公开(公告)号：EP2000648B1

公开(公告)日：2014-01-29

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：EP1679425B1

公开(公告)日：2013-10-30

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

公开(公告)号：EP2586970A2

公开(公告)日：2013-05-01

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）延伸的多个芯气体通道密封件（82）。 多个核心气体通道密封件（82）中的每一个在接合部（86I）处从转子环（84）延伸，界面（861）沿辐条（86）限定。

公开(公告)号：EP1672172B1

公开(公告)日：2012-01-18

申请号：EP05257349.0

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 ,  F01D11/001 ,  F05D2260/4031

公开(公告)号：EP1936312A3

公开(公告)日：2012-01-04

申请号：EP07254800.1

申请日：2007-12-12

Applicant: United Technologies Corporation

Inventor： Norris, James W. ,  Noordeen, Craig A.

IPC: F28D15/02 ,  F02C7/224

CPC classification number: F28D15/02 ,  F02C7/14 ,  F02C7/185 ,  F02C7/224 ,  Y02T50/675

Abstract: A heat exchanger system (20) includes a first fluid layer (30A) defining a first flowpath for a gas, a second fluid layer (32) defining a second flowpath for a liquid, a first vapor cycle layer (28A) located between the first fluid layer (30A) and the second fluid layer (32) for enabling heat transfer between the first and second fluid layers (30A, 32), a first boundary wall (34B) defining a shared boundary between the first fluid layer (30A) and the first vapor cycle layer (28A), and a second boundary wall (34C) defining a shared boundary between the second fluid layer (32) and the first vapor cycle layer (28A). The first vapor cycle layer (28A) includes a working medium configured to transfer heat through an evaporation and condensation cycle, and the working medium of the first vapor cycle layer (28A) is sealed between the first and second boundary walls (34B, 34C).

公开(公告)号：EP1591623B1

公开(公告)日：2010-05-26

申请号：EP05252295.0

申请日：2005-04-13

Applicant: United Technologies Corporation

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

IPC: F01D5/06 ,  F01D11/00 ,  F01D5/02 ,  F16B21/16

CPC classification number: F01D5/066 ,  F01D5/025 ,  F01D11/001 ,  Y10T29/4932 ,  Y10T29/49321 ,  Y10T29/49323 ,  Y10T29/49947

公开(公告)号：EP1672171A3

公开(公告)日：2009-09-02

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

Abstract: A turbine engine has a first disk (34C) and a second disk (34D), each extending radially from an inner aperture to an outer periphery. A coupling transmits a torque and a longitudinal compressive force between the first and second disks (34C,34D). The coupling has first means (66C) for transmitting a majority of the torque and second means, radially outboard of the first means (62C), for transmitting a majority of the force.

公开(公告)号：EP1655541A3

公开(公告)日：2009-07-08

申请号：EP05256864.9

申请日：2005-11-07

Applicant: United Technologies Corporation

Inventor： Norris, James W. ,  Nordeen, Craig A. ,  Twelves Jr, Wendell V.

IPC: F23R7/00 ,  F23C15/00 ,  F23R3/00 ,  F23R3/56

CPC classification number: F23C15/00 ,  F23R3/002 ,  F23R3/08 ,  F23R3/56 ,  F23R7/00

Abstract: A pulsed combustion apparatus includes a conduit (40) having an outer wall (60) and an inner wall (62). The inner wall (62) has a number of apertures (164, 174, 176). An interior space (44) is separated from the outer wall (60) by the inner wall (62). An induction system is positioned to cyclicly admit charges to the interior space. An ignition system is positioned to ignite the charges. Flow directing surfaces are positioned to at least cyclicly direct cooling air through the apertures.

公开(公告)号：EP1679425A2

公开(公告)日：2006-07-12

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.

Abstract translation: 燃气涡轮发动机转子堆（32）包括一个或多个纵向向外凹的间隔件（62）。 间隔件的外侧表面（144）可以靠近翼片翼型件（36）的内侧顶端（48）。 间隔件（62）可以提供随着转速而增加的纵向压缩力。

公开(公告)号：EP1672172A1

公开(公告)日：2006-06-21

申请号：EP05257349.0

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 ,  F01D11/001 ,  F05D2260/4031

Abstract: A turbine engine has a first disk (34A) and a second disk (34B), each extending radially from an inner aperture to an outer periphery. A coupling transmits a torque and a longitudinal compressive force between the first and second disks (34A,34B). The coupling has first means (70A) for transmitting a majority of the torque and a majority of the force and second means, radially outboard of the first means (62A), for vibration stabilizing.

Abstract translation: 涡轮发动机具有第一盘（34A）和第二盘（34B），每个盘从内孔径向延伸到外周。 联接器在第一和第二盘（34A，34B）之间传递扭矩和纵向压缩力。 联接器具有用于传递大部分扭矩的第一装置（70A）以及第一装置（62A）的径向外侧的大部分力和第二装置，用于振动稳定。