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公开(公告)号：US09822980B2
公开(公告)日：2017-11-21
申请号：US14494872
申请日：2014-09-24
发明人： Eduardo Hawie , Nigel Davenport , Yen-Wen Wang
CPC分类号： F23R3/28 , F23D11/107 , F23D2900/11101 , F23R3/10
摘要： 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.
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公开(公告)号：US09752774B2
公开(公告)日：2017-09-05
申请号：US14505787
申请日：2014-10-03
发明人： Yen-Wen Wang , Nigel Davenport
CPC分类号： F23D11/383 , F23D11/102 , F23D11/103 , F23D11/107 , F23D2900/14021 , F23R3/12 , F23R3/286
摘要： 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.
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公开(公告)号：US10598374B2
公开(公告)日：2020-03-24
申请号：US15667757
申请日：2017-08-03
发明人： Yen-Wen Wang , Nigel Davenport
摘要： 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.
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公开(公告)号：US10364988B2
公开(公告)日：2019-07-30
申请号：US15788092
申请日：2017-10-19
摘要： 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.
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公开(公告)号：US10184661B2
公开(公告)日：2019-01-22
申请号：US15995721
申请日：2018-06-01
发明人： Daniel Hayek , Jason Herborth , Yen-Wen Wang
摘要： A method and an apparatus for reducing airflow leakage between a combustor liner and a rail of a heat shield mounted to an inner surface of the combustor liner. The method comprises locally deforming the combustor liner in sealing engagement with the rail by applying a pressure on the outer surface of the combustor liner over the rail of the heat shield. A tool, such as a sealing clip, may be mounted in pressing engagement with the outer surface of the combustor liner to apply forces locally on the liner over the rail of the heat shield.
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公开(公告)号：US10801415B2
公开(公告)日：2020-10-13
申请号：US15360161
申请日：2016-11-23
发明人： Nigel Davenport , Yen-Wen Wang
摘要： 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.
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公开(公告)号：US10317083B2
公开(公告)日：2019-06-11
申请号：US14505778
申请日：2014-10-03
发明人： Yen-Wen Wang , Nigel Davenport , Eduardo Hawie
摘要： 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.
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公开(公告)号：US10012385B2
公开(公告)日：2018-07-03
申请号：US14455185
申请日：2014-08-08
发明人： Daniel Hayek , Jason Herborth , Yen-Wen Wang
CPC分类号： F23R3/002 , F23R3/60 , F23R2900/00012
摘要： A method and an apparatus for reducing airflow leakage between a combustor liner and a rail of a heat shield mounted to an inner surface of the combustor liner. The method comprises locally deforming the combustor liner in sealing engagement with the rail by applying a pressure on the outer surface of the combustor liner over the rail of the heat shield. A tool, such as a sealing clip, may be mounted in pressing engagement with the outer surface of the combustor liner to apply forces locally on the liner over the rail of the heat shield.
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公开(公告)号：US09765974B2
公开(公告)日：2017-09-19
申请号：US14505765
申请日：2014-10-03
发明人： Yen-Wen Wang , Nigel Davenport , Eduardo Hawie
CPC分类号： F23R3/286 , F23D11/107 , F23D2900/11101 , F23R3/28
摘要： 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.
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公开(公告)号：US10829236B2
公开(公告)日：2020-11-10
申请号：US16015621
申请日：2018-06-22
发明人： Ninad Joshi , Yen-Wen Wang , Tony Yee
摘要： Herein provided are systems and methods for operating an aircraft engine during inclement weather. At least one image of a location substantially in line with a heading of the aircraft is acquired. Based on the at least one image, an inclement weather condition in the location is detected. An alert mode of the engine is triggered upon detecting the inclement weather condition. Responsive to the alert mode being triggered, at least one predetermined performance parameter of the engine is monitored. Upon detecting a change in the at least one predetermined performance parameter beyond a predetermined threshold, at least one operating condition of the engine is altered.
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