公开(公告)号：EP2985421A1

公开(公告)日：2016-02-17

申请号：EP15180516.5

申请日：2015-08-11

Applicant: United Technologies Corporation

Inventor： SUCIU, Gabriel L. ,  MERRY, Brian D. ,  HILL, James D.

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

CPC classification number: F01D5/087 ,  F01D5/06 ,  F01D5/081 ,  F01D5/12 ,  F01D5/34 ,  F01D11/006 ,  F01D25/005 ,  F01D25/12 ,  F04D29/321 ,  F04D29/58 ,  F05D2220/32 ,  F05D2220/3219 ,  F05D2240/30 ,  F05D2260/20 ,  F05D2300/175 ,  Y02T50/672 ,  Y02T50/676

Abstract: A gas turbine engine (20;100) may comprise a first rotor (206) with a primary flowpath (201) along an outer diameter of the first rotor (206). A secondary flowpath (202) may be radially inward from the primary flowpath (201). The secondary flowpath (202) may pass through an opening (208) through the first rotor (206). A blade (252) may be disposed on a distal end of the first rotor (206). The blade (252) may extend into the primary flowpath (201). A bleed tube (204) may be in a wall of the primary flowpath (201) and forward of the blade (252). The bleed tube (204) may extend radially inward from the primary flowpath (201). The bleed tube (204) may fluidly connect to the opening (208) through the first rotor (206). A plenum (210) may be aft of the blade (252) and radially inward from the primary flowpath (201). The plenum (210) may be fluidly connected to the opening (208) through the first rotor (206). A second rotor (216) may be aft of the plenum (210).

Abstract translation: 燃气涡轮发动机（20; 100）可以包括具有沿着第一转子（206）的外径的主流路（201）的第一转子（206）。 二次流路202可以从主流路201径向向内。 次级流路202可穿过第一转子206的开口208。 刀片（252）可以设置在第一转子（206）的远端上。 刀片（252）可以延伸到主流路（201）中。 排放管（204）可以在主流路（201）的壁中并且在叶片（252）的前方。 排放管（204）可以从主流路（201）径向向内延伸。 排放管（204）可以通过第一转子（206）流体地连接到开口（208）。 气室（210）可以是叶片（252）的后部并且从主流路（201）径向向内。 气室210可以通过第一转子206流体连接到开口208。 第二转子（216）可以是集气室（210）的后部。

公开(公告)号：EP2952681A1

公开(公告)日：2015-12-09

申请号：EP15170840.1

申请日：2015-06-05

Applicant: United Technologies Corporation

Inventor： SUCIU, Gabriel L. ,  MERRY, Brian D. ,  HILL, James D.

IPC: F01D5/08 ,  F01D9/06 ,  F01D25/12 ,  F02C6/08 ,  F02C7/18

Abstract: A turbine injection system (148) for a gas turbine engine (20) includes a first end operable to receive air from a heat exchanger (140), a second end operable to distribute mixed cooling air to a turbine stage, an opening (136) downstream of said first end and a mixing plenum (152) downstream of said first end and said opening (136). The opening (136) provides a direct fluid pathway into said turbine injection system (148) from the combustor (56) of the engine (20).

Abstract translation: 一种用于燃气涡轮发动机（20）的涡轮喷射系统（148）包括：第一端部，其可操作以从热交换器（140）接收空气;第二端部，其可操作以将混合的冷却空气分配到涡轮级;开口（136） 在所述第一端的下游和在所述第一端和所述开口（136）下游的混合室（152）。 开口（136）提供从发动机（20）的燃烧器（56）进入所述涡轮喷射系统（148）的直接流体路径。

公开(公告)号：EP2820280A2

公开(公告)日：2015-01-07

申请号：EP13784640.8

申请日：2013-02-15

Applicant: United Technologies Corporation

Inventor： SUCIU, Gabriel L. ,  MERRY, Brian D.

IPC: F02K3/072 ,  F02K3/04 ,  F02C7/04

CPC classification number: F02C7/36 ,  F01D1/26 ,  F01D1/28 ,  F01D15/12 ,  F02C3/067 ,  F02C3/107 ,  F02C7/06 ,  F02K3/068 ,  F02K3/072 ,  F05D2260/40311 ,  F05D2260/53 ,  Y02T50/671

Abstract: A gas turbine engine includes a shaft defining an axis of rotation. An inner rotor directly drives the shaft and includes an inner set of blades. An outer rotor has an outer set of blades interspersed with the inner set of blades. The outer rotor is configured to rotate in an opposite direction about the axis of rotation from the inner rotor. A gear system couples the outer rotor to the shaft and is configured to rotate the inner set of blades at a lower speed than the outer set of blades.

公开(公告)号：EP2820265A2

公开(公告)日：2015-01-07

申请号：EP13790583.2

申请日：2013-02-25

Applicant: United Technologies Corporation

Inventor： SUCIU, Gabriel L. ,  MERRY, Brian D. ,  MCCUNE, Michael E. ,  MAGGE, Shankar S.

IPC: F02C3/067 ,  F02K3/072

CPC classification number: F02C3/107 ,  F01D1/26 ,  F02C3/067 ,  F02C7/36 ,  F02K3/072 ,  F05D2250/44 ,  F05D2260/40311 ,  Y02T50/671

Abstract: A gas turbine engine includes a shaft defining an axis of rotation. An outer turbine rotor directly drives the shaft and includes an outer set of blades. An inner turbine rotor has an inner set of blades interspersed with the outer set of blades. The inner turbine rotor is configured to rotate in an opposite direction about the axis of rotation from the outer turbine rotor. A splitter gear system couples the inner turbine rotor to the shaft and is configured to rotate the inner set of blades at a faster speed than the outer set of blades.

公开(公告)号：EP2809914A1

公开(公告)日：2014-12-10

申请号：EP13770230.4

申请日：2013-01-07

Applicant: United Technologies Corporation

Inventor： MERRY, Brian D. ,  SUCIU, Gabriel L.

IPC: F02C7/06 ,  F02C7/36 ,  F02K3/02

CPC classification number: F01D25/16 ,  F01D25/162 ,  F02C7/06 ,  F02C7/36 ,  F02K3/04 ,  F05D2250/19 ,  F05D2260/40311

Abstract: A gas turbine engine includes a core housing providing a core flowpath. A shaft supports a compressor section arranged within the core flowpath. First and second bearings support the shaft relative to the core housing and are arranged radially inward of and axially overlapping with the compressor section.

公开(公告)号：EP2952698B1

公开(公告)日：2020-12-09

申请号：EP15170890.6

申请日：2015-06-05

Applicant: United Technologies Corporation

Inventor： SUCIU, Gabriel L. ,  MERRY, Brian D. ,  HILL, James D. ,  ZELESKY, Mark F.

IPC: F01D25/12 ,  F02C3/13 ,  F02C7/18 ,  F02C9/18

公开(公告)号：EP3708792A1

公开(公告)日：2020-09-16

申请号：EP20162850.0

申请日：2013-04-23

Applicant: United Technologies Corporation

Inventor： SUCIU, Gabriel L. ,  SCHWARZ, Frederick M. ,  KUPRATIS, Daniel Bernard ,  MERRY, Brian D. ,  ACKERMANN, William K.

IPC: F01D25/16 ,  F02C7/06

Abstract: A gas turbine engine (20) includes a very high speed low pressure turbine (46) such that a quantity defined by the exit area (401) of the low pressure turbine (46) multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine (54) is at a ratio between about 0.5 and about 1.5. The high pressure turbine (54) is supported by a bearing (142) positioned at a point where the first shaft (32) connects to a hub (500) carrying turbine rotors associated with the second turbine section (54).

公开(公告)号：EP2932073B1

公开(公告)日：2020-08-05

申请号：EP13863329.2

申请日：2013-12-10

Applicant: United Technologies Corporation

Inventor： SNAPE, Nathan ,  MERRY, Brian D. ,  PENDA, Allan R. ,  SUCIU, Gabriel L.

IPC: F02C6/08 ,  F02C9/18 ,  F02C7/141 ,  F02C6/12

公开(公告)号：EP2952681B1

公开(公告)日：2020-05-06

申请号：EP15170840.1

申请日：2015-06-05

Applicant: United Technologies Corporation

Inventor： SUCIU, Gabriel L. ,  MERRY, Brian D. ,  HILL, James D.

IPC: F01D5/08 ,  F01D9/06 ,  F01D25/12 ,  F02C6/08 ,  F02C7/18

公开(公告)号：EP3594452A1

公开(公告)日：2020-01-15

申请号：EP19188877.5

申请日：2015-06-08

Applicant: United Technologies Corporation

Inventor： PACK, David R. ,  PARTYKA, Julian ,  HILL, James D. ,  SUCIU, Gabriel L. ,  DOLANSKY, Gregory M. ,  MERRY, Brian D.

IPC: F01D11/00

Abstract: A seal segment (102) for a gas turbine engine (20) includes a first axial span (134) that extends between a first radial span (130) and a second radial span (132). A second axial span (136) extends between the first radial span (130) and the second radial span (132), the first radial span (130), the second radial span (132), the first axial span (134) and the second axial span (136) form a torque box. A plurality of seal segments (102) may be located between first and second rotor disks (68, 70).