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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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
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Publication number: 20170074170Abstract: 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: ApplicationFiled: November 23, 2016Publication date: March 16, 2017Inventors: Nigel DAVENPORT, Yen-Wen WANG
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Publication number: 20170067395Abstract: 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: November 16, 2016Publication date: March 9, 2017Inventors: Jean THOMASSIN, Nigel DAVENPORT, Eugene GEKHT
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Patent number: 9534785Abstract: 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: August 26, 2014Date of Patent: January 3, 2017Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Nigel Davenport, Yen-Wen Wang
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Patent number: 9528434Abstract: 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: January 25, 2013Date of Patent: December 27, 2016Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Jean Thomassin, Nigel Davenport, Eugene Gekht
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Publication number: 20160320064Abstract: 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 14, 2016Publication date: November 3, 2016Inventors: Eduardo HAWIE, Nigel Davenport
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Patent number: 9441546Abstract: The combustor has a laser ignitor mounted to the casing, remotely from the liner of the combustion chamber. The laser ignitor has an igniter beam path for igniting the fuel and air mixture in the combustion chamber, the igniter beam path extending at least partially across the air plenum surrounding the liner and into the combustion chamber through a corresponding beam path aperture provided in the liner.Type: GrantFiled: February 26, 2013Date of Patent: September 13, 2016Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Nigel Davenport, Bhawan Patel, Eduardo Hawie
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Patent number: 9416972Abstract: 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: GrantFiled: December 7, 2011Date of Patent: August 16, 2016Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Eduardo Hawie, Nigel Davenport
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Publication number: 20160097537Abstract: 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: ApplicationFiled: October 3, 2014Publication date: April 7, 2016Inventors: Yen-Wen WANG, Nigel Davenport, Eduardo Hawie
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Publication number: 20160097538Abstract: 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: ApplicationFiled: October 3, 2014Publication date: April 7, 2016Inventors: Yen-Wen WANG, Nigel DAVENPORT
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Publication number: 20160097536Abstract: 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: October 3, 2014Publication date: April 7, 2016Inventors: Yen-Wen WANG, Nigel DAVENPORT, Eduardo HAWIE
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Publication number: 20160084503Abstract: 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: ApplicationFiled: September 24, 2014Publication date: March 24, 2016Inventors: Eduardo HAWIE, Nigel DAVENPORT, Yen-Wen WANG
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Publication number: 20160061448Abstract: 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: ApplicationFiled: August 26, 2014Publication date: March 3, 2016Inventors: NIGEL DAVENPORT, YEN-WEN WANG
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Patent number: 9243802Abstract: A combustor for a gas turbine engine comprises an inner annular liner and an outer annular liner. A first and a second combustion stages are defined between the liners, each said combustion stage having a plurality of fuel injection bores distributed in a liner wall defining the respective stage. Valves at the fuel injection bores of one of the combustion stages, the valves each defining an air passage from an exterior to an interior of the combustion stage, the valves each having an actuatable member for adjusting a size of a respective air passage for air staging the combustor.Type: GrantFiled: December 7, 2011Date of Patent: January 26, 2016Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Eduardo Hawie, Nigel Davenport
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Patent number: 9194586Abstract: A combustor for a gas turbine engine comprises an inner annular liner and an outer annular liner. First and second combustion stages are defined between the liners. Each combustion stage has a plurality of fuel injection bores distributed in a liner wall defining the respective stage. A lobed mixer extends into the combustor, the lobed mixer arranged to receive combustion gases from each combustion stage for mixing flows of said combustion gases.Type: GrantFiled: December 7, 2011Date of Patent: November 24, 2015Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Eduardo Hawie, Nigel Davenport
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Publication number: 20150240710Abstract: 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: May 7, 2015Publication date: August 27, 2015Inventors: Jean THOMASSIN, Nigel DAVENPORT, Eugene GEKHT
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Patent number: 9038594Abstract: A Wankel engine having an insert in the 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 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: October 14, 2011Date of Patent: May 26, 2015Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Jean Thomassin, Nigel Davenport, Eugene Gekht
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Publication number: 20140237989Abstract: The combustor has a laser ignitor mounted to the casing, remotely from the liner of the combustion chamber. The laser ignitor has an igniter beam path for igniting the fuel and air mixture in the combustion chamber, the igniter beam path extending at least partially across the air plenum surrounding the liner and into the combustion chamber through a corresponding beam path aperture provided in the liner.Type: ApplicationFiled: February 26, 2013Publication date: August 28, 2014Applicant: PRATT & WHITNEY CANADA CORP.Inventors: NIGEL DAVENPORT, BHAWAN PATEL, EDUARDO HAWIE
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Publication number: 20130145767Abstract: A combustor for a gas turbine engine comprises an inner annular liner and an outer annular liner. First and second combustion stages are defined between the liners. Each combustion stage has a plurality of fuel injection bores distributed in a liner wall defining the respective stage. A lobed mixer extends into the combustor, the lobed mixer arranged to receive combustion gases from each combustion stage for mixing flows of said combustion gases.Type: ApplicationFiled: December 7, 2011Publication date: June 13, 2013Inventors: Eduardo Hawie, Nigel Davenport
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Publication number: 20130145766Abstract: 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: December 7, 2011Publication date: June 13, 2013Inventors: Eduardo HAWIE, Nigel Davenport