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公开(公告)号：US09976522B2
公开(公告)日：2018-05-22
申请号：US15130019
申请日：2016-04-15
Applicant: Solar Turbines Incorporated
Inventor： Rajeshriben Patel , James Scott Piper , Raymond Alvarez , Rasoul Paydar , Ram Srinivasan
CPC classification number: F02M29/06 , F02M61/14 , F23R3/14 , F23R3/28 , F23R3/286 , F23R3/36 , Y02T50/675
Abstract: A fuel injector for a combustion engine includes an injector head including a nozzle, a premixer, and a distributor structured to distribute a plurality of different fuels to different sets of fueling orifices in the premixer. A pilot assembly of the fuel injector is coupled to the premixer and includes a first fueling passage for a first fuel and a second fueling passage for a second fuel. Multiple sets of fueling orifices are positioned within the fuel injector, the fueling orifice sets being selectively connectable to a plurality of different fuel supplies, and both located and sized so as to accommodate a wide range of flow rates to enable a combustion engine coupled with the fuel injector to operate on fuels having a range of Wobbe indices and compositions.
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公开(公告)号：US20160116168A1
公开(公告)日：2016-04-28
申请号：US14525061
申请日：2014-10-27
Applicant: SOLAR TURBINES INCORPORATED
Inventor： Ramarao Venkat Bandaru , James Scott Piper , Peter Joseph Giella , Behruz N. Rustomi
IPC: F23R3/28
Abstract: A fuel injector for a combustor of a gas turbine engine is disclosed. The fuel injector includes a flange, a fitting boss, a stem, a gas fuel passage, a gas fuel fitting, and a gas heat shield. The fitting boss protrudes from the flange. The stem extends from the flange. The gas fuel passage extends through the stem. The gas fuel fitting is joined to the fitting boss. The gas heat shield extends from the gas fuel fitting at least partially through the gas fuel passage. The gas heat shield is sized to form a gas heat shield gap between the gas heat shield and the stem at the gas fuel passage.
Abstract translation: 公开了一种用于燃气涡轮发动机的燃烧器的燃料喷射器。 燃料喷射器包括凸缘，配件凸台，杆，气体燃料通道，气体燃料配件和气体隔热罩。 配件凸台从凸缘突出。 杆从凸缘延伸。 气体燃料通道延伸穿过阀杆。 气体燃料配件连接到配件凸台。 气体热屏蔽从气体燃料配件至少部分地延伸穿过气体燃料通道。 气体隔热罩的尺寸设计成在气体燃料通道处形成气体隔热罩和阀杆之间的气体隔热隔离物。
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公开(公告)号：US20140332603A1
公开(公告)日：2014-11-13
申请号：US13893180
申请日：2013-05-13
Applicant: Solar Turbines Incorporated
Inventor： Donald James Cramb , James Scott Piper , Sean Kelly Spivey , Michael John Ramotowski , Matthew Mayer
IPC: F02M69/04
CPC classification number: F23R3/343 , F23D11/36 , F23D2900/00015 , F23R3/12 , F23R3/283 , F23R2900/00017
Abstract: A pilot liquid tube having a pilot liquid fuel inlet, a pilot liquid fuel conduit, a pilot liquid fuel nozzle, and a shroud configured to shield the pilot liquid fuel nozzle. The pilot liquid tube may be installed and/or removed from an injector of a gas turbine engine while the shroud remains fixed to pilot liquid fuel conduit.
Abstract translation: 具有先导液体燃料入口，先导液体燃料管道，先导液体燃料喷嘴和构造成屏蔽先导液体燃料喷嘴的护罩的先导液体管。 导向液体管可以在燃气涡轮发动机的喷射器中被安装和/或移除，同时护罩保持固定到先导液体燃料管道。
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公开(公告)号：US20140332602A1
公开(公告)日：2014-11-13
申请号：US13893083
申请日：2013-05-13
Applicant: Solar Turbines Incorporated
Inventor： Donald James Cramb , James Scott Piper , Sean Kelly Spivey , Michael John Ramotowski , Matthew Mayer
CPC classification number: B01F5/06 , F23R3/14 , F23R3/283 , F23R3/286 , F23R2900/00017 , F23R2900/00019 , Y02T50/675 , Y10T29/4973
Abstract: An inner premix tube for a fuel injector of a gas turbine engine includes a transition end, a tip end, and a premix tube inner surface. The transition end includes an annular disk portion with an annular disk shape and a redirection portion extending radially inward and axially from the annular disk portion. The transition end also includes a plurality of wipe passages extending through the transition end. The tip end includes a cylindrical portion with a hollow right circular cylinder shape. The premix tube inner surface is a radially outer surface including the redirection portion outer surface and the cylindrical portion outer surface.
Abstract translation: 用于燃气涡轮发动机的燃料喷射器的内部预混管包括过渡端，末端和预混管内表面。 过渡端包括具有环形盘形状的环形盘部分和从环形盘部分径向向内和轴向延伸的重定向部分。 过渡端还包括延伸穿过过渡端的多个擦拭通道。 尖端包括具有中空的右圆柱形形状的圆柱形部分。 预混管内表面是包括重定向部分外表面和圆筒部分外表面的径向外表面。
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公开(公告)号：US10274201B2
公开(公告)日：2019-04-30
申请号：US14988549
申请日：2016-01-05
Applicant: SOLAR TURBINES INCORPORATED
Inventor： Sean Kelly Spivey , Donald James Cramb , James Scott Piper , Michael John Ramotowski
Abstract: A fuel injector for a gas turbine engine is disclosed. The fuel injector includes two primary tubes, a secondary tube, a primary gas gallery, and a secondary gas gallery. The two primary tubes are connected in a parallel configuration to provide a main gas fuel to the primary gas gallery. The secondary tube provides the main gas fuel to the secondary gas gallery independent from the two primary tubes and the primary gas gallery. The primary gas gallery and the secondary gas gallery provide the main gas fuel to a premix passage independently allowing for robust control of the gas turbine engine.
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Patent Agency Ranking
公开(公告)号：US10054093B2
公开(公告)日：2018-08-21
申请号：US14988574
申请日：2016-01-05
Applicant: SOLAR TURBINES INCORPORATED
Inventor： Sean Kelly Spivey , Donald James Cramb , James Scott Piper , Michael John Ramotowski
CPC classification number: F02M61/163 , F05D2220/32 , F05D2240/35 , F23R3/28 , F23R3/286 , F23R3/34 , F23R3/36 , F23R2900/00004 , F23R2900/03343
Abstract: A center body assembly for a fuel injector is disclosed. The center body assembly defines a primary liquid passage, a liquid gallery, swirl slots, and a prefilm passage. The primary liquid passage supplies liquid fuel to the liquid gallery. The liquid gallery includes a gallery discharge end and a gallery inlet end that aligns with the primary liquid passage. The liquid gallery tapers down from the gallery inlet end to the gallery discharge end. The swirl slots extend from the liquid gallery to the prefilm passage in a helical pattern. The prefilm passage includes an annular shape that turns inward towards an assembly axis of the center body assembly.
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公开(公告)号：US20170298875A1
公开(公告)日：2017-10-19
申请号：US15130019
申请日：2016-04-15
Applicant: Solar Turbines Incorporated
Inventor： Rajeshriben Patel , James Scott Piper , Raymond Alvarez , Rasoul Paydar , Ram Srinivasan
CPC classification number: F02M29/06 , F02M61/14 , F23R3/14 , F23R3/28 , F23R3/286 , F23R3/36 , Y02T50/675
Abstract: A fuel injector for a combustion engine includes an injector head including a nozzle, a premixer, and a distributor structured to distribute a plurality of different fuels to different sets of fueling orifices in the premixer. A pilot assembly of the fuel injector is coupled to the premixer and includes a first fueling passage for a first fuel and a second fueling passage for a second fuel. Multiple sets of fueling orifices are positioned within the fuel injector, the fueling orifice sets being selectively connectable to a plurality of different fuel supplies, and both located and sized so as to accommodate a wide range of flow rates to enable a combustion engine coupled with the fuel injector to operate on fuels having a range of Wobbe indices and compositions.
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公开(公告)号：US20170191667A1
公开(公告)日：2017-07-06
申请号：US14988549
申请日：2016-01-05
Applicant: SOLAR TURBINES INCORPORATED
Inventor： Sean Kelly Spivey , Donald James Cramb , James Scott Piper , Michael John Ramotowski
Abstract: A fuel injector for a gas turbine engine is disclosed. The fuel injector includes two primary tubes, a secondary tube, a primary gas gallery, and a secondary gas gallery. The two primary tubes are connected in a parallel configuration to provide a main gas fuel to the primary gas gallery. The secondary tube provides the main gas fuel to the secondary gas gallery independent from the two primary tubes and the primary gas gallery. The primary gas gallery and the secondary gas gallery provide the main gas fuel to a premix passage independently allowing for robust control of the gas turbine engine.
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公开(公告)号：US20170191428A1
公开(公告)日：2017-07-06
申请号：US14988562
申请日：2016-01-05
Applicant: SOLAR TURBINES INCORPORATED
Inventor： Sean Kelly Spivey , Donald James Cramb , James Scott Piper , Michael John Ramotowski
Abstract: A method for lean direct injection of a liquid fuel from a fuel injector into a combustion chamber of a gas turbine engine is disclosed. The method includes injecting all of the liquid fuel into the combustion chamber through a pilot liquid fuel circuit during light off and during acceleration towards idle. The method also includes injecting the liquid fuel in two streams including injecting a majority of the liquid fuel as an annular film through a main liquid fuel circuit and injecting a remainder of the liquid fuel through the pilot liquid fuel circuit when the gas turbine engine is at idle and for operating ranges of the gas turbine engine above idle.
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公开(公告)号：US09592480B2
公开(公告)日：2017-03-14
申请号：US13893083
申请日：2013-05-13
Applicant: Solar Turbines Incorporated
Inventor： Donald James Cramb , James Scott Piper , Sean Kelly Spivey , Michael John Ramotowski , Matthew Mayer
CPC classification number: B01F5/06 , F23R3/14 , F23R3/283 , F23R3/286 , F23R2900/00017 , F23R2900/00019 , Y02T50/675 , Y10T29/4973
Abstract: An inner premix tube for a fuel injector of a gas turbine engine includes a transition end, a tip end, and a premix tube inner surface. The transition end includes an annular disk portion with an annular disk shape and a redirection portion extending radially inward and axially from the annular disk portion. The transition end also includes a plurality of wipe passages extending through the transition end. The tip end includes a cylindrical portion with a hollow right circular cylinder shape. The premix tube inner surface is a radially outer surface including the redirection portion outer surface and the cylindrical portion outer surface.
Abstract translation: 用于燃气涡轮发动机的燃料喷射器的内部预混管包括过渡端，末端和预混管内表面。 过渡端包括具有环形盘形状的环形盘部分和从环形盘部分径向向内和轴向延伸的重定向部分。 过渡端还包括延伸穿过过渡端的多个擦拭通道。 尖端包括具有中空的右圆柱形形状的圆柱形部分。 预混管内表面是包括重定向部分外表面和圆筒部分外表面的径向外表面。
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