Patents by Inventor Ian A. Macfarlane
Ian A. Macfarlane 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: 11933180Abstract: A labyrinth seal assembly comprising: an outer seal having a radially inner cavity surface, and an axial cavity surface inward of the radially inner cavity surface; a floating seal received by the outer seal so as to be movable in a radial direction relative to the outer seal, the floating seal having a radially outer seal surface spaced inwardly from the radially inner cavity surface, a radially inner surface inward of the radially outer seal surface, and an axial seal surface bearing against the axial cavity surface; and an inner seal received by the floating seal, the inner seal having a radially outer surface spaced inwardly from the radially inner surface, a first one of the radially outer surface and the radially inner surface defining one tooth projecting toward a second one of the radially outer surface and the radially inner surface to inward of the axial seal surface.Type: GrantFiled: December 16, 2021Date of Patent: March 19, 2024Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Ian Macfarlane, Eric Durocher, Guy Lefebvre
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Publication number: 20230193774Abstract: A labyrinth seal assembly comprising: an outer seal having a radially inner cavity surface, and an axial cavity surface inward of the radially inner cavity surface; a floating seal received by the outer seal so as to be movable in a radial direction relative to the outer seal, the floating seal having a radially outer seal surface spaced inwardly from the radially inner cavity surface, a radially inner surface inward of the radially outer seal surface, and an axial seal surface bearing against the axial cavity surface; and an inner seal received by the floating seal, the inner seal having a radially outer surface spaced inwardly from the radially inner surface, a first one of the radially outer surface and the radially inner surface defining one tooth projecting toward a second one of the radially outer surface and the radially inner surface to inward of the axial seal surface.Type: ApplicationFiled: December 16, 2021Publication date: June 22, 2023Inventors: Ian MACFARLANE, Eric DUROCHER, Guy LEFEBVRE
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Publication number: 20230138749Abstract: An apparatus is provided for a gas turbine engine. This gas turbine engine apparatus includes a hot section structure of the gas turbine engine. The hot section structure is configured with a plurality of surfaces respectively forming boundaries of a gas path through the hot section structure. The surfaces include a first surface and a second surface. The hot section structure includes metal and thermal barrier material. The first surface is formed by the metal. The second surface is formed by the thermal barrier material.Type: ApplicationFiled: October 29, 2021Publication date: May 4, 2023Inventors: Eric Durocher, Ian MacFarlane, Guy Lefebvre
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Patent number: 11338400Abstract: A method of manufacturing a compressor stator having: a first stator blade with a first leading edge and a first trailing edge; a second stator blade disposed a circumferential distance from the first stator blade, the second stator blade having a second leading edge disposed an axial distance from the first leading edge and a second trailing edge disposed an axial distance from the first trailing edge; the method comprising: using additive manufacturing to deposit and fuse together progressive layers of metal material commencing at a substrate to form the first stator blade, the second stator blade, at least one intermediate support structure disposed between the first stator blade and the second stator blade, and at least one primary support structure disposed between the substrate and at least one of: the first stator blade; and the second stator blade; and removing the primary support structure and the intermediate support structure.Type: GrantFiled: May 12, 2021Date of Patent: May 24, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Ian A. MacFarlane, Peter Townsend, Hong Yu
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Publication number: 20220003354Abstract: A gas turbine engine includes a casing including a plurality of interconnected casing segments defining an outer surface of the casing. One of the casing segments is a gearbox segment enclosing a gearbox and having a gearbox flange extending radially outwardly from the outer surface of the casing. The engine includes a bearing housing enclosing at least one bearing and having an annular body with an inner segment disposed within the casing. The annular body having an extension segment extending radially outwardly from the inner segment to a bearing housing flange disposed radially-outwardly of the outer surface of the casing. The bearing housing flange is engageable with the gearbox flange to removably mount the gearbox segment to the bearing housing.Type: ApplicationFiled: September 20, 2021Publication date: January 6, 2022Inventor: Ian A. MACFARLANE
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Patent number: 11168828Abstract: A gas turbine engine includes a casing including a plurality of interconnected casing segments defining an outer surface of the casing. One of the casing segments is a gearbox segment enclosing a gearbox and having a gearbox flange extending radially outwardly from the outer surface of the casing. The engine includes a bearing housing enclosing at least one bearing and having an annular body with an inner segment disposed within the casing. The annular body having an extension segment extending radially outwardly from the inner segment to a bearing housing flange disposed radially-outwardly of the outer surface of the casing. The bearing housing flange is engageable with the gearbox flange to removably mount the gearbox segment to the bearing housing.Type: GrantFiled: May 2, 2017Date of Patent: November 9, 2021Assignee: PRATT & WHITNEY CANADA CORP.Inventor: Ian A. Macfarlane
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Publication number: 20210260706Abstract: A method of manufacturing a compressor stator having: a first stator blade with a first leading edge and a first trailing edge; a second stator blade disposed a circumferential distance from the first stator blade, the second stator blade having a second leading edge disposed an axial distance from the first leading edge and a second trailing edge disposed an axial distance from the first trailing edge; the method comprising: using additive manufacturing to deposit and fuse together progressive layers of metal material commencing at a substrate to form the first stator blade, the second stator blade, at least one intermediate support structure disposed between the first stator blade and the second stator blade, and at least one primary support structure disposed between the substrate and at least one of: the first stator blade; and the second stator blade; and removing the primary support structure and the intermediate support structure.Type: ApplicationFiled: May 12, 2021Publication date: August 26, 2021Inventors: Ian A. MACFARLANE, Peter TOWNSEND, Hong YU
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Patent number: 11033992Abstract: A method of manufacturing a compressor stator having: a first stator blade with a first leading edge and a first trailing edge; a second stator blade disposed a circumferential distance from the first stator blade, the second stator blade having a second leading edge disposed an axial distance from the first leading edge and a second trailing edge disposed an axial distance from the first trailing edge; the method comprising: using additive manufacturing to deposit and fuse together progressive layers of metal material commencing at a substrate to form the first stator blade, the second stator blade, at least one intermediate support structure disposed between the first stator blade and the second stator blade, and at least one primary support structure disposed between the substrate and at least one of: the first stator blade; and the second stator blade; and removing the primary support structure and the intermediate support structure.Type: GrantFiled: October 5, 2018Date of Patent: June 15, 2021Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Ian A. Macfarlane, Peter Townsend, Hong Yu
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Patent number: 10975726Abstract: A sleeve is provided for supplying lubricant to an inter-shaft bearing mounted between co-axially mounted inner and outer shafts of a gas turbine engine. The sleeve has a sleeve annular outer surface and a sleeve annular inner surface. At least one lubricant supply connecting member extends from the sleeve outer surface for connection to a lubricant supply. At least one sleeve channel fluidly links the sleeve annular inner surface to the lubricant supply connecting member.Type: GrantFiled: January 15, 2019Date of Patent: April 13, 2021Assignee: PRATT & WHITNEY CANADA CORP.Inventor: Ian A. MacFarlane
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Patent number: 10746188Abstract: A multi-spool gas turbine engine comprises a low pressure (LP) spool and a high pressure (HP) spool. The LP spool has an LP shaft for transferring a torque from an LP turbine to an LP compressor. The HP spool has an HP shaft for transferring a torque from an HP turbine to an HP compressor. The LP shaft is coaxially mounted inside the HP shaft. An inter-shaft bearing is mounted radially between the LP shaft and the HP shaft. The inter-shaft bearing is disposed axially between the HP compressor and the LP compressor.Type: GrantFiled: April 10, 2017Date of Patent: August 18, 2020Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Ian A. MacFarlane, Sean Powers, Martin Poulin, Jean-Jacques Forest
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Publication number: 20200116041Abstract: A low pressure compressor section of a gas turbine engine includes low pressure compressor stages spaced apart along an axis of rotation of the low pressure compressor section. The low pressure compressor section includes at least one of a fluid conduit extending between an air inlet of the gas turbine engine and the low pressure compression stages. The fluid conduit having at least one flow diverter displaceable between a first position and a second position to modulate air through the low pressure compressor stages. And/or a compressor stage disabler is engageable with at least one of the low pressure compressor stages and configured to reduce a rotation thereof.Type: ApplicationFiled: October 11, 2018Publication date: April 16, 2020Inventors: Ghislain PLANTE, Ian MACFARLANE
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Publication number: 20200108473Abstract: A method of manufacturing a compressor stator having: a first stator blade with a first leading edge and a first trailing edge; a second stator blade disposed a circumferential distance from the first stator blade, the second stator blade having a second leading edge disposed an axial distance from the first leading edge and a second trailing edge disposed an axial distance from the first trailing edge; the method comprising: using additive manufacturing to deposit and fuse together progressive layers of metal material commencing at a substrate to form the first stator blade, the second stator blade, at least one intermediate support structure disposed between the first stator blade and the second stator blade, and at least one primary support structure disposed between the substrate and at least one of: the first stator blade; and the second stator blade; and removing the primary support structure and the intermediate support structure.Type: ApplicationFiled: October 5, 2018Publication date: April 9, 2020Inventors: Ian A. MACFARLANE, Peter TOWNSEND, Hong YU
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Publication number: 20200080435Abstract: 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: ApplicationFiled: September 10, 2018Publication date: March 12, 2020Inventors: Eric DUROCHER, Ian A. MACFARLANE, John PIETROBON, Eric HO, Jamal ZEINALOV
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Patent number: 10445117Abstract: According to one example, a method includes, with an analytics component, receiving performance data from a Virtual Network Function (VNF), the VNF including a plurality of VNF components running on a plurality of virtual machines. The method further includes, with the analytics component, performing an analytics function on the performance data. The method further includes, with the analytics component, based on the analytics function determining a prediction event in response to determining that a set of conditions within the performance data is present. The method further includes, with the analytics component, notifying a VNF manager of the prediction event.Type: GrantFiled: February 24, 2017Date of Patent: October 15, 2019Assignee: GENBAND US LLCInventors: Paul Miller, Ian Macfarlane
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Patent number: 10385785Abstract: A radial air inlet for a gas turbine engine. The air inlet has an inlet duct defined between two axially-spaced radially-extending annular walls and has a plurality of circumferentially-spaced axially-extending struts extending between the annular walls adjacent a radially-outer portion of the air inlet. At least one of the struts has an internal passage extending between a first opening in a forward end of the strut and a second opening in an aft end of the strut, the first and second openings being axially spaced apart. A transmission shaft extends through the internal passage of said strut.Type: GrantFiled: July 17, 2017Date of Patent: August 20, 2019Assignee: Pratt & Whitney Canada Corp.Inventors: Ian MacFarlane, Lazar Mitrovic
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Publication number: 20190145276Abstract: A sleeve is provided for supplying lubricant to an inter-shaft bearing mounted between co-axially mounted inner and outer shafts of a gas turbine engine. The sleeve has a sleeve annular outer surface and a sleeve annular inner surface. At least one lubricant supply connecting member extends from the sleeve outer surface for connection to a lubricant supply. At least one sleeve channel fluidly links the sleeve annular inner surface to the lubricant supply connecting member.Type: ApplicationFiled: January 15, 2019Publication date: May 16, 2019Inventor: Ian A. MACFARLANE
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Patent number: 10215052Abstract: A sleeve is provided for supplying lubricant to an inter-shaft bearing mounted between co-axially mounted inner and outer shafts of a gas turbine engine. The sleeve has a sleeve annular outer surface and a sleeve annular inner surface. At least one lubricant supply connecting member extends from the sleeve outer surface for connection to a lubricant supply. At least one sleeve channel fluidly links the sleeve annular inner surface to the lubricant supply connecting member.Type: GrantFiled: March 14, 2017Date of Patent: February 26, 2019Assignee: PRATT & WHITNEY CANADA CORP.Inventor: Ian A. MacFarlane
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Publication number: 20190017442Abstract: A radial air inlet for a gas turbine engine. The air inlet has an inlet duct defined between two axially-spaced radially-extending annular walls and has a plurality of circumferentially-spaced axially-extending struts extending between the annular walls adjacent a radially-outer portion of the air inlet. At least one of the struts has an internal passage extending between a first opening in a forward end of the strut and a second opening in an aft end of the strut, the first and second openings being axially spaced apart. A transmission shaft extends through the internal passage of said strut.Type: ApplicationFiled: July 17, 2017Publication date: January 17, 2019Inventors: Ian MACFARLANE, Lazar MITROVIC
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Publication number: 20180320811Abstract: A gas turbine engine includes a casing including a plurality of interconnected casing segments defining an outer surface of the casing. One of the casing segments is a gearbox segment enclosing a gearbox and having a gearbox flange extending radially outwardly from the outer surface of the casing. The engine includes a bearing housing enclosing at least one bearing and having an annular body with an inner segment disposed within the casing. The annular body having an extension segment extending radially outwardly from the inner segment to a bearing housing flange disposed radially-outwardly of the outer surface of the casing. The bearing housing flange is engageable with the gearbox flange to removably mount the gearbox segment to the bearing housing.Type: ApplicationFiled: May 2, 2017Publication date: November 8, 2018Inventor: Ian A. MACFARLANE
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Publication number: 20180266274Abstract: A sleeve is provided for supplying lubricant to an inter-shaft bearing mounted between co-axially mounted inner and outer shafts of a gas turbine engine. The sleeve has a sleeve annular outer surface and a sleeve annular inner surface. At least one lubricant supply connecting member extends from the sleeve outer surface for connection to a lubricant supply. At least one sleeve channel fluidly links the sleeve annular inner surface to the lubricant supply connecting member.Type: ApplicationFiled: March 14, 2017Publication date: September 20, 2018Inventor: Ian A. MACFARLANE