Patents by Inventor Nigel Davenport
Nigel Davenport 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: 20210348764Abstract: A combustor for a gas turbine engine comprises an inner annular liner wall and an outer annular liner wall cooperating to form a combustion chamber of the combustor. A first dome wall has a circumferential array of first fuel injection bores. A second dome has a circumferential array of second fuel injection bores. An intermediate wall extends between the first dome wall and the second dome wall. A first combustion stage is defined by the inner liner wall forward end, the first dome wall and the intermediate wall. A second combustion stage is defined at least by the outer liner wall forward end, the second dome wall and the intermediate wall, the first combustion stage communicating with the first fuel injection bores, the second combustion stage communicating with the second fuel injection bores.Type: ApplicationFiled: July 23, 2021Publication date: November 11, 2021Inventors: Eduardo Hawie, Nigel Davenport
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Patent number: 10801415Abstract: A seal for sealing a combustor heat shield against an interior surface of a combustor shell, the seal comprising: a first sealing surface on the interior surface of the combustor shell; and a second sealing surface on a rail on an edge of a heat shield, wherein each of the first and second sealing surfaces include first and second projections defining a non-linear leakage path between the projections.Type: GrantFiled: November 23, 2016Date of Patent: October 13, 2020Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Nigel Davenport, Yen-Wen Wang
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Patent number: 10697365Abstract: A rotary engine having an insert in a peripheral wall of the stator body, the insert being made of a material having a greater heat resistance than that of the peripheral wall, having a subchamber defined therein and having an inner surface, the subchamber communicating with the cavity through at least one opening defined in the inner surface and having a shape forming a reduced cross-section adjacent the opening, a pilot fuel injector having a tip received in the subchamber, an ignition element having a tip received in the subchamber, and a main fuel injector extending through the stator body and having a tip communicating with the cavity at a location spaced apart from the insert. The subchamber has a volume corresponding to from 5% to 25% of a sum of the minimum volume and the volume of the subchamber. A method of injecting heavy fuel into a Wankel engine is also discussed.Type: GrantFiled: October 23, 2018Date of Patent: June 30, 2020Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Jean Thomassin, Nigel Davenport, Eugene Gekht
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Patent number: 10598374Abstract: A method of inducing swirl in pressurized air flowing through an air passageway of a fuel nozzle of a gas turbine engine includes inducing swirl in the pressurized air at an exit of the air passageway, by directing the pressurised air through helicoidal grooves formed at a downstream end of the air passageway. The swirling pressurized air exiting the air passageway is then directed into a mixing zone at a downstream end of the fuel nozzle.Type: GrantFiled: August 3, 2017Date of Patent: March 24, 2020Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Yen-Wen Wang, Nigel Davenport
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Patent number: 10578012Abstract: A non-Wankel rotary engine having an insert in the peripheral wall of the outer body, the insert being made of a material having a greater heat resistance than that of the peripheral wall, having a subchamber defined therein and having an inner surface bordering the cavity, the subchamber communicating with the cavity through at least one opening defined in the inner surface and having a shape forming a reduced cross-section adjacent the opening, a pilot fuel injector having a tip received in the subchamber, an ignition element having a tip received in the subchamber, and a main fuel injector extending through the housing and having a tip communicating with the cavity at a location spaced apart from the insert.Type: GrantFiled: March 1, 2018Date of Patent: March 3, 2020Assignee: Pratt & Whitney Canada Corp.Inventors: Jean Thomassin, Nigel Davenport, Eugene Gekht
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Patent number: 10557407Abstract: A rotary engine including a rotor sealingly received within an internal cavity of an outer body to define a plurality of combustion chambers having a variable volume, a pilot subchamber located in a wall of the outer body, the pilot subchamber in fluid communication with the internal cavity via at least two spaced apart transfer holes defining a flow restriction between the pilot subchamber and the internal cavity, a pilot fuel injector in fluid communication with the pilot subchamber, an ignition element configured for igniting fuel in the pilot subchamber, and a main fuel injector extending through the stator body and communicating with the cavity at a location spaced apart from the pilot subchamber. A method of combusting fuel in a rotary engine is also discussed.Type: GrantFiled: November 29, 2017Date of Patent: February 11, 2020Assignee: Pratt & Whitney Canada Corp.Inventors: Serge Dussault, Andre Julien, Michael Lanktree, Edwin Schulz, Jean Thomassin, Nigel Davenport, Eugene Gekht
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Patent number: 10364988Abstract: A method for delivering fuel from a fuel nozzle of a combustor of a gas turbine engine includes directing fuel from a fuel source through a flow splitter to provide at least two concentric fuel flows, filming the concentric two fuel flows on concentrically arranged inwardly facing filming surfaces that are disposed downstream of the flow splitter, and atomizing the concentric fuel flows into a core air flow.Type: GrantFiled: October 19, 2017Date of Patent: July 30, 2019Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Eduardo David Hawie, Nigel Davenport, Yen-Wen Wang
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Publication number: 20190226681Abstract: A method of delivering fuel from a fuel nozzle of a gas turbine engine includes carrying by a fuel passageway of the fuel nozzle a film of pressurised fuel, the fuel passageway being disposed radially outwardly from an air passageway carrying a flow of pressurised air, and directing the film of pressurised fuel onto an inside surface of an exit lip of an outer wall of the fuel passageway and thinning the film of pressurised fuel as it travels therealong. The exit lip generally increases in diameter as it extends downstream.Type: ApplicationFiled: April 3, 2019Publication date: July 25, 2019Inventors: Yen-Wen WANG, Nigel DAVENPORT, Eduardo HAWIE
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Patent number: 10317083Abstract: A fuel nozzle for a combustor of a gas turbine engine includes a body defining an axial direction and a radial direction, an air passageway defined axially in the body, and a fuel passageway defined axially in the body radially outwardly from the air passageway. The fuel passageway has an outer wall including an exit lip at a downstream portion of the outer wall. The lip generally increases in diameter as it extends downstream.Type: GrantFiled: October 3, 2014Date of Patent: June 11, 2019Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Yen-Wen Wang, Nigel Davenport, Eduardo Hawie
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Publication number: 20190055882Abstract: A rotary engine having an insert in a peripheral wall of the stator body, the insert being made of a material having a greater heat resistance than that of the peripheral wall, having a subchamber defined therein and having an inner surface, the subchamber communicating with the cavity through at least one opening defined in the inner surface and having a shape forming a reduced cross-section adjacent the opening, a pilot fuel injector having a tip received in the subchamber, an ignition element having a tip received in the subchamber, and a main fuel injector extending through the stator body and having a tip communicating with the cavity at a location spaced apart from the insert. The subchamber has a volume corresponding to from 5% to 25% of a sum of the minimum volume and the volume of the subchamber. A method of injecting heavy fuel into a Wankel engine is also discussed.Type: ApplicationFiled: October 23, 2018Publication date: February 21, 2019Inventors: Jean THOMASSIN, Nigel DAVENPORT, Eugene GEKHT
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Patent number: 10125676Abstract: A rotary engine having an insert in a peripheral wall of the stator body, the insert being made of a material having a greater heat resistance than that of the peripheral wall, having a subchamber defined therein and having an inner surface, the subchamber communicating with the cavity through at least one opening defined in the inner surface and having a shape forming a reduced cross-section adjacent the opening, a pilot fuel injector having a tip received in the subchamber, an ignition element having a tip received in the subchamber, and a main fuel injector extending through the stator body and having a tip communicating with the cavity at a location spaced apart from the insert. The subchamber has a volume corresponding to from 5% to 25% of a sum of the minimum volume and the volume of the subchamber. A method of injecting heavy fuel into a Wankel engine is also discussed.Type: GrantFiled: May 7, 2015Date of Patent: November 13, 2018Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Jean Thomassin, Nigel Davenport, Eugene Gekht
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Publication number: 20180187593Abstract: A non-Wankel rotary engine having an insert in the peripheral wall of the outer body, the insert being made of a material having a greater heat resistance than that of the peripheral wall, having a subchamber defined therein and having an inner surface bordering the cavity, the subchamber communicating with the cavity through at least one opening defined in the inner surface and having a shape forming a reduced cross-section adjacent the opening, a pilot fuel injector having a tip received in the subchamber, an ignition element having a tip received in the subchamber, and a main fuel injector extending through the housing and having a tip communicating with the cavity at a location spaced apart from the insert.Type: ApplicationFiled: March 1, 2018Publication date: July 5, 2018Inventors: Jean THOMASSIN, Nigel DAVENPORT, Eugene GEKHT
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Patent number: 10006358Abstract: A non-Wankel rotary engine having an insert in the peripheral wall of the outer body, the insert being made of a material having a greater heat resistance than that of the peripheral wall, having a subchamber defined therein and having an inner surface bordering the cavity, the subchamber communicating with the cavity through at least one opening defined in the inner surface and having a shape forming a reduced cross-section adjacent the opening, a pilot fuel injector having a tip received in the subchamber, an ignition element having a tip received in the subchamber, and a main fuel injector extending through the housing and having a tip communicating with the cavity at a location spaced apart from the insert.Type: GrantFiled: November 16, 2016Date of Patent: June 26, 2018Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Jean Thomassin, Nigel Davenport, Eugene Gekht
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Publication number: 20180080371Abstract: A rotary engine including a rotor sealingly received within an internal cavity of an outer body to define a plurality of combustion chambers having a variable volume, a pilot subchamber located in a wall of the outer body, the pilot subchamber in fluid communication with the internal cavity via at least two spaced apart transfer holes defining a flow restriction between the pilot subchamber and the internal cavity, a pilot fuel injector in fluid communication with the pilot subchamber, an ignition element configured for igniting fuel in the pilot subchamber, and a main fuel injector extending through the stator body and communicating with the cavity at a location spaced apart from the pilot subchamber. A method of combusting fuel in a rotary engine is also discussed.Type: ApplicationFiled: November 29, 2017Publication date: March 22, 2018Inventors: Serge DUSSAULT, Andre JULIEN, Michael LANKTREE, Edwin SCHULZ, Jean THOMASSIN, Nigel DAVENPORT, Eugene GEKHT
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Publication number: 20180058694Abstract: A method for delivering fuel from a fuel nozzle of a combustor of a gas turbine engine includes directing fuel from a fuel source through a flow splitter to provide at least two concentric fuel flows, filming the concentric two fuel flows on concentrically arranged inwardly facing filming surfaces that are disposed downstream of the flow splitter, and atomizing the concentric fuel flows into a core air flow.Type: ApplicationFiled: October 19, 2017Publication date: March 1, 2018Inventors: Eduardo David HAWIE, Nigel DAVENPORT, Yen-Wen WANG
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Publication number: 20170370590Abstract: A fuel nozzle for a combustor of a gas turbine engine includes a body defining an axial direction and a radial direction, an air passageway defined axially in the body, and a fuel passageway defined axially in the body radially outwardly from the air passageway. The fuel passageway has an outer wall including an exit lip at a downstream portion of the outer wall. The exit lip has a surface treatment including a swirl-inducing relief. A gas turbine engine and a method of inducing swirl in at least one of pressurised fuel and air exiting a fuel nozzle of a gas turbine engine are also presented.Type: ApplicationFiled: August 11, 2017Publication date: December 28, 2017Inventors: Yen-Wen WANG, Nigel DAVENPORT, Eduardo HAWIE
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Patent number: 9822980Abstract: A fuel nozzle for a combustor of a gas turbine engine includes a body defining an axial direction and a radial direction, a primary air passageway centrally defined axially in the body, and a plurality of concentrically-arranged nozzle tip projections disposed at a downstream portion of the body. Each of the plurality of nozzle tip projections has a radially inwardly facing fuel filming surface communicating with respective fuel passages. The fuel filming surfaces are disposed radially outwardly of an outlet of the primary air passageway. A method for delivering fuel from a fuel nozzle of a combustor of a gas turbine engine is also presented.Type: GrantFiled: September 24, 2014Date of Patent: November 21, 2017Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Eduardo Hawie, Nigel Davenport, Yen-Wen Wang
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Publication number: 20170328558Abstract: A method of inducing swirl in pressurized air flowing through an air passageway of a fuel nozzle of a gas turbine engine includes inducing swirl in the pressurized air at an exit of the air passageway, by directing the pressurised air through helicoidal grooves formed at a downstream end of the air passageway. The swirling pressurized air exiting the air passageway is then directed into a mixing zone at a downstream end of the fuel nozzle.Type: ApplicationFiled: August 3, 2017Publication date: November 16, 2017Inventors: Yen-Wen WANG, Nigel DAVENPORT
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Patent number: 9765974Abstract: A fuel nozzle for a combustor of a gas turbine engine includes a body defining an axial direction and a radial direction, an air passageway defined axially in the body, and a fuel passageway defined axially in the body radially outwardly from the air passageway. The fuel passageway has an outer wall including an exit lip at a downstream portion of the outer wall. The exit lip has a surface treatment including a swirl-inducing relief. A gas turbine engine and a method of inducing swirl in at least one of pressurised fuel and air exiting a fuel nozzle of a gas turbine engine are also presented.Type: GrantFiled: October 3, 2014Date of Patent: September 19, 2017Assignee: Pratt & Whitney Canada Corp.Inventors: Yen-Wen Wang, Nigel Davenport, Eduardo Hawie
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Patent number: 9752774Abstract: A fuel nozzle for a combustor of a gas turbine engine includes a body defining an axial direction and a radial direction, an air passageway defined axially in the body, and a fuel passageway defined axially in the body radially outwardly from the air passageway. The air passageway has a swirl-inducing relief defined at an exit lip of an outer wall of the air passageway. A gas turbine engine and a method of inducing swirl in an air passageway of a fuel nozzle of a gas turbine engine are also presented.Type: GrantFiled: October 3, 2014Date of Patent: September 5, 2017Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Yen-Wen Wang, Nigel Davenport