公开(公告)号：EP2586970A3

公开(公告)日：2017-05-24

申请号：EP12190264.7

申请日：2012-10-26

Applicant: United Technologies Corporation

Inventor： Suciu, Gabriel L. ,  Muron, Stephen P. ,  Dye, Christopher M. ,  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 spacer (62C) for a gas turbine engine includes a rotor ring (84) defined along an axis of rotation and a plurality of core gas path seals (82) which extend from the rotor ring (84). Each of the plurality of core gas path seals (82) extends from the rotor ring (84) at an interface (86I), the interface (861) defined along a spoke (86).

Abstract translation: 用于燃气涡轮发动机的间隔件（62C）包括沿着旋转轴线限定的转子环（84）和从转子环（84）延伸的多个核心气体路径密封件（82）。 多个核心气体路径密封件（82）中的每一个在界面（86I）处从转子环（84）延伸，界面（861）沿着辐条（86）限定。

公开(公告)号：EP2071153B1

公开(公告)日：2015-09-02

申请号：EP08253894.3

申请日：2008-12-05

Applicant: United Technologies Corporation

Inventor： Norris, James W. ,  Merry, Brian D.

IPC: F02K3/072 ,  F02C3/107 ,  F02C3/067

CPC classification number: F02K3/072 ,  F02C3/067 ,  F02C3/107 ,  F05D2260/40 ,  F05D2260/4031 ,  Y02T50/671

公开(公告)号：EP2295763A3

公开(公告)日：2013-03-13

申请号：EP10251567.3

申请日：2010-09-09

Applicant: United Technologies Corporation

Inventor： Norris, James W. ,  Costa, Mark W. ,  Epstein, Alan ,  Berryann, Andrew P. ,  Roberge, Gary D. ,  Kupratis, Daniel B.

IPC: F02C3/107 ,  F02C3/14 ,  F02C7/32 ,  F02C7/36 ,  F02K3/105

CPC classification number: F02C3/107 ,  F02C3/145 ,  F02C7/32 ,  F02C7/36 ,  F02K3/105 ,  F05D2220/76 ,  Y02T50/671

Abstract: A gas turbine engine (10) comprises a fan drive gear system (12), a low spool (14) connected to the fan drive gear system, and a high spool (16) disposed aft of the low spool. The low spool comprises a rearward-flow low pressure compressor (26) disposed aft of the fan drive gear system, and a forward-flow low pressure turbine (30) disposed aft of the low pressure compressor. The high spool comprises a forward-flow high pressure turbine (32) disposed aft of the low pressure turbine, a combustor (18) disposed aft of the high pressure turbine, and a forward-flow high pressure compressor (36) disposed aft of the combustor.

Abstract translation: 燃气涡轮发动机（10）包括风扇驱动齿轮系统（12），连接到风扇驱动齿轮系统的低阀芯（14）和设置在低阀芯后面的高阀芯（16）。 低阀芯包括设置在风扇驱动齿轮系统后方的后向低压压缩机（26）和设置在低压压缩机后方的前进低压涡轮机（30）。 高阀芯包括设置在低压涡轮机后方的前流高压涡轮机（32），设置在高压涡轮机后方的燃烧室（18），以及设置在高压涡轮机后方的前进高压压缩机（36） 燃烧室。

公开(公告)号：EP2000648A2

公开(公告)日：2008-12-10

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

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).

Abstract translation: 燃气涡轮发动机（10）设置有与冷却空气流相关联的第一热交换器（58,64,72），以将冷却空气输送到涡轮部分（15）。 第二热交换器（52）与用于将燃料输送到燃烧部分（14）的燃料供应管线（50）相关联。 中间流体在第一热交换器（58,64,72）处冷却空气，并且在第二热交换器（52）处加热燃料。

公开(公告)号：EP1939408A2

公开(公告)日：2008-07-02

申请号：EP07254801.9

申请日：2007-12-12

Applicant: United Technologies Corporation

Inventor： Norris, James W. ,  Twelves, Wendell V., Jr.

IPC: F01D25/12 ,  F02C5/02 ,  F02C7/16 ,  F02C7/18

CPC classification number: F02C5/02 ,  F01D25/12 ,  F02C7/16 ,  F02C7/18 ,  F02C7/224 ,  F02K7/02 ,  F05D2220/40 ,  F05D2260/2322

Abstract: An engine cooling system includes a combustion chamber assembly (34) configured to generate detonation waves and a first vapor cooling assembly (40). The combustion chamber assembly (34) defines a flowpath between an inner liner (34A) and an outer liner (34B). The first vapor cooling assembly (40) includes a vaporization section (42A) located adjacent to the flowpath and a condenser section (44A)spaced from the flowpath, and is configured to transport thermal energy from the vaporization section (42A) to the condenser section (44A) through cyclical evaporation and condensation of a working medium sealed within the first vapor cooling assembly (40A).

Abstract translation: 发动机冷却系统包括构造成产生爆震波的燃烧室组件（34）和第一蒸气冷却组件（40）。 燃烧室组件（34）限定内衬（34A）和外衬套（34​​B）之间的流路。 第一蒸气冷却组件（40）包括位于流路附近的蒸发部分（42A）和与该流动路径间隔开的冷凝器部分（44A），并被构造成将热能从蒸发部分（42A）传送到冷凝器部分 （44A）通过密封在第一蒸气冷却组件（40A）内的工作介质的循环蒸发和冷凝。

公开(公告)号：EP1908922A2

公开(公告)日：2008-04-09

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).

公开(公告)号：EP2586969B1

公开(公告)日：2020-03-25

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

公开(公告)号：EP2586971B1

公开(公告)日：2019-06-12

申请号：EP12190276.1

申请日：2012-10-26

Applicant: United Technologies Corporation

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

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

公开(公告)号：EP2586971A3

公开(公告)日：2017-05-24

申请号：EP12190276.1

申请日：2012-10-26

Applicant: United Technologies Corporation

Inventor： Suciu, Gabriel L. ,  Muron, Stephen P. ,  Dye, Christopher M. ,  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 spacer (62C) for a gas turbine engine includes a rotor ring (84) defined along an axis of rotation. The rotor ring (84) defines a forward circumferential flange (92) which defines a first thickness and an aft circumferential flange (94) which defines a second thickness, the first thickness different than the second thickness. A plurality of core gas path seals (82) which extend from the rotor ring (84) opposite the flanges (92, 94).

Abstract translation: 用于燃气涡轮发动机的间隔件（62C）包括沿着旋转轴线限定的转子环（84）。 转子环（84）限定了限定第一厚度的向前周向凸缘（92）和限定第二厚度的向后周向凸缘（94），第一厚度不同于第二厚度。 多个芯部气体通道密封件（82）从与凸缘（92,94）相对的转子环（84）延伸。

公开(公告)号：EP2518293B1

公开(公告)日：2016-09-28

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