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    Apparatus for hybrid vapor and film cooling of a turbine blade
    21.
    发明授权
    Apparatus for hybrid vapor and film cooling of a turbine blade 有权
    Vorrichtung zur hybriden Verdampfungs- undFilmkühlungeiner Turbinenschaufel

    公开(公告)号：EP1908922B1

    公开(公告)日：2015-05-27

    申请号：EP07253811.9

    申请日：2007-09-26

    Applicant: United Technologies Corporation

    Inventor： Norris, James W. ,  Hill, James D.

    IPC: F01D5/18 ,  F01D5/08 ,  F01D5/30

    CPC classification number: F01D5/18 ,  F01D5/082 ,  F01D5/181 ,  F01D5/187 ,  F01D5/3007 ,  F05D2260/202 ,  F05D2260/205 ,  F05D2260/207 ,  F05D2260/22141

    Abstract: An apparatus for a gas turbine engine includes an airfoil (22) defining a leading edge (28) and a trailing edge (30), a root (26) located adjacent to the airfoil (22), a vapor cooling system, and a film cooling system for cooling the airfoil in conjunction with the vapor cooling system. The vapor cooling system includes a vaporization section (36) located within the airfoil (22) and a condenser (40) section located within the root (26).

    Abstract translation: 一种用于燃气涡轮发动机的装置包括限定前缘（28）和后缘（30）的翼型件（22），邻近翼型件（22）定位的根部（26），蒸汽冷却系统和薄膜 冷却系统，用于与蒸气冷却系统一起冷却翼型。 蒸汽冷却系统包括位于机翼（22）内的蒸发部分（36）和位于根部（26）内的冷凝器（40）部分。

    Rotating vane seal with cooling air passages
    23.
    发明公开
    Rotating vane seal with cooling air passages 审中-公开
    Dichtung einesFlügelradesmitKühlluftdurchgänge

    公开(公告)号：EP2586992A2

    公开(公告)日：2013-05-01

    申请号：EP12189312.7

    申请日：2012-10-19

    Applicant: United Technologies Corporation

    Inventor： Norris, James W. ,  Bridges, Jr., Joseph W.

    IPC: F01D11/00

    CPC classification number: F01D11/005 ,  F01D11/001 ,  F02C7/12 ,  F02C7/18 ,  F04D29/164 ,  F04D29/545 ,  F04D29/547 ,  F05D2260/941

    Abstract: An inner diameter vane seal (42) for a gas turbine engine (10) comprises an annular, ring-like body having inner and outer diameter rims (56, 54), forward and aft faces (47A, 47B) and an air passage (74). The outer diameter rim (54) extends circumferentially for engaging inner diameter ends (73) of stator vanes (38). The inner diameter rim (56) extends circumferentially and is spaced radially from the outer diameter rim (54). The forward and aft faces (47A, 47B) extend radially between the outer diameter rim (54) and the inner diameter rim (56). The air passage (74) extends from the forward face (47A) to the aft face (47B) between the inner and outer diameter rims (56, 54).

    Abstract translation: 用于燃气涡轮发动机（10）的内径叶片密封件（42）包括具有内径和外径边缘（56,54）的环形环形体，前和后面（47A，47B）和空气通道 74）。 外径边缘（54）周向延伸，用于接合定子叶片（38）的内径端部（73）。 内径边缘（56）周向延伸并且与外直径边缘（54）径向间隔开。 前外表面（47A，47B）在外径边缘（54）和内径边缘（56）之间径向延伸。 空气通道（74）从前外表面（47A）延伸到内直径边缘（56,54）之间的后表面（47B）。

    Multiple core variable cycle gas turbine engine and method of operation
    25.
    发明公开
    Multiple core variable cycle gas turbine engine and method of operation 有权
    Gasturbinenmotor mit mehrfachen Kerntriebwerke und Betriebsverfahren

    公开(公告)号：EP2518293A2

    公开(公告)日：2012-10-31

    申请号：EP12165824.9

    申请日：2012-04-26

    Applicant: United Technologies Corporation

    Inventor： Norris, James W.

    IPC: F02C3/14 ,  F02K3/06 ,  F02K3/12

    CPC classification number: F02K3/12 ,  F02C3/145 ,  F02C9/18 ,  F02K3/06 ,  F02K3/077 ,  F05D2230/52 ,  F05D2240/40 ,  F05D2250/314 ,  Y02T50/671

    Abstract: A gas turbine engine system (10) includes a fan assembly (12), a low pressure compressor (14), a low pressure turbine (16), a plurality of engine cores (30-1 to 30-n) including a first engine core and a second engine core, and a control assembly (36). A primary flowpath (F P ) is defined through the fan assembly (12), the low pressure compressor (14), the low pressure turbine (16), and the active engine cores. Each engine core includes a high pressure compressor (40), a combustor (38) downstream from the high pressure compressor (40), and a high pressure turbine (42) downstream from the combustor (38). The control assembly (36) is configured to control operation of the plurality of engine cores (30-1 to 30-n) such that in a first operational mode the first and the second engine cores are active to generate combustion products and in a second operational mode the first engine core is active to generate combustion products while the second engine core is idle.

    Abstract translation: 燃气涡轮发动机系统（10）包括风扇组件（12），低压压缩机（14），低压涡轮机（16），包括第一发动机的多个发动机机芯（30-1至30-n） 芯和第二发动机芯，以及控制组件（36）。 主流道（F P）通过风扇组件（12），低压压缩机（14），低压涡轮机（16）和主动发动机内芯来定义。 每个发动机芯包括高压压缩机（40），来自高压压缩机（40）下游的燃烧器（38）和在燃烧器（38）下游的高压涡轮机42。 控制组件（36）构造成控制多个发动机机芯（30-1至30-n）的操作，使得在第一操作模式中，第一和第二发动机机芯有效以产生燃烧产物，并且在第二操作模式 操作模式，第一个发动机内燃机在第二个发动机机芯空转时有效地产生燃烧产物。

    Non-interrupted oil supply for gas turbine engine
    26.
    发明公开
    Non-interrupted oil supply for gas turbine engine 有权
    Nicht-unterbrocheneÖlversorgungfürGasturbinenmotor

    公开(公告)号：EP2103794A3

    公开(公告)日：2012-01-04

    申请号：EP09250626.0

    申请日：2009-03-04

    Applicant: United Technologies Corporation

    Inventor： Norris, James W.

    IPC: F02C7/06 ,  F01D25/20

    CPC classification number: F01D25/20 ,  F02C7/06

    Abstract: An oil supply system for a gearbox (22) in a gas turbine engine includes a holding container (50) which holds a quantity of oil to be delivered to a pump. The holding container includes a flexible barrier (60). One side of the flexible barrier (60) is in communication with a source of pressurized fluid through a connection (31). The other side is in communication with the oil supply.

    Abstract translation: 用于燃气涡轮发动机中的齿轮箱（22）的供油系统包括：保持容器（50），其保持要输送到泵的一定量的油。 保持容器包括柔性屏障（60）。 柔性屏障（60）的一侧通过连接（31）与加压流体源连通。 另一方是与供油机通信。

    Hybrid cooling of a gas turbine engine
    28.
    发明公开
    Hybrid cooling of a gas turbine engine 有权
    混合冷却的燃气涡轮发动机

    公开(公告)号：EP2003311A3

    公开(公告)日：2011-04-27

    申请号：EP08252045.3

    申请日：2008-06-13

    Applicant: United Technologies Corporation

    Inventor： Norris, James W. ,  Hill, James D. ,  Raver, Bernard J.

    IPC: F02C7/14 ,  F02C7/18 ,  F02C7/224

    CPC classification number: F02C7/185 ,  F02C7/14 ,  F02C7/224 ,  F05D2260/205 ,  F05D2260/207 ,  F05D2260/213

    Abstract: A hybrid cooling system for a gas turbine engine (10) includes a vapor cooling assembly (26) and a cooling air cooling assembly (16). The cooling air cooling assembly (16) is configured to remove thermal energy from cooling air used to cool a first component (12) of the gas turbine engine (10). The vapor cooling assembly (26) configured to transport thermal energy from a vaporization section (52) to a condenser section (54) through cyclical evaporation and condensation of a working medium sealed within the vapor cooling assembly (26). The vaporization section (52) is located at least partially within a second component (14) of the gas turbine engine, and the condenser section (54) is located outside the second component (14).

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