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公开(公告)号：WO2014186150A1
公开(公告)日：2014-11-20
申请号：PCT/US2014/036536
申请日：2014-05-02
Applicant: SOLAR TURBINES INCORPORATED
Inventor： CRAMB, Donald James , PIPER, James Scott , SPIVEY, Sean Kelly , RAMOTOWSKI, Michael John , MAYER, Matthew
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：WO2017120035A1
公开(公告)日：2017-07-13
申请号：PCT/US2016/067794
申请日：2016-12-20
Applicant: SOLAR TURBINES INCORPORATED
CPC classification number: F02C7/222 , F05D2220/32 , F23R3/28 , F23R3/286 , F23R3/34 , F23R3/36 , F23R2900/00004 , F23R2900/03343
Abstract: A fuel injector (600) for a gas turbine engine (100) is disclosed. The fuel injector (600) includes a flange assembly (610) with a distribution block (612), three main gas tubes, and an injector head (630). The distribution block (612) evenly distributes a main gas fuel to the three main gas tubes. The injector head (630) includes an injector body (640) with a primary gas gallery (643) including an annular shape. The three main gas tubes are connected in a parallel configuration between the distribution block (612) and the primary gas gallery (643). The three main gas tubes are all in flow communication with the primary gas gallery (643) and provide the main gas fuel from the same main gas fuel source.
Abstract translation: 公开了用于燃气涡轮发动机（100）的燃料喷射器（600）。 燃料喷射器（600）包括具有分配块（612）的法兰组件（610），三个主燃气管以及喷射器头（630）。 分配块（612）将主气体燃料均匀地分配到三个主气管。 注射头（630）包括具有包括环形形状的主气体通道（643）的注射器主体（640）。 三个主气管在分配块（612）和主气体通道（643）之间以平行配置连接。 三个主要气体管与主要气体通道（643）全部流动连通，并提供来自同一主要气体燃料源的主要气体燃料。
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公开(公告)号：WO2014186148A1
公开(公告)日：2014-11-20
申请号：PCT/US2014/036518
申请日：2014-05-02
Applicant: SOLAR TURBINES INCORPORATED
Inventor： CRAMB, Donald James , PIPER, James Scott , SPIVEY, Sean Kelly , RAMOTOWSKI, Michael John , MAYER, Matthew
CPC classification number: F02C7/232 , F23R3/14 , F23R3/286 , F23R2900/00019 , Y10T29/49401
Abstract: A gas turbine engine outer premix barrel is disclosed. The outer premix barrel includes a body portion, a barrel portion, and a plurality of vanes. The body portion includes vent air inlets. The barrel portion extends axially aft from the body portion. The plurality of vanes extends axially forward from the body portion. Each vane includes an inward surface located at a radially inner end of the vane, and a plurality of vent passages exiting the vane at the inward surface. Each vent passage is in flow communication with at least one vent air inlet.
Abstract translation: 公开了一种燃气涡轮发动机外部预混料筒。 外部预混料桶包括主体部分，筒部分和多个叶片。 主体部分包括排放空气入口。 枪管部分从主体部分轴向延伸。 多个叶片从主体部分轴向地向前延伸。 每个叶片包括位于叶片的径向内端处的向内表面和在内表面处离开叶片的多个通气通道。 每个通气通道与至少一个排气入口流动连通。
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Patent Agency Ranking
公开(公告)号：WO2017120038A1
公开(公告)日：2017-07-13
申请号：PCT/US2016/067826
申请日：2016-12-20
Applicant: SOLAR TURBINES INCORPORATED
Abstract: A method for lean direct injection of a liquid fuel from a fuel injector (600) into a combustion chamber (390) of a gas turbine engine (100) is disclosed. The method includes injecting all of the liquid fuel into the combustion chamber (390) through a pilot liquid fuel circuit (608,609,628) 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 (607,627,643,721,769, 774, 775) and injecting a remainder of the liquid fuel through the pilot liquid fuel circuit (608,609,628) when the gas turbine engine (100) is at idle and for operating ranges of the gas turbine engine (100) above idle.
Abstract translation: 公开了一种用于从燃料喷射器（600）向燃气涡轮发动机（100）的燃烧室（390）稀薄地直接喷射液体燃料的方法。 该方法包括在点火期间和朝着怠速加速期间通过先导液体燃料回路（608,609,628）将所有液体燃料喷射到燃烧室（390）中。 该方法还包括以两种液流注入液体燃料，包括通过主液体燃料回路（607,627,643,721,769,774,775）将大部分液体燃料作为环形膜注入，并将剩余的液体燃料通过先导液体燃料回路 当燃气涡轮发动机（100）处于怠速状态并且燃气涡轮发动机（100）的工作范围高于空转时，所述燃气涡轮发动机（608,609,628）
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5.发明申请
公开(公告)号：WO2017120037A1
公开(公告)日：2017-07-13
申请号：PCT/US2016/067811
申请日：2016-12-20
Applicant: SOLAR TURBINES INCORPORATED
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 (700) for a fuel injector (600) is disclosed. The center body assembly (700) defines a primary liquid passage (721), a liquid gallery, swirl slots (775), and a prefilm passage (769). The primary liquid passage (721) supplies liquid fuel to the liquid gallery. The liquid gallery includes a gallery discharge end (785) and a gallery inlet end (781) that aligns with the primary liquid passage (721). The liquid gallery tapers down from the gallery inlet end (781) to the gallery discharge end (785). The swirl slots (775) extend from the liquid gallery to the prefilm passage (769) in a helical pattern. The prefilm passage (769) includes an annular shape that turns inward towards an assembly axis of the center body assembly (700).
Abstract translation: 公开了用于燃料喷射器（600）的中心本体组件（700）。 中心体组件（700）限定了主液体通道（721），液体通道，涡流槽（775）和预膜通道（769）。 主液体通道（721）将液体燃料供应到液体通道。 液体通道包括通道排出端（785）和与主液体通道（721）对齐的通道入口端（781）。 液体廊道从廊道入口端（781）向廊道排放端（785）渐缩。 涡流槽（775）以螺旋形式从液体通道延伸到预制膜通道（769）。 预制膜通道（769）包括朝着中心体组件（700）的组装轴线向内转动的环形形状。
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公开(公告)号：WO2014186146A1
公开(公告)日：2014-11-20
申请号：PCT/US2014/036511
申请日：2014-05-02
Applicant: SOLAR TURBINES INCORPORATED
Inventor： CRAMB, Donald James , PIPER, James Scott , SPIVEY, Sean Kelly , RAMOTOWSKI, Michael John , MAYER, Matthew
CPC classification number: F02C7/232 , F23D11/402 , F23D2900/14641 , F23R3/14 , F23R3/286 , F23R2900/00019 , Y10T29/49229
Abstract: A liquid gallery for a fuel injector of a gas turbine engine includes a gallery body, a liquid gallery scroll, a plurality of atomizer inlets, and a plurality of atomizer bosses. The liquid gallery scroll extends into the gallery body spanning from a first end to a second end in a circumferential direction. The liquid gallery scroll includes a taper with a cross-sectional area of the liquid gallery scroll reducing from the first end to the second end. Each atomizer inlet is in flow communication with the liquid gallery scroll. Each atomizer boss is aligned with one of the plurality of atomizer inlets.
Abstract translation: 一种用于燃气涡轮发动机的燃料喷射器的液体显示器，包括一个画廊体，一个液体画廊卷轴，多个雾化器入口以及多个雾化器凸台。 液体仓卷轴沿圆周方向从第一端延伸到第二端。 液体库卷轴包括具有从第一端到第二端的液体槽涡旋的横截面面积的锥形。 每个雾化器入口与液体库卷轴流动连通。 每个雾化器凸台与多个雾化器入口之一对准。
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公开(公告)号：WO2017120039A1
公开(公告)日：2017-07-13
申请号：PCT/US2016/067834
申请日：2016-12-20
Applicant: SOLAR TURBINES INCORPORATED
Abstract: A fuel injector (600) for a gas turbine engine (100) is disclosed. The fuel injector (600) includes two primary tubes, a secondary tube (603), a primary gas gallery (643), and a secondary gas gallery (644). The two primary tubes are connected in a parallel configuration to provide a main gas fuel to the primary gas gallery (643). The secondary tube (603) provides the main gas fuel to the secondary gas gallery (644) independent from the two primary tubes and the primary gas gallery (643). The primary gas gallery (643) and the secondary gas gallery (644) provide the main gas fuel to a premix passage (669) independently allowing for robust control of the gas turbine engine (100).
Abstract translation: 公开了用于燃气涡轮发动机（100）的燃料喷射器（600）。 燃料喷射器（600）包括两个主管，第二管（603），第一气体通道（643）和第二气体通道（644）。 两个主管以平行配置连接以向主要气体通道（643）提供主气体燃料。 次级管（603）将主气体燃料提供给独立于两个主管和主气体通道（643）的次级气体通道（644）。 主气体通道（643）和第二气体通道（644）将主气体燃料提供给预混合物通道（669），独立地允许燃气涡轮发动机（100）的鲁棒控制。
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公开(公告)号：WO2014186149A1
公开(公告)日：2014-11-20
申请号：PCT/US2014/036528
申请日：2014-05-02
Applicant: SOLAR TURBINES INCORPORATED
Inventor： CRAMB, Donald James , PIPER, James Scott , SPIVEY, Sean Kelly , RAMOTOWSKI, Michael John , MAYER, Matthew
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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