled: August 18, 2016Date of Patent: September 8, 2020Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Domenico Di Florio, Eric Hosking
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Publication number: 20180051634Abstract: A system comprises a pipe defining a fluid passage, the pipe having a first rate of thermal expansion. A housing defines an opening for receiving an end of the pipe for fluid circulation between the fluid passage and an interior of the housing, the housing having a second rate of thermal expansion lesser than the first rate of thermal expansion, at least one annular gap defined between a periphery of the opening and the end of the pipe when the system is below a safety condition threshold temperature. Seal(s) seal the annular gap, wherein the pipe and the housing are configured and the first and second rates of thermal expansion are selected so that, when the system exceeds the safety condition threshold temperature, the end of the pipe contacts the periphery of the opening by thermal expansion to seal the annular gap independent of the at least one seal.Type: ApplicationFiled: August 18, 2016Publication date: February 22, 2018Inventors: Domenico DI FLORIO, Eric HOSKING
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Patent number: 9822644Abstract: A rotor blade vibration damper for a gas turbine engine includes an elongated damper body including a top portion extending longitudinally between a front end and a rear end. The top portion has a width defined between spaced apart lateral sides and is substantially flat between the front and rear ends and between the lateral sides such as to define a longitudinal plane within which the top portion lies. A front tab extends downwardly from the front end of the top portion relative to the longitudinal plane. The rear end of the top portion is flat and generally contained in the longitudinal plane. A pair of lateral tabs extends downwardly from each of said lateral sides of the top portion relative to the longitudinal plane.Type: GrantFiled: February 27, 2015Date of Patent: November 21, 2017Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Marc Tardif, Domenico Di Florio, Aldo Abate
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Publication number: 20160251963Abstract: A rotor blade vibration damper for a gas turbine engine includes an elongated damper body including a top portion extending longitudinally between a front end and a rear end. The top portion has a width defined between spaced apart lateral sides and is substantially flat between the front and rear ends and between the lateral sides such as to define a longitudinal plane within which the top portion lies. A front tab extends downwardly from the front end of the top portion relative to the longitudinal plane. The rear end of the top portion is flat and generally contained in the longitudinal plane. A pair of lateral tabs extends downwardly from each of said lateral sides of the top portion relative to the longitudinal plane.Type: ApplicationFiled: February 27, 2015Publication date: September 1, 2016Inventors: Marc TARDIF, Domenico DI FLORIO, Aldo ABATE
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Publication number: 20160177835Abstract: A gas turbine engine includes a combustor having a plurality of fuel nozzles arranged circumferentially equidistant from one another about a first center. The plurality of fuel nozzles produce a plurality of pressure pulses in a fluid contained in the combustor. A turbine section is disposed downstream of the combustor and receiving the fluid from the combustor. The turbine section includes a plurality of vanes arranged circumferentially equidistant from one another about a second center. When projecting the second center onto the first center, the plurality of vanes is angularly offset in a circumferential direction relative to the plurality of fuel nozzles of a predetermined amount. The offsetting positions the vanes in flowpaths of the pressure pulses generated by the plurality of fuel nozzles.Type: ApplicationFiled: December 22, 2014Publication date: June 23, 2016Inventors: Marc Tardif, Jacinthe Rondeau, Domenico Di Florio
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Patent number: 8591195Abstract: A turbine blade adapted for mounting to a turbine rotor includes a root portion, and an airfoil portion extending outward from the root portion and defining a blade tip at an outermost end thereof. The airfoil portion having a pressure side and a suction side opposite the pressure side, and including a stiffening rib disposed at the blade tip. The stiffening rib projects from the pressure side of the airfoil portion of the turbine blade.Type: GrantFiled: May 28, 2010Date of Patent: November 26, 2013Assignee: Pratt & Whitney Canada Corp.Inventors: Domenico Di Florio, Aldo Abate
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Publication number: 20110293436Abstract: A turbine blade comprising a root portion, and an airfoil portion extending outward from the root portion and defining a blade tip at an outermost end thereof. The airfoil portion having a pressure side and a suction side opposite the pressure side, and including a stiffening rib at the blade tip. The stiffening rib extends in a substantially tangential direction on the pressure side of the airfoil portion of the turbine blade.Type: ApplicationFiled: May 28, 2010Publication date: December 1, 2011Inventors: Domenico Di Florio, Aldo Abate