公开(公告)号：EP2075411B1

公开(公告)日：2015-06-03

申请号：EP08254049.3

申请日：2008-12-18

Applicant: United Technologies Corporation

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

IPC: F01D5/34 ,  F04D29/32 ,  F01D11/00 ,  F01D5/08 ,  B23P15/00

CPC classification number: F01D5/34 ,  F01D5/084 ,  F01D11/006 ,  F04D29/322 ,  F04D29/329 ,  F05D2230/10 ,  F05D2230/12 ,  F05D2260/941

公开(公告)号：EP1672171B1

公开(公告)日：2014-06-25

申请号：EP05257347.4

申请日：2005-11-29

Applicant: United Technologies Corporation

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

IPC: F01D5/06 ,  F01D11/00

CPC classification number: F01D5/066 ,  F05D2260/4031

公开(公告)号：EP1939408A3

公开(公告)日：2013-03-06

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 ,  F02K7/02 ,  F02C7/224

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).

公开(公告)号：EP2485106A2

公开(公告)日：2012-08-08

申请号：EP12161339.2

申请日：2008-02-19

Applicant: United Technologies Corporation

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

IPC: G05B19/418 ,  G05B19/4099 ,  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).

Abstract translation: 一个集成的添加剂制造单元（IAMC）（101）确实结合了常规的制造技术与添加剂的制造工艺是游离缺失盘。 个别IAMCs（101）可以被配置和复杂的组件，或其它工业应用中的特定部分的家庭优化。 该IAMCs收纳功能并降低硬件成本和时间，让当地的剪裁中成分复杂的合金材料性能的优化。 在一个实施例中对IMAC（101）包围中央制造单元（103）包括具有的接入端口有多个（105）。 机械和电气接口端口与每个访问端口（105）以耦合电源，通信和机械公用事业到外部模块（107 ... 115）相关联。

公开(公告)号：EP2295763A2

公开(公告)日：2011-03-16

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

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.

公开(公告)号：EP1591622B1

公开(公告)日：2010-06-02

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

公开(公告)号：EP1679425A3

公开(公告)日：2009-10-14

申请号：EP05256887.0

申请日：2005-11-07

Applicant: United Technologies Corporation

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

IPC: F01D5/06

CPC classification number: F01D11/001 ,  F01D5/066 ,  F05D2250/70 ,  F05D2250/712 ,  F05D2260/30

Abstract: A gas turbine engine rotor stack (32) includes one or more longitudinally outwardly concave spacers (62). Outboard surfaces (144) of the spacers may be in close facing proximity to inboard tips (48) of vane airfoils (36). The spacers (62) may provide a longitudinal compression force that increases with rotational speed.

公开(公告)号：EP2075411A1

公开(公告)日：2009-07-01

申请号：EP08254049.3

申请日：2008-12-18

Applicant: United Technologies Corporation

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

IPC: F01D5/34 ,  F04D29/32 ,  F01D11/00 ,  F01D5/08 ,  B23P15/00

CPC classification number: F01D5/34 ,  F01D5/084 ,  F01D11/006 ,  F04D29/322 ,  F04D29/329 ,  F05D2230/10 ,  F05D2230/12 ,  F05D2260/941

Abstract: An integrally bladed rotor (80) for a gas turbine engine includes at least one discontinuity (88,90,92) formed in an outer face of an outer rim (82). The discontinuity (88,90,92) reduces hoop stress in the outer rim (82).

Abstract translation: 用于燃气涡轮发动机的整体叶片转子（80）包括形成在外轮缘（82）的外表面中的至少一个不连续部（88,90,92）。 不连续性（88,90,92）减小外缘（82）中的环向应力。

公开(公告)号：EP1956214A2

公开(公告)日：2008-08-13

申请号：EP08250177.6

申请日：2008-01-14

Applicant: United Technologies Corporation

Inventor： Norris, James W. ,  Nordeen, Craig A. ,  Hill, James D.

IPC: F02C7/16 ,  F02K3/06

CPC classification number: F02C6/08 ,  F01D9/065 ,  F01D25/12 ,  F02C7/16 ,  F02K3/06 ,  F05D2240/55 ,  F05D2260/208 ,  F05D2260/221 ,  F05D2260/232

Abstract: A cooling system for a gas turbine engine includes a non-rotating component (32) extending into an engine flowpath, a vapor cooling assembly (26) configured to transport thermal energy from a vaporization section (34) to a condenser section (36) through cyclical evaporation and condensation of a working medium sealed within the vapor cooling assembly (26), wherein the vaporization section (34) is located at least partially within the non-rotating component (32), and wherein the condenser section (36) is located outside the non-rotating component (32) and away from the engine flowpath.

Abstract translation: 一种用于燃气涡轮发动机的冷却系统包括延伸到发动机流路中的非旋转部件（32），蒸气冷却组件（26），其被配置为将热能从汽化部分（34）运送到冷凝器部分（36）通过 密封在蒸汽冷却组件（26）内的工作介质的循环蒸发和冷凝，其中蒸发部分（34）至少部分地位于非旋转部件（32）内，并且其中冷凝器部分（36）位于 在非旋转部件（32）外部并且远离发动机流动路径。

公开(公告)号：EP1961514B1

公开(公告)日：2019-04-03

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