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    METHOD OF FORMING CONCAVITIES IN THE SURFACE OF A METAL COMPONENT, AND RELATED PROCESSES AND ARTICLES
    81.
    发明申请
    METHOD OF FORMING CONCAVITIES IN THE SURFACE OF A METAL COMPONENT, AND RELATED PROCESSES AND ARTICLES 有权
    金属部件表面形成方法及相关工艺及文章

    公开(公告)号：US20070235157A1

    公开(公告)日：2007-10-11

    申请号：US10841366

    申请日：2004-05-06

    Applicant: Ronald Bunker ,  Canan Hardwicke ,  Ching-Pang Lee

    Inventor： Ronald Bunker ,  Canan Hardwicke ,  Ching-Pang Lee

    IPC: B22C9/00 ,  B22C9/10

    CPC classification number: B22C9/10 ,  B33Y10/00 ,  C04B41/009 ,  C04B41/5031 ,  C04B41/87 ,  C04B2111/0087 ,  C23C4/01 ,  F05B2260/222 ,  C04B41/4539 ,  C04B41/4572 ,  C04B41/5029 ,  C04B35/04 ,  C04B35/10 ,  C04B35/14 ,  C04B35/18 ,  C04B35/565 ,  C04B35/48 ,  C04B35/584 ,  C04B35/481 ,  C04B35/505

    Abstract: A method of forming at least one concavity of a selected size and shape within a surface of an internal passageway of a metallic component comprises: depositing a ceramic-based material by a direct-write technique onto a ceramic core which is suitable for forming the internal passageway during a casting process to form the metallic component, wherein the ceramic-based material is deposited as a positive feature; heat-treating the deposited ceramic-based material; forming the metallic component by a casting process in which the ceramic core is incorporated into the casting, in a position selected as a desired position for the internal passageway; and then removing the ceramic core from the metal component after the casting process is complete, thereby forming the internal passageway, with the concavity contained within the surface of the passageway, said concavity formed by removal of the positive feature of the ceramic-based material.

    Abstract translation: 在金属部件的内部通道的表面内形成选定尺寸和形状的至少一个凹部的方法包括：通过直接写入技术将陶瓷基材料沉积到适于形成内部的陶瓷芯上 在铸造过程中形成金属部件的通道，其中所述陶瓷基材料作为阳性特征沉积; 对沉积的陶瓷基材料进行热处理; 通过铸造工艺形成金属部件，其中将陶瓷芯体结合到铸件中，位于被选择为内部通道的期望位置的位置; 然后在铸造过程完成之后从金属部件上除去陶瓷芯，由此形成内部通道，凹部包含在通道的表面内，通过去除陶瓷基材料的积极特征而形成所述凹部。

    Methods and apparatus for assembling turbine engines
    82.
    发明申请
    Methods and apparatus for assembling turbine engines 审中-公开
    涡轮发动机组装方法及装置

    公开(公告)号：US20070134087A1

    公开(公告)日：2007-06-14

    申请号：US11297082

    申请日：2005-12-08

    Applicant: Ching-Pang Lee ,  Joseph Guentert ,  Wenfeng Lu ,  Mitchell Iles ,  Douglas Fortuna

    Inventor： Ching-Pang Lee ,  Joseph Guentert ,  Wenfeng Lu ,  Mitchell Iles ,  Douglas Fortuna

    IPC: F01D9/00

    CPC classification number: F01D9/023 ,  F01D9/042 ,  F01D25/246 ,  F05D2300/505 ,  Y02T50/673 ,  Y02T50/675

    Abstract: A method facilitates the assembly of a gas turbine engine. The method of assembly comprises providing a turbine nozzle including an inner band, an outer band, and at least one vane extending between the inner and outer bands, coupling the turbine nozzle within the gas turbine engine, such that the turbine nozzle is downstream from a combustor, and coupling the turbine nozzle to the combustor using at least a first annular ring, wherein the first annular ring substantially seals a gap defined between the turbine nozzle and the combustor.

    Abstract translation: 一种方法有助于燃气涡轮发动机的组装。 组装方法包括提供涡轮喷嘴，其包括内带，外带，以及在内带和外带之间延伸的至少一个叶片，将涡轮喷嘴连接在燃气涡轮发动机内，使得涡轮喷嘴在 燃烧器，并且使用至少第一环形环将涡轮喷嘴耦合到燃烧器，其中第一环形圈基本上密封限定在涡轮喷嘴和燃烧器之间的间隙。

    Bullnose step turbine nozzle
    84.
    发明授权
    Bullnose step turbine nozzle 有权
    Bullnose级涡轮喷嘴

    公开(公告)号：US07195454B2

    公开(公告)日：2007-03-27

    申请号：US11002570

    申请日：2004-12-02

    Applicant: Wenfeng Lu ,  Ching-Pang Lee ,  Nicholas Charles Palmer

    Inventor： Wenfeng Lu ,  Ching-Pang Lee ,  Nicholas Charles Palmer

    IPC: F03B1/04 ,  F03B3/16

    CPC classification number: F01D5/143 ,  F01D5/145 ,  F01D9/041 ,  F01D11/005 ,  F01D25/246 ,  F05D2250/19 ,  Y02T50/673

    Abstract: A turbine airfoil includes opposite pressure and suction sides extending in span from a flowpath surface. The flowpath surface has chordally opposite forward and aft edges and laterally opposite first and second endfaces corresponding with the airfoil pressure and suction sides. The flowpath surface joins the first endface at the forward edge in a forward bullnose and joins the second endface at the aft edge in an aft bullnose, with the bullnoses varying in radius from the opposite edges.

    Abstract translation: 涡轮机翼型包括从流路表面跨越的相对的压力和吸力侧。 流路表面具有弦向相反的前后边缘，并且与翼型压力和吸力侧对应的横向相对的第一和第二端面。 流路表面将前端长嘴的前边缘处的第一端面连接起来，并且在后方长臂处的后边缘处连接第二端面，其中棱镜从相对边缘的半径变化。

    TURBINE AIRFOIL WITH CURVED SQUEALER TIP
    85.
    发明申请
    TURBINE AIRFOIL WITH CURVED SQUEALER TIP 有权
    涡轮发动机带有弯曲的螺母提示

    公开(公告)号：US20070059182A1

    公开(公告)日：2007-03-15

    申请号：US11162433

    申请日：2005-09-09

    Applicant: Mark Stegemiller ,  Chander Prakash ,  Leslie Leeke ,  Kevin Klasing ,  Ching-Pang Lee

    Inventor： Mark Stegemiller ,  Chander Prakash ,  Leslie Leeke ,  Kevin Klasing ,  Ching-Pang Lee

    IPC: B64C27/46

    CPC classification number: F01D5/20 ,  F05D2250/71 ,  F05D2250/712 ,  Y02T50/67

    Abstract: An airfoil for a gas turbine engine includes a root, a tip, a leading edge, a trailing edge, and opposed pressure and suction sidewalls extending generally along a radial axis. The airfoil includes a tip cap extending between the pressure and suction sidewalls; and spaced-apart suction-side and pressure-side tip walls extending radially outward from the tip cap to define a tip cavity therebetween. The pressure-side tip wall includes a continuously concave curved arcuate portion, at least a section of which extends circumferentially outward from a radial axis of the airfoil.

    Abstract translation: 用于燃气涡轮发动机的翼型件包括根部，尖端，前缘，后缘以及大致沿径向轴线延伸的相对的压力和吸力侧壁。 翼型件包括在压力侧和吸力侧壁之间延伸的顶盖; 并且间隔开的吸入侧和压力侧尖端壁从尖端帽径向向外延伸以在它们之间限定尖端腔。 压力侧末端壁包括连续凹入的弯曲弧形部分，其至少一部分从翼型件的径向轴向向外延伸。

    METHOD AND APPARATUS FOR REDUCING TURBINE BLADE TEMPERATURES
    86.
    发明申请
    METHOD AND APPARATUS FOR REDUCING TURBINE BLADE TEMPERATURES 失效
    减少涡轮叶片温度的方法和装置

    公开(公告)号：US20070059172A1

    公开(公告)日：2007-03-15

    申请号：US10824283

    申请日：2004-04-14

    Applicant: Ching-Pang Lee ,  Aspi Wadia ,  Steven Brassfield

    Inventor： Ching-Pang Lee ,  Aspi Wadia ,  Steven Brassfield

    IPC: F01D5/18

    CPC classification number: F01D5/187 ,  Y02T50/676

    Abstract: An airfoil for a gas turbine engine includes a first sidewall and a second sidewall coupled together at a leading edge and atrailing edge, such that a cavity is defined therebetween. A plurality of rib walls extends at least partially between the first and second sidewalls, wherein the plurity of rib walls define at least one cooling circuit having at least three cooling chambers. At least one row of openings extend through at least one of the rib walls, wherein a first of cooling chambers supplies cooling fluid to the cavity, and the remaining cooling chambers are coupled in flow communication with the first cooling chamber via the openings.

    Abstract translation: 用于燃气涡轮发动机的翼型件包括在前缘和后缘处联接在一起的第一侧壁和第二侧壁，使得在其间限定空腔。 多个肋壁至少部分地在第一和第二侧壁之间延伸，其中肋壁的柔软度限定了至少一个具有至少三个冷却室的冷却回路。 至少一排开口延伸穿过所述肋壁中的至少一个，其中第一冷却室将冷却流体供应到空腔，并且剩余的冷却室经由所述开口与第一冷却室流动连通地联接。

    Crescentic ramp turbine stage
    89.
    发明申请
    Crescentic ramp turbine stage 有权
    新月形斜坡涡轮机阶段

    公开(公告)号：US20060233641A1

    公开(公告)日：2006-10-19

    申请号：US11106198

    申请日：2005-04-14

    Applicant: Ching-Pang Lee ,  Anna Tam ,  Kevin Kirtley ,  Scott Lamson

    Inventor： Ching-Pang Lee ,  Anna Tam ,  Kevin Kirtley ,  Scott Lamson

    IPC: F03B11/02

    CPC classification number: F01D5/143 ,  F05D2250/711 ,  F05D2250/712 ,  Y02T50/673 ,  Y10S415/914

    Abstract: A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Each platform includes a crescentic ramp increasing in height from the leading and trailing edges toward the midchord of the airfoil along the pressure side thereof.

    Abstract translation: 涡轮级包括连接到相应平台的一排翼型件，以限定它们之间的流动通道。 每个翼型件包括相对的压力和吸力侧面，并且在相对的前缘和后缘之间延伸成弦。 每个平台包括沿其压力侧从翼型的前缘和后缘向中部的高度增加的新月形斜面。

    COMMON TIP CHAMBER BLADE
    90.
    发明申请
    COMMON TIP CHAMBER BLADE 失效
    普通烤箱

    公开(公告)号：US20060062671A1

    公开(公告)日：2006-03-23

    申请号：US10898835

    申请日：2004-07-26

    Applicant: Ching-Pang Lee ,  Wenfeng Lu

    Inventor： Ching-Pang Lee ,  Wenfeng Lu

    IPC: F01D5/18

    CPC classification number: F01D5/20 ,  F01D5/081 ,  F01D5/187 ,  F05D2260/607 ,  Y02T50/673 ,  Y02T50/676

    Abstract: A turbine blade includes an airfoil having pressure and suction sidewalls spaced apart between opposite leading and trailing edges and interconnected by a plurality of partitions to define first and second independent cooling circuits therein. The cooling circuits have corresponding inlets in a dovetail of the blade and extend through a platform of the blade and through the airfoil to its tip. A common discharge chamber is disposed below the airfoil tip and includes a plurality of outlet holes for discharging cooling air from the circuits.

    Abstract translation: 涡轮机叶片包括具有在相对的前缘和后缘间隔开的压力和吸力侧壁的翼型件，并通过多个隔板互连以在其中限定第一和第二独立冷却回路。 冷却回路在叶片的燕尾形中具有相应的入口，并延伸穿过叶片的平台并且通过翼型件到其顶端。 公共排放室设置在翼型件末端的下方，并且包括用于从电路排出冷却空气的多个出口孔。

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