公开(公告)号：EP2586992A3

公开(公告)日：2016-11-23

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 ,  F04D29/16 ,  F02C7/12 ,  F04D29/54 ,  F02C7/18

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).

公开(公告)号：EP2518293A3

公开(公告)日：2015-04-08

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 ,  F02K3/077 ,  F02C9/18

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.

公开(公告)号：EP2586969A2

公开(公告)日：2013-05-01

申请号：EP12190261.3

申请日：2012-10-26

Applicant: United Technologies Corporation

Inventor： Suciu, Gabriel L. ,  Muron, Stephen P. ,  Alvanos, Ioannis ,  Dye, Christopher M. ,  Merry, Brian D. ,  Salve, Arthur M. ,  Norris, James W.

IPC: F01D5/08 ,  F01D11/00 ,  F01D25/12 ,  F01D5/30

Abstract: A rotor (60C) for a gas turbine engine includes a plurality of blades (64) which extend from a rotor disk (66), each of the plurality of blades (64) extends from the rotor disk (66) at an interface (801), the interface (801) defined along a spoke (80).

Abstract translation: 用于燃气涡轮发动机的转子（60C）包括从转子盘（66）延伸的多个叶片（64），多个叶片（64）中的每一个在转子盘（66）的界面处 ），沿着辐条（80）限定的接口（801）。

公开(公告)号：EP2586968A2

公开(公告)日：2013-05-01

申请号：EP12190258.9

申请日：2012-10-26

Applicant: United Technologies Corporation

Inventor： Suciu, Gabriel L. ,  Dye, Christopher M. ,  Ackermann, William K. ,  Muron, Stephen P. ,  Alvanos, Ioannis ,  Merry, Brian D. ,  Salve, Arthur M. ,  Norris, James W.

IPC: F01D5/08 ,  F01D5/30 ,  F01D11/00 ,  F01D25/12

CPC classification number: F01D5/084 ,  F01D5/3061 ,  F01D11/008 ,  F01D25/12

Abstract: A rotor (60) for a gas turbine engine includes a plurality of blades (64) which extend from a rotor disk (66) and at least one spacer (62CA) adjacent to the plurality of blades (64). A flow passage is defined between the rotor disk (66) and the blades (62) and spacer (62CA). A plurality of inlets (88) are formed within the spacer (62CA) to pump air into the flow passage.

公开(公告)号：EP2000648A3

公开(公告)日：2010-12-01

申请号：EP08251971.1

申请日：2008-06-06

Applicant: United Technologies Corporation

Inventor： Norris, James W. ,  Berryman, Andrew P.

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

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

Abstract: A gas turbine engine (10) is provided with a first heat exchanger (58,64,72) associated with a cooling air flow to deliver cooling air to a turbine section (15). A second heat exchanger (52) is associated with a fuel supply line (50) for delivering fuel into a combustion section (14). An intermediate fluid cools air at the first heat exchanger (58,64,72) and heats fuel at the second heat exchanger (52).

公开(公告)号：EP1908922A3

公开(公告)日：2010-05-05

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。

公开(公告)号：EP2103794A2

公开(公告)日：2009-09-23

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.

公开(公告)号：EP1961514A3

公开(公告)日：2009-08-05

申请号：EP08250563.7

申请日：2008-02-19

Applicant: United Technologies Corporation

Inventor： Twelves, Wendell V, Jr. ,  Norris, James W. ,  Raver, Bernard J.

IPC: G05B19/418 ,  G05B19/409 ,  B23P21/00 ,  B23Q41/06

CPC classification number: B23P21/004 ,  B22F3/1055 ,  B22F2003/1056 ,  B23K26/364 ,  B33Y10/00 ,  B33Y30/00 ,  B33Y40/00 ,  B33Y80/00 ,  G05B19/4099 ,  G05B19/4188 ,  G05B2219/32397 ,  G05B2219/49016 ,  Y02P10/295 ,  Y02P80/40 ,  Y02P90/24 ,  Y10T29/51

Abstract: An integrated additive manufacturing cell (IAMC) (101) that combines conventional manufacturing technologies with additive manufacturing processes is disclosed. Individual IAMCs (101) may be configured and optimized for specific part families of complex components, or other industrial applications. The IAMCs incorporate features that reduce hardware cost and time and allow for local alloy tailoring for material properties optimization in complex components. In one embodiment the IMAC (101) comprises an enclosed central manufacturing cell (103) having a plurality of access ports (105). A mechanical and electrical port interface is associated with each access port (105) to couple power, communications and mechanical utilities with an external module (107...115).

公开(公告)号：EP2003311A2

公开(公告)日：2008-12-17

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).

Abstract translation: 用于燃气涡轮发动机（10）的混合冷却系统包括蒸汽冷却组件（26）和冷却空气冷却组件（16）。 冷却空气冷却组件（16）构造成从用于冷却燃气涡轮发动机（10）的第一部件（12）的冷却空气中去除热能。 蒸汽冷却组件（26）构造成通过循环蒸发和密封在蒸气冷却组件（26）内的工作介质的冷凝，将热能从蒸发部分（52）运送到冷凝器部分（54）。 蒸发部分（52）至少部分地位于燃气涡轮发动机的第二部件（14）内，并且冷凝器部分（54）位于第二部件（14）的外部。

公开(公告)号：EP1591622A3

公开(公告)日：2006-11-15

申请号：EP05252294.3

申请日：2005-04-13

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Suciu, Grabiel L. ,  Norris, James W.

IPC: F01D5/06

CPC classification number: F01D11/001 ,  F01D5/06 ,  Y10T29/4932 ,  Y10T29/49716

Abstract: A gas turbine engine rotor stack (32) includes one or more longitudinally outwardly concave spacers (62C). The spacers may provide a longitudinal compression force that increases with rotational speed.