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    Gas turbine engine having improved core system
    91.
    发明申请
    Gas turbine engine having improved core system 有权
    具有改进的核心系统的燃气轮机

    公开(公告)号：US20060053804A1

    公开(公告)日：2006-03-16

    申请号：US10941508

    申请日：2004-09-15

    Applicant: Robert Orlando ,  Kattalaicheri Venkataramani ,  Ching-Pang Lee

    Inventor： Robert Orlando ,  Kattalaicheri Venkataramani ,  Ching-Pang Lee

    IPC: F02C5/00 ,  F02C7/12

    CPC classification number: F02C5/00 ,  F05D2260/20 ,  Y02T50/676

    Abstract: A gas turbine engine having a longitudinal centerline axis therethrough, including: a fan section at a forward end of the gas turbine engine including at least a first fan blade row connected to a drive shaft; a booster compressor positioned downstream of the fan section including a plurality of stages, where each stage includes a stationary compressor blade row and a rotating compressor blade row connected to the drive shaft and interdigitated with the stationary compressor blade row; and, a combustion system for producing pulses of gas having increased pressure and temperature of a fluid flow provided to an inlet thereof so as to produce a working fluid at an outlet. A first source of compressed air from the booster compressor is provided to the combustion system inlet and a second source of compressed air from the booster compressor is provided to cool the combustion system, where the pressure of the compressed air from the second source has a greater pressure than that of the compressed air from the first source.

    Abstract translation: 一种燃气涡轮发动机，其具有穿过其的纵向中心线轴线，包括：燃气涡轮发动机前端的风扇部分，至少包括连接到驱动轴的第一风扇叶片排; 位于风扇部分的下游的增压压缩机，包括多个级，其中每个级包括固定式压缩机叶片排和连接到驱动轴并与固定压缩机叶片排相互指向的旋转压缩机叶片排; 以及用于产生具有提高到其入口的流体流的压力和温度增加的气体脉冲以便在出口处产生工作流体的燃烧系统。 来自增压压缩机的第一压缩空气源被提供给燃烧系统入口，并且提供来自增压压缩机的第二压缩空气源以冷却燃烧系统，其中来自第二源的压缩空气的压力具有更大的压力 压力高于来自第一源的压缩空气的压力。

    Cooling system for gas turbine engine having improved core system
    92.
    发明申请
    Cooling system for gas turbine engine having improved core system 审中-公开
    具有改进的核心系统的燃气轮机的冷却系统

    公开(公告)号：US20060053801A1

    公开(公告)日：2006-03-16

    申请号：US10941547

    申请日：2004-09-15

    Applicant: Robert Orlando ,  Kattalaicheri Venkataramani ,  Ching-Pang Lee

    Inventor： Robert Orlando ,  Kattalaicheri Venkataramani ,  Ching-Pang Lee

    IPC: F02C7/12

    CPC classification number: F02K3/06 ,  F02C7/224 ,  F23D2214/00 ,  F23R3/28

    Abstract: A gas turbine engine having a longitudinal centerline axis therethrough, including: a fan section at a forward end of the gas turbine engine including at least a first fan blade row connected to a first drive shaft; a booster compressor positioned downstream of and in at least partial flow communication with the fan section including a plurality of stages, each stage including a stationary compressor blade row and a rotating compressor blade row connected to a drive shaft and interdigitated with the stationary compressor blade row; a core system positioned downstream of the booster compressor, the core system further comprising a combustion system for producing pulses of gas having increased pressure and temperature from a fluid flow provided to an inlet thereof so as to produce a working fluid at an outlet; a low pressure turbine positioned downstream of and in flow communication with the core system, the low pressure turbine being utilized to power the first drive shaft; and, a system for cooling the combustion system, wherein fuel is utilized as a cooling fluid prior to being supplied to the combustion system. The core system may further include an intermediate compressor positioned downstream of and in flow communication with the compressor connected to a second drive shaft; and an intermediate turbine positioned downstream of the combustion system in flow communication with the working fluid.

    Abstract translation: 一种燃气涡轮发动机，其具有穿过其的纵向中心线轴线，包括：在所述燃气涡轮发动机的前端处的风扇部分，至少包括连接到第一驱动轴的第一风扇叶片排; 位于与包括多个级的风扇部分的下游并且至少部分流动连通的增压压缩机，每个级包括固定压缩机叶片排和连接到驱动轴的旋转压缩机叶片排，并与固定压缩机叶片排相互指向 ; 位于增压压缩机下游的核心系统，所述核心系统还包括燃烧系统，用于从提供给其入口的流体流产生具有增加的压力和温度的气体脉冲，以便在出口处产生工作流体; 位于所述核心系统下游并与所述核心系统流动连通的低压涡轮机，所述低压涡轮机用于为所述第一驱动轴提供动力; 以及用于冷却燃烧系统的系统，其中燃料在被供应到燃烧系统之前用作冷却流体。 核心系统可以进一步包括位于与连接到第二驱动轴的压缩机下游并与其连通的中间压缩机; 以及位于与工作流体流动连通的燃烧系统下游的中间涡轮机。

    Thermal shield turbine airfoil
    93.
    发明授权
    Thermal shield turbine airfoil 失效
    隔热涡轮机翼型

    公开(公告)号：US07011502B2

    公开(公告)日：2006-03-14

    申请号：US10824922

    申请日：2004-04-15

    Applicant: Ching-Pang Lee ,  Ronald Scott Bunker

    Inventor： Ching-Pang Lee ,  Ronald Scott Bunker

    IPC: F01D5/18

    CPC classification number: F01D5/187 ,  Y02T50/676

    Abstract: A turbine airfoil includes opposite pressure and suction sides joined together at leading and trailing edges. An outwardly convex nose bridge bridges the pressure and suction sides behind the leading edge, and is integrally joined to a complementary thermally insulating shield spaced therefrom to define a bridge channel. The shield includes the leading edge and wraps laterally aft around the nose bridge along both the pressure and suction sides.

    Abstract translation: 涡轮机翼片包括在前缘和后缘处连接在一起的相对的压力和吸力侧。 一个向外凸起的鼻梁桥接了前缘后面的压力和吸力侧，并且与其隔开的互补隔热屏蔽件整体地接合以限定桥接通道。 护罩包括前缘，沿着压力和吸力侧在鼻梁周围侧向包裹。

    Triple circuit turbine blade
    94.
    发明授权
    Triple circuit turbine blade 失效
    三回路涡轮叶片

    公开(公告)号：US06984103B2

    公开(公告)日：2006-01-10

    申请号：US10718465

    申请日：2003-11-20

    Applicant: Ching-Pang Lee ,  Steven Robert Brassfield ,  Chander Prakash

    Inventor： Ching-Pang Lee ,  Steven Robert Brassfield ,  Chander Prakash

    IPC: F03D11/00

    CPC classification number: F01D5/187 ,  Y02T50/673 ,  Y02T50/676

    Abstract: A turbine blade includes an airfoil having pressure and suction sidewalls extending between leading and trailing edges, and from root to tip. A dovetail is joined to the airfoil root at a platform. Three internal cooling circuits extend in span inside the airfoil, and each circuit includes a respective inlet channel commencing in axially adjacent alignment in the dovetail. The inlet channels twist together from the dovetail, through the platform, and into the airfoil behind the leading edge in transverse adjacent alignment across the sidewalls.

    Abstract translation: 涡轮叶片包括具有在前缘和后缘之间延伸的压力和吸力侧壁以及从根部到尖端的翼型件。 燕尾榫在平台上连接到翼型根部。 三个内部冷却回路在翼型内部的跨度上延伸，并且每个回路包括相应的入口通道，其从燕尾榫开始轴向相邻对准。 入口通道从燕尾榫通过平台扭转在一起，并且横跨相邻的侧壁横向相邻对齐，并进入前缘的后翼。

    Synthetic model casting
    95.
    发明申请
    Synthetic model casting 有权
    合成模型铸造

    公开(公告)号：US20050205232A1

    公开(公告)日：2005-09-22

    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: B22C9/04 ,  B22C9/10 ,  B29C67/00 ,  B22C9/02

    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。

    Casting having an enhanced heat transfer, surface, and mold and pattern for forming same
    99.
    发明授权
    Casting having an enhanced heat transfer, surface, and mold and pattern for forming same 失效
    铸造具有增强的热传递，表面和模具以及用于形成它们的图案

    公开(公告)号：US06786982B2

    公开(公告)日：2004-09-07

    申请号：US10279654

    申请日：2002-10-24

    Applicant: Ching Pang Lee ,  Wayne Charles Hasz ,  Nesim Abuaf ,  Robert Alan Johnson

    Inventor： Ching Pang Lee ,  Wayne Charles Hasz ,  Nesim Abuaf ,  Robert Alan Johnson

    IPC: C22C3800

    CPC classification number: B22C9/04 ,  B22C7/02 ,  B22C9/02 ,  B22D25/06

    Abstract: A casting includes a heat transfer surface having a plurality of cavities. The plurality of cavities include a density of at least about 25 cavities per square centimeter to about 1,100 cavities per square centimeter resulting in increased surface area and therefore enhanced heat transfer capability. Also disclosed is a mold for forming a pattern for molding the casting. The mold includes a surface defining a portion of a chamber to which are attached a plurality of particles having an average particle size in a range of about 300 microns to about 2,000 microns.

    Abstract translation: 铸件包括具有多个空腔的传热表面。 多个空腔包括每平方厘米至少约25个腔体至每平方厘米约1,100个空腔的密度，导致增加的表面积并因此提高传热能力。 还公开了一种用于形成用于模制铸件的图案的模具。 模具包括限定室的一部分的表面，其中连接有平均粒度在约300微米至约2,000微米范围内的多个颗粒。

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