中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

519 records (took 0.027 seconds)

    Gas turbine engine combustor hot streak control
    221.
    发明授权
    Gas turbine engine combustor hot streak control 失效
    燃气轮机发动机燃烧器热条纹控制

    公开(公告)号：US07739873B2

    公开(公告)日：2010-06-22

    申请号：US11256786

    申请日：2005-10-24

    Applicant: Kattalaicheri Srinivasan Venkataramani ,  William Joseph Myers, Jr. ,  Robert Joseph Orlando ,  Paul Cooker ,  Ching-Pang Lee

    Inventor： Kattalaicheri Srinivasan Venkataramani ,  William Joseph Myers, Jr. ,  Robert Joseph Orlando ,  Paul Cooker ,  Ching-Pang Lee

    IPC: F02C9/00

    CPC classification number: F02C9/263 ,  F05D2270/112 ,  F05D2270/3032 ,  F23K5/005 ,  F23K5/06 ,  F23K2203/105 ,  F23N1/00 ,  F23N1/002 ,  F23N5/02 ,  F23N5/022 ,  F23N5/24 ,  F23N5/242

    Abstract: A gas turbine engine combustion system includes a plurality of fuel injectors circumferentially disposed around a combustor in a one to one fuel supply relationship with a plurality of fuel nozzle valves, and an electronic controller for controlling the fuel nozzle valves to eliminate and/or reduce hot streaking in response to sensed hot streak conditions. The fuel nozzle valves may be modulating valves. The electronic controller may be used to individually control the fuel nozzle valves. The hot streak conditions may be sensed with temperature sensors such as temperature sensors operably mounted in the combustor. A program in the electronic controller may be used for determining broken or malfunctioning sensors by calculating a combustor temperature and comparing it to measured temperatures from the sensors and comparing the measured fuel pressures in the individual fuel nozzle circuits with the simulated or calculated fuel pressures.

    Abstract translation: 燃气涡轮发动机燃烧系统包括多个燃料喷射器，其周向地设置在与多个燃料喷嘴阀一对一燃料供给关系中的燃烧器周围;以及电子控制器，用于控制燃料喷嘴阀以消除和/或减少热量 响应于感测到的热条件条件。 燃料喷嘴阀可以是调节阀。 电子控制器可以用于单独地控制燃料喷嘴阀。 温度传感器可以感测热条纹条件，诸如可操作地安装在燃烧器中的温度传感器。 电子控制器中的程序可用于通过计算燃烧器温度并将其与来自传感器的测量温度进行比较并将各个燃料喷嘴回路中测量的燃料压力与模拟或计算的燃料压力进行比较来确定破坏或故障的传感器。

    Method and system to facilitate preferentially distributed recuperated film cooling of turbine shroud assembly
    222.
    发明授权
    Method and system to facilitate preferentially distributed recuperated film cooling of turbine shroud assembly 有权
    促进涡轮机罩组件优先分布复原薄膜冷却的方法和系统

    公开(公告)号：US07722315B2

    公开(公告)日：2010-05-25

    申请号：US11565253

    申请日：2006-11-30

    Applicant: Ching-Pang Lee ,  Eric Alan Estill ,  James Harvey Laflen ,  Paul Hadley Vitt ,  Michael Elliot Wymore

    Inventor： Ching-Pang Lee ,  Eric Alan Estill ,  James Harvey Laflen ,  Paul Hadley Vitt ,  Michael Elliot Wymore

    IPC: F01D25/14

    CPC classification number: F01D11/08 ,  F05D2240/11 ,  F05D2260/202 ,  Y02T50/671 ,  Y02T50/676 ,  Y10T29/49236

    Abstract: A method of assembling a gas turbine engine includes coupling a turbine shroud assembly within the gas turbine engine. The turbine shroud assembly includes a shroud segment having a leading edge defining a forward face and a radial inner surface. A turbine nozzle is coupled to the turbine shroud assembly such that a gap is defined between an aft face of an outer band of the turbine nozzle and the forward face. A plurality of recuperated cooling openings are defined through the leading edge at an oblique inlet angle with respect to a centerline of the gap and between the forward face and the radial inner surface to direct cooling fluid through the leading edge to facilitate preferential cooling of the leading edge.

    Abstract translation: 一种组装燃气涡轮发动机的方法包括将涡轮机罩组件联接在燃气涡轮发动机内。 涡轮机罩组件包括具有限定前表面和径向内表面的前缘的护罩区段。 涡轮喷嘴联接到涡轮机护罩组件，使得在涡轮喷嘴的外带的后表面和前表面之间限定间隙。 多个恢复的冷却开口通过前缘以相对于间隙的中心线和前表面和径向内表面之间的倾斜入口角定义，以将冷却流体引导通过前缘，以便于先导的优先冷却 边缘。

    Methods and system for recuperated cooling of integral turbine nozzle and shroud assemblies
    223.
    发明授权
    Methods and system for recuperated cooling of integral turbine nozzle and shroud assemblies 失效
    整体涡轮喷嘴和护罩组件的回热冷却方法和系统

    公开(公告)号：US07665953B2

    公开(公告)日：2010-02-23

    申请号：US11565176

    申请日：2006-11-30

    Applicant: Ching-Pang Lee ,  Eric Alan Estill ,  James Harvey Laflen ,  Katherine Jaynetorrence Andersen

    Inventor： Ching-Pang Lee ,  Eric Alan Estill ,  James Harvey Laflen ,  Katherine Jaynetorrence Andersen

    IPC: F01D25/12

    CPC classification number: F01D11/24 ,  F05D2240/11 ,  Y02T50/671

    Abstract: A method for cooling a shroud segment of a gas turbine engine is provided. The method includes providing a turbine shroud assembly including a shroud segment having an inner surface and a leading edge that is substantially perpendicular to the inner surface, and coupling a turbine nozzle to the turbine shroud segment such that a gap is defined between an aft edge of an outer band of the turbine nozzle and the leading edge. The method also includes directing cooling air into the gap, and directing the cooling air in the gap through at least one cooling hole extending between the leading edge and the inner surface.

    Abstract translation: 提供了一种用于冷却燃气涡轮发动机的护罩部分的方法。 该方法包括提供一种涡轮机护罩组件，其包括具有内表面和大致垂直于内表面的前缘的护罩区段，以及将涡轮喷嘴连接到涡轮机护罩区段，使得间隙限定在 涡轮喷嘴的外带和前缘。 该方法还包括将冷却空气引导到间隙中，以及通过在前缘和内表面之间延伸的至少一个冷却孔将间隙中的冷却空气引导。

    Ovate band turbine stage
    224.
    发明授权
    Ovate band turbine stage 有权
    卵形带涡轮机阶段

    公开(公告)号：US07578653B2

    公开(公告)日：2009-08-25

    申请号：US11642001

    申请日：2006-12-19

    Applicant: Kevin Samuel Klasing ,  Ching-Pang Lee ,  Scott David Hunter

    Inventor： Kevin Samuel Klasing ,  Ching-Pang Lee ,  Scott David Hunter

    IPC: F01D11/02 ,  F01D9/04

    CPC classification number: F01D11/001 ,  F01D5/143 ,  F01D11/04 ,  Y02T50/673

    Abstract: A turbine stage includes a stator nozzle having a row of vanes mounted between inner and outer bands. The inner band terminates in an ovate ledge converging aft from the vanes with radially outer and inner convex surfaces joined at a convex apex. The ovate ledge reduces aerodynamic losses at the rotary seal with a row of following turbine rotor blades.

    Abstract translation: 涡轮级包括具有安装在内带和外带之间的一排叶片的定子喷嘴。 内带终止于从叶片向后收敛的卵形突出部，其中凸起的顶部与径向外部和内部凸起表面接合。 卵形凸缘在一系列以下的涡轮转子叶片上减小了在旋转密封处的空气动力学损失。

    RECIPROCAL COOLED TURBINE NOZZLE
    228.
    发明申请
    RECIPROCAL COOLED TURBINE NOZZLE 有权
    回转冷却涡轮喷嘴

    公开(公告)号：US20080317585A1

    公开(公告)日：2008-12-25

    申请号：US11765522

    申请日：2007-06-20

    Applicant: Ching-Pang Lee ,  Robert Joseph Orlando

    Inventor： Ching-Pang Lee ,  Robert Joseph Orlando

    IPC: F01D5/18

    CPC classification number: F01D9/041 ,  F01D5/186 ,  F01D5/189 ,  F05D2260/201 ,  F05D2260/202 ,  Y02T50/67 ,  Y02T50/673 ,  Y02T50/676

    Abstract: A turbine nozzle includes first and second vanes joined to outer and inner bands. The vanes include outboard sides defining outboard flow passages containing axial splitlines, and opposite inboard sides defining an inboard flow passage without axial splitline. The two vanes include different cooling circuits for differently cooling the inboard and outboard vane sides.

    Abstract translation: 涡轮喷嘴包括连接到外带和内带的第一和第二叶片。 叶片包括限定外侧流动通道的外侧面，其包含轴向分裂线，并且相对的内侧限定内侧流动通道而不具有轴向分裂线。 两个叶片包括用于不同地冷却内侧和外侧叶片侧面的不同冷却回路。

    Synthetic model casting
    229.
    发明授权
    Synthetic model casting 有权
    合成模型铸造

    公开(公告)号：US07413001B2

    公开(公告)日：2008-08-19

    申请号：US11130443

    申请日：2005-05-16

    Applicant: Hsin-Pang Wang ,  Ching-Pang Lee

    Inventor： Hsin-Pang Wang ,  Ching-Pang Lee

    IPC: B22C9/00 ,  B22C9/10

    CPC classification number: B22C9/10 ,  B29C64/00 ,  B33Y80/00 ,  Y02P10/292

    Abstract: A synthetic model of a component is created from a 3-D numerical model thereof. A core is then cast inside the synthetic model. The synthetic model may then be removed from the cast core, and then the cast core is used for casting an authentic component therearound. The core is removed from inside the authentic component, which authentic component precisely matches the original synthetic model therefor.

    Abstract translation: 组件的合成模型由其三维数值模型创建。 然后将核心投入合成模型。 然后可以将合成模型从铸造芯中移除，然后铸造芯用于铸造其周围的真实组件。 核心从真实组件内部移除，该真实组件与原始合成模型精确匹配。

    Cluster bridged casting core
    230.
    发明申请
    Cluster bridged casting core 有权
    集群桥接铸铁芯

    公开(公告)号：US20080145234A1

    公开(公告)日：2008-06-19

    申请号：US11641286

    申请日：2006-12-19

    Applicant: Ching-Pang Lee ,  Steven Robert Brassfield

    Inventor： Ching-Pang Lee ,  Steven Robert Brassfield

    IPC: F01D5/18 ,  B22D15/00

    CPC classification number: B22C9/103 ,  F01D5/187 ,  F05D2230/211 ,  F05D2260/202 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676

    Abstract: A casting core for a turbine blade includes a plurality of rods extending above a shank. The rods define internal cooling channels in the airfoil of the blade, and the shank defines an inlet channel in the dovetail of the blade. A plurality of stubs are clustered together at a bulb joined to the shank and radiate outwardly to integrally join different ones of the rods for increasing strength of the core.

    Abstract translation: 用于涡轮叶片的铸芯包括在柄上方延伸的多个杆。 杆在叶片的翼型中限定内部冷却通道，并且杆在叶片的燕尾形中限定入口通道。 多个短棒在连接到柄的灯泡上聚集在一起并向外辐射以一体地连接不同的杆，以增加芯的强度。

Patent Agency Ranking