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    Interstage cooled turbine engine
    71.
    发明申请
    Interstage cooled turbine engine 有权
    级间冷却涡轮发动机

    公开(公告)号：US20080112793A1

    公开(公告)日：2008-05-15

    申请号：US11595606

    申请日：2006-11-10

    Applicant: Ching-Pang Lee ,  Thomas Ory Moniz ,  Robert Joseph Orlando

    Inventor： Ching-Pang Lee ,  Thomas Ory Moniz ,  Robert Joseph Orlando

    IPC: F01D5/18

    CPC classification number: F01D5/088 ,  F01D5/082 ,  F05D2260/20 ,  Y02T50/672 ,  Y02T50/676

    Abstract: A gas turbine engine includes a compressor, combustor, and high pressure (HP) turbine operatively joined together. An interstage cooling circuit is joined in flow communication from an intermediate stage of the compressor to a forward face of an HP disk supporting a row of turbine blades for channeling interstage bleed cooling air thereto.

    Abstract translation: 燃气涡轮发动机包括可操作地连接在一起的压缩机，燃烧器和高压（HP）涡轮机。 级间冷却回路从压缩机的中间阶段流动连接到支撑一排涡轮机叶片的HP盘的前面，用于将级间排放冷却空气引导到其中。

    Compound turbine cooled engine
    72.
    发明申请
    Compound turbine cooled engine 有权
    复合涡轮冷却发动机

    公开(公告)号：US20080112791A1

    公开(公告)日：2008-05-15

    申请号：US11595668

    申请日：2006-11-10

    Applicant: Ching-Pang Lee ,  Thomas Ory Moniz ,  Robert Joseph Orlando

    Inventor： Ching-Pang Lee ,  Thomas Ory Moniz ,  Robert Joseph Orlando

    IPC: F02C9/18

    CPC classification number: F01D9/065 ,  F01D25/12 ,  F02C7/12 ,  Y02T50/671 ,  Y02T50/675

    Abstract: A gas turbine engine includes a compressor, combustor, and high pressure turbine operatively joined together. The turbine includes a row of nozzle vanes followed by a row of rotor blades. The vanes and blades have corresponding forward and aft internal cooling channels. First, second, third, and fourth bleed circuits are joined in flow communication with different stages of the compressor for bleeding pressurized air therefrom at different pressures to provide coolant to the forward and aft channels of the turbine vanes and blades.

    Abstract translation: 燃气涡轮发动机包括可操作地连接在一起的压缩机，燃烧器和高压涡轮机。 涡轮机包括一排喷嘴叶片，随后是一排转子叶片。 叶片和叶片具有相应的前后冷却通道。 第一，第二，第三和第四泄放回路与压缩机的不同级联流动连通，以在不同压力下从其中排出加压空气，以向涡轮机叶片和叶片的前后通道提供冷却剂。

    Turbine airfoil with variable and compound fillet
    73.
    发明授权
    Turbine airfoil with variable and compound fillet 有权
    涡轮机翼与可变和复合圆角

    公开(公告)号：US07371046B2

    公开(公告)日：2008-05-13

    申请号：US11160010

    申请日：2005-06-06

    Applicant: Ching-Pang Lee ,  Joseph Michael Guentert ,  James Robert Bailey

    Inventor： Ching-Pang Lee ,  Joseph Michael Guentert ,  James Robert Bailey

    IPC: F04D29/54

    CPC classification number: F01D5/143 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2240/80 ,  Y02T50/673

    Abstract: A turbine airfoil may be a rotating blade having a single platform, or a stationary nozzle having a pair of platforms. The airfoil body has pressure and suction sidewalls extending between leading and trailing edges. A compound fillet is disposed between the airfoil body and at least one of the platforms. The compound fillet includes a concave first fillet having a first radius, and a concave second fillet having a second, greater radius. The second fillet extends from the leading edge downstream along the suction sidewall and terminates at a point upstream of the trailing edge. The second fillet may also extend downstream from the leading edge along the pressure sidewall.

    Abstract translation: 涡轮机翼片可以是具有单个平台的旋转叶片或具有一对平台的固定喷嘴。 机翼本体具有在前缘和后缘之间延伸的压力和吸力侧壁。 在翼型件本体和至少一个平台之间设置复合内圆角。 复合圆角包括具有第一半径的凹入的第一圆角和具有第二较大半径的凹入的第二圆角。 第二圆角从前缘沿着吸力侧壁向下游延伸，并终止在后缘上游的一个点处。 第二圆角也可以沿着压力侧壁从前缘的下游延伸。

    TURBINE BLADE TIP SQUEALER AND REBUILD METHOD
    75.
    发明申请
    TURBINE BLADE TIP SQUEALER AND REBUILD METHOD 失效
    涡轮叶片推进器和重建方法

    公开(公告)号：US20080060197A1

    公开(公告)日：2008-03-13

    申请号：US11766509

    申请日：2007-06-21

    Applicant: Ching-Pang Lee

    Inventor： Ching-Pang Lee

    IPC: B21K3/04

    CPC classification number: B23P6/007 ,  F01D5/005 ,  F01D5/20 ,  F05D2260/202 ,  Y10T29/49318 ,  Y10T29/49337 ,  Y10T29/49339 ,  Y10T29/49341 ,  Y10T29/49728 ,  Y10T29/53091

    Abstract: A turbine blade with a tip squealer and method of rebuilding a turbine blade for a gas turbine engine. The blade is of the type including an airfoil having first and second spaced-apart sidewalls defining an interior void and joined at a leading edge and a trailing edge. The first and second sidewalls extending from a root disposed adjacent the dovetail to a tip cap for channeling combustion gases, and a squealer tip including at least one tip rib extending outwardly from the tip cap. The method includes the steps of removing the squealer tip, including the at least one rib tip, from the tip cap and adding new material to the tip cap to serve as a new squealer tip. A plurality of spaced-apart notches is formed in the new material between the leading edge and the trailing edge of the airfoil. At least one hole is formed in each notch communicating with the interior void of the airfoil for channeling cooling air from the interior void of the airfoil to thereby form a squealer tip.

    Abstract translation: 具有尖端喷嘴的涡轮机叶片和用于重建用于燃气涡轮发动机的涡轮机叶片的方法。 叶片类型包括具有限定内部空隙并且在前缘和后缘处连接的第一和第二间隔开的侧壁的翼型件。 所述第一和第二侧壁从邻近所述燕尾榫设置的根部延伸到用于引导燃烧气体的尖端帽，以及尖叫尖端，其包括从所述尖端帽向外延伸的至少一个尖端肋。 该方法包括以下步骤：从顶盖移除包括至少一个肋尖端的尖叫尖端，并将新材料添加到尖端盖以用作新的尖叫尖端。 在翼缘的前缘和后缘之间的新材料中形成多个间隔开的凹口。 在与翼型件的内部空隙连通的每个凹口中形成至少一个孔，用于从翼型的内部空间引导冷却空气，从而形成尖叫尖端。

    Counter tip baffle airfoil
    77.
    发明申请
    Counter tip baffle airfoil 有权
    台顶挡板翼型

    公开(公告)号：US20080044291A1

    公开(公告)日：2008-02-21

    申请号：US11507132

    申请日：2006-08-21

    Applicant: Ching-Pang Lee ,  Kevin Samuel Klasing ,  Paul Hadley Vitt ,  Brian David Keith

    Inventor： Ching-Pang Lee ,  Kevin Samuel Klasing ,  Paul Hadley Vitt ,  Brian David Keith

    IPC: B64C11/16

    CPC classification number: F01D5/20 ,  F01D5/145 ,  F05D2250/70 ,  Y02T50/671 ,  Y02T50/673

    Abstract: A turbine blade includes an airfoil having first and second tip ribs extending along the opposite pressure and suction sides thereof The tip ribs are spaced apart between the leading and trailing edges of the airfoil to include a tip baffle. The baffle extends chordally in counter profile with the first rib to define a first pocket, and in counter profile with the second rib to define a second pocket.

    Abstract translation: 涡轮叶片包括具有沿其相对的压力和吸力侧延伸的第一和第二末端肋的翼型件。末端肋在翼型的前缘和后缘之间间隔开，以包括顶端挡板。 所述挡板以第一肋条与第一肋条相反地延伸，以相反轮廓延伸，以限定第一凹槽，并且与第二肋条对置形成第二凹槽。

    Conformal tip baffle airfoil
    78.
    发明申请
    Conformal tip baffle airfoil 有权
    保形挡板翼型

    公开(公告)号：US20080044290A1

    公开(公告)日：2008-02-21

    申请号：US11507121

    申请日：2006-08-21

    Applicant: Kevin Samuel Klasing ,  Ching-Pang Lee ,  Paul Hadley Vitt ,  Brian David Keith

    Inventor： Kevin Samuel Klasing ,  Ching-Pang Lee ,  Paul Hadley Vitt ,  Brian David Keith

    IPC: B64C11/16

    CPC classification number: F01D5/20 ,  F01D5/187 ,  F05D2250/185 ,  F05D2250/70 ,  Y02T50/673 ,  Y02T50/676

    Abstract: A turbine blade includes an airfoil tip with first and second tip ribs extending from a tip floor. The ribs extend along the opposite pressure and suction sides of the blade and are joined together at opposite leading and trailing edges. A tip baffle is nested transversely between the ribs, and conforms with the second rib to bifurcate the airfoil tip into first and second tip pockets extending along the corresponding pressure and suction sides.

    Abstract translation: 涡轮机叶片包括具有从尖端底板延伸的第一和第二末端肋的翼面末端。 肋沿刀片的相对的压力和吸力侧延伸并且在相对的前缘和后缘连接在一起。 尖端挡板横向嵌套在肋之间，并且与第二肋条一致，以使翼型件尖端分叉成沿相应的压力侧和吸力侧延伸的第一和第二尖端口袋。

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