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    Variable guide vane extended variable fillet
    33.
    发明授权
    Variable guide vane extended variable fillet 有权

    公开(公告)号：US09631504B2

    公开(公告)日：2017-04-25

    申请号：US14243701

    申请日：2014-04-02

    Applicant: SOLAR TURBINES INCORPORATED

    Inventor： Sean Joseph Bentley

    IPC: F01D9/02 ,  F01D5/14 ,  F01D17/16 ,  F04D29/56

    CPC classification number: F01D9/02 ,  F01D5/143 ,  F01D17/162 ,  F04D29/563

    Abstract: A guide vane is disclosed. The guide vane includes a button, a trunnion connected to the button, and an airfoil connected to the button. The airfoil includes an overhang portion wherein the overhang portion extends from one end of the button to a distal end of the airfoil. The guide vane includes a button corner located near the beginning of the overhang portion. The guide vane includes a variable fillet extending into the overhang portion. The variable fillet includes sections of different radiuses along the length of the fillet.

    Tri-lobe bearing for a gearbox
    36.
    发明授权
    Tri-lobe bearing for a gearbox 有权
    用于齿轮箱的三叶轴承

    公开(公告)号：US09562602B2

    公开(公告)日：2017-02-07

    申请号：US14325179

    申请日：2014-07-07

    Applicant: Solar Turbines Incorporated

    Inventor： Edward William Sieveking ,  Yuanhong Guan

    IPC: F16H1/34 ,  F16H57/00 ,  F16C17/02 ,  F16H57/08 ,  F16C33/10 ,  F16C3/02 ,  F16H1/28

    CPC classification number: F16H57/0006 ,  F16C3/02 ,  F16C17/028 ,  F16C33/1055 ,  F16C33/1075 ,  F16C2361/61 ,  F16H1/28 ,  F16H57/08 ,  F16H2057/085

    Abstract: A bearing for a gearbox, the bearing having a cylindrical body. The cylindrical body defines a hollow interior chamber. The cylindrical body has a gear supporting section. The gear supporting section has a cross-section formed by three lobes equally distributed around a circumference of the cylindrical body. Each of the lobes has a land portion having a first radius over at least 20% of the lobe. Each lobe also has a tapered portion that gradually slopes from the first radius of the land portion to a reduced radius region that is smaller than the first radius. The tapered portion is formed over less than 80% of each lobe. Each lobe also has an opening formed in the reduced radius region and a flow passage fluidly connecting the hollow interior of the cylindrical body with the opening formed in the reduced radius region.

    Abstract translation: 用于齿轮箱的轴承，该轴承具有圆柱体。 圆筒体限定了一个中空的内部腔室。 圆柱体具有齿轮支撑部分。 齿轮支撑部分具有由围绕圆柱体的圆周均匀分布的三个叶片形成的横截面。 每个裂片具有在凸起的至少20％上具有第一半径的脊部分。 每个叶片还具有逐渐从陆部的第一半径倾斜到小于第一半径的缩小半径区域的锥形部分。 锥形部分形成在每个凸角的小于80％以上。 每个叶片还具有形成在缩小半径区域中的开口和流体连通圆筒体的中空内部与形成在缩小半径区域中的开口的流动通道。

    COMBUSTION STABILITY LOGIC DURING OFF-LOAD TRANSIENTS
    37.
    发明申请
    COMBUSTION STABILITY LOGIC DURING OFF-LOAD TRANSIENTS 有权
    在负载过渡期间的燃烧稳定性逻辑

    公开(公告)号：US20160348593A1

    公开(公告)日：2016-12-01

    申请号：US14727019

    申请日：2015-06-01

    Applicant: Solar Turbines Incorporated

    Inventor： Fabrizio Oliverio

    IPC: F02C9/22 ,  F02C9/28 ,  F02C9/32

    CPC classification number: F02C9/28 ,  F02C9/54 ,  F05D2270/303 ,  F05D2270/304 ,  F05D2270/31

    Abstract: A method for operating a gas turbine engine is disclosed. The method includes detecting an off-load transient of the gas turbine engine. The method includes reducing a total flow of fuel to a combustor section of the gas turbine engine to a first reduced flow in response to detecting the off-load transient. The method includes adjusting a position of an inlet guide vane in response to detecting the off-load transient until either an on-load transient is detected or until an amount of time elapsed since detection of the off-load transient exceeds a maximum override time.

    Abstract translation: 公开了一种操作燃气涡轮发动机的方法。 该方法包括检测燃气涡轮发动机的卸载瞬态。 该方法包括响应于检测到负载瞬态而将燃气涡轮发动机的燃烧器部分的总流量减少到第一减小的流量。 该方法包括响应于检测到负载瞬态而调整入口导流叶片的位置，直到检测到负载瞬态，或者直到从断开负载瞬态的检测超过最大超驰时间而经过的时间量。

    HIGH SPEED RECORDER FOR A GAS TURBINE ENGINE
    38.
    发明申请
    HIGH SPEED RECORDER FOR A GAS TURBINE ENGINE 审中-公开
    用于燃气涡轮发动机的高速记录仪

    公开(公告)号：US20160348532A1

    公开(公告)日：2016-12-01

    申请号：US15169417

    申请日：2016-05-31

    Applicant: Solar Turbines Incorporated

    Inventor： Luvigi Di Raimondo ,  Roberto Camboni ,  Gennaro Abbatiello

    IPC: F01D21/00 ,  G01M15/14

    CPC classification number: F01D21/003 ,  F05D2220/32 ,  F05D2260/80 ,  F05D2270/304 ,  G01M15/14 ,  G05B23/0221 ,  G05B23/0264

    Abstract: A control system for a gas turbine engine is disclosed. In embodiments, control system includes a controller and a high speed recorder. The controller obtains sensor values from sensors connected to the gas turbine engine and publishes a map of trigger events. The high speed recorder reads the sensor values from the controller. The high speed recorder checks a map header for a change to the map header on a predetermined map reading interval, sets a flag when the map header has changed, and reads the map during the next loop of the map reading interval. The control system maintains timestamps assigned for the sensor values and to the trigger events on the same temporal axis.

    Abstract translation: 公开了一种用于燃气涡轮发动机的控制系统。 在实施例中，控制系统包括控制器和高速记录器。 控制器从连接到燃气涡轮发动机的传感器获得传感器值，并发布触发事件的映射。 高速记录仪从控制器读取传感器值。 高速记录器在预定的地图读取间隔上检查地图标题对地图标题的改变，当地图标题改变时设置标志，并且在地图读取间隔的下一个循环期间读取地图。 控制系统保持为相同时间轴上的传感器值和触发事件分配的时间戳。

    Compressor blade for gas turbine engine
    39.
    发明授权
    Compressor blade for gas turbine engine 有权
    燃气轮机发动机用压缩机叶片

    公开(公告)号：US09506347B2

    公开(公告)日：2016-11-29

    申请号：US13720640

    申请日：2012-12-19

    Applicant: Solar Turbines Incorporated

    Inventor： Jeremiah W. Key

    IPC: F01D5/14

    CPC classification number: F01D5/141 ,  Y02T50/671 ,  Y02T50/673

    Abstract: A compressor blade for a gas turbine engine includes a root configured to engage a hub of the gas turbine engine, and an airfoil radially extending a distance from the root to a tip. The airfoil includes a suction side, a pressure side, a leading edge connecting the suction and pressure sides, and a trailing edge connecting the suction and pressure sides opposite the leading edge. The distance that the airfoil extends from the root to the tip may be divided into a plurality of radially adjacent regions. At least one, but not all, of the plurality of radially adjacent regions may have a substantially constant thickness.

    Abstract translation: 用于燃气涡轮发动机的压缩机叶片包括构造成接合燃气涡轮发动机的轮毂的根部和从根部到尖端径向延伸一定距离的翼型件。 翼型件包括吸入侧，压力侧，连接吸力侧和压力侧的前缘以及连接与前缘相对的吸力侧和压力侧的后缘。 翼型件从根部延伸到尖端的距离可以被分成多个径向相邻的区域。 多个径向相邻区域中的至少一个但不是全部可以具有基本恒定的厚度。

    Exhaust collector with curved side panel
    40.
    发明授权
    Exhaust collector with curved side panel 有权
    具有弯曲侧板的排气收集器

    公开(公告)号：US09476324B2

    公开(公告)日：2016-10-25

    申请号：US14031408

    申请日：2013-09-19

    Applicant: SOLAR TURBINES INCORPORATED

    Inventor： Kevin Kiyoto Hirako ,  Brian Alan Fox ,  Leslie John Faulder

    IPC: F01N5/00 ,  F01D25/30

    CPC classification number: F01D25/30 ,  F05D2250/713

    Abstract: An exhaust collector for a gas turbine engine is disclosed. The exhaust collector includes a front panel, a rear panel, and a side panel. The side panel includes a circumferential portion, a first contoured portion, and a second contoured portion. The circumferential portion extends about the exhaust collector axis with a constant radius. The first contoured portion and the second contoured portion are each between the circumferential portion and the exhaust outlet and include a plurality of curved sections with alternating concavity. Each of the plurality of curved sections extends from the front panel to the rear panel.

    Abstract translation: 公开了一种用于燃气涡轮发动机的排气收集器。 排气收集器包括前面板，后面板和侧面板。 侧板包括圆周部分，第一轮廓部分和第二轮廓部分。 周向部分围绕排气收集器轴线以恒定的半径延伸。 第一轮廓部分和第二轮廓部分各自在圆周部分和排气出口之间，并且包括具有交替凹陷的多个弯曲部分。 多个弯曲部分中的每个从前面板延伸到后面板。

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