公开(公告)号：WO2014074195A2

公开(公告)日：2014-05-15

申请号：PCT/US2013/055490

申请日：2013-08-18

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： HARRIS, Meggan ,  FARAH, Jorge, I. ,  TREAT, Christopher ,  DALE, Timothy

IPC: F01D25/24 ,  F02C7/00

CPC classification number: F01D25/28 ,  F01D25/162 ,  F16B9/023 ,  Y10T29/49323

Abstract: A turbine engine includes multiple tierod supports. Each of the tierod supports is connected to an inner frame case of the turbine engine via multiple fasteners and at least one self anti-rotating bushing component.

Abstract translation: 涡轮发动机包括多个tierod支架。 每个支架支架通过多个紧固件和至少一个自防旋转衬套部件连接到涡轮发动机的内框架壳体。

公开(公告)号：WO2014021973A2

公开(公告)日：2014-02-06

申请号：PCT/US2013/040232

申请日：2013-05-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： TREAT, Christopher ,  STENMAN, Christina A. ,  DUELM, Shelton O. ,  SIMPSON, Alex J.

IPC: F02K1/12 ,  F02K1/06 ,  F02C7/00

CPC classification number: F02K1/1223 ,  F02K1/12 ,  F05D2300/6033 ,  F23R3/16

Abstract: A liner assembly includes a plurality of flaps arranged about a central axis and operable to move relative to the central axis. Each of the plurality of flaps defines a forward end and an aft end, lateral sides, and an inner surface and an outer surface relative to the central axis. Each of the plurality of flaps has a thickness between the inner surface and the outer surface, and thickness varies in a lateral direction between the lateral sides.

Abstract translation: 衬套组件包括围绕中心轴布置并可操作以相对于中心轴线移动的多个翼片。 多个翼片中的每一个限定了前端和后端，侧面以及相对于中心轴线的内表面和外表面。 多个翼片中的每一个在内表面和外表面之间具有厚度，并且厚度在横向方向之间在横向方向上变化。

公开(公告)号：EP3263841A2

公开(公告)日：2018-01-03

申请号：EP17176961.5

申请日：2017-06-20

Applicant: United Technologies Corporation

Inventor： TREAT, Christopher ,  HUANG, Jeffrey H. ,  KARANIAN, Caroline

IPC: F01D9/04 ,  F01D25/24

CPC classification number: F01D25/24 ,  F01D9/041 ,  F01D25/28 ,  F05D2220/32 ,  F05D2230/10 ,  F05D2230/21 ,  F05D2230/237 ,  F05D2230/30

Abstract: The invention is related to a stiffness boss (102) for a turbine case (70) of a gas turbine engine (2) wherein the stiffness boss (102) includes a head portion (104) disposed on an outer case surface (120) of the turbine case (70), the head portion (104) configured to provide rigidity in response to a transverse load (304) being applied to the turbine case (70) in a transverse direction. The stiffness boss (102) also includes a leg portion (106) disposed on the outer case surface (120) of the turbine case (70) and connected to the head portion (104), the leg portion (106) configured to provide rigidity in response to an axial load (302) being applied to the turbine case (70) in an axial direction, such that deformation of the turbine case (70) is resisted.

公开(公告)号：EP3263841A3

公开(公告)日：2018-04-25

申请号：EP17176961.5

申请日：2017-06-20

Applicant: United Technologies Corporation

Inventor： TREAT, Christopher ,  HUANG, Jeffrey H. ,  KARANIAN, Caroline

IPC: F01D9/04 ,  F01D25/24

CPC classification number: F01D25/24 ,  F01D9/041 ,  F01D25/28 ,  F05D2220/32 ,  F05D2230/10 ,  F05D2230/21 ,  F05D2230/237 ,  F05D2230/30

Abstract: The invention is related to a stiffness boss (102) for a turbine case (70) of a gas turbine engine (2) wherein the stiffness boss (102) includes a head portion (104) disposed on an outer case surface (120) of the turbine case (70), the head portion (104) configured to provide rigidity in response to a transverse load (304) being applied to the turbine case (70) in a transverse direction. The stiffness boss (102) also includes a leg portion (106) disposed on the outer case surface (120) of the turbine case (70) and connected to the head portion (104), the leg portion (106) configured to provide rigidity in response to an axial load (302) being applied to the turbine case (70) in an axial direction, such that deformation of the turbine case (70) is resisted.

Abstract translation: 本发明涉及一种用于燃气涡轮发动机（2）的涡轮机壳体（70）的刚性凸台（102），其中该刚性凸台（102）包括设置在外壳表面（120）上的头部（104） 所述涡轮机壳体（70），所述头部（104）构造成响应于沿横向方向施加到所述涡轮机壳体（70）的横向负载（304）而提供刚性。 刚性凸台（102）还包括设置在涡轮机壳体（70）的外壳体表面（120）上并连接到头部（104）的腿部（106），腿部（106）构造成提供刚性 响应于沿轴向方向施加到涡轮机壳体（70）的轴向负载（302），从而抵抗涡轮机壳体（70）的变形。

公开(公告)号：EP3040523B1

公开(公告)日：2018-02-07

申请号：EP15200748.0

申请日：2015-12-17

Applicant: United Technologies Corporation

Inventor： FARAH, Jorge I. ,  TREAT, Christopher ,  CHAN, Jenny

IPC: F01D25/16 ,  F01D9/06 ,  F01D25/24 ,  B22D25/02 ,  F01D25/28

CPC classification number: F01D25/243 ,  B22D25/02 ,  F01D9/065 ,  F01D25/162 ,  F01D25/24 ,  F01D25/28 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2230/25 ,  F05D2260/941 ,  Y02T50/671

Abstract: An inner case (59) for a gas turbine engine includes a case body (100; 200; 300) defining a centerline axis. The case body includes a turbine seal support (102), and an I-rod support (106) downstream of the turbine seal support. A mid-turbine frame for a gas turbine engine includes an inner case (59) having an integral case body (100; 200; 300). A method for manufacturing an inner case (59) for a turbomachine with an integral high pressure turbine seal support (102) includes fabricating a case body (100; 200; 300).

公开(公告)号：EP2888454A2

公开(公告)日：2015-07-01

申请号：EP13853570.3

申请日：2013-08-18

Applicant: United Technologies Corporation

Inventor： HARRIS, Meggan ,  FARAH, Jorge, I. ,  TREAT, Christopher ,  DALE, Timothy

IPC: F01D25/24 ,  F02C7/00

CPC classification number: F01D25/28 ,  F01D25/162 ,  F16B9/023 ,  Y10T29/49323

Abstract: A turbine engine includes multiple tierod supports. Each of the tierod supports is connected to an inner frame case of the turbine engine via multiple fasteners and at least one self anti-rotating bushing component.

公开(公告)号：EP3081761B1

公开(公告)日：2019-06-12

申请号：EP16164954.6

申请日：2016-04-12

Applicant: United Technologies Corporation

Inventor： BROULIDAKIS, Alexander ,  COLLIER, Michael D. ,  DEVANEY, Patrick M. ,  NADEAU, Patrick M. ,  SEDOR, Joseph ,  TREAT, Christopher

IPC: F01D9/06 ,  F01D25/16 ,  F01D25/24 ,  F01D25/26 ,  F01D25/28

公开(公告)号：EP3064716B1

公开(公告)日：2019-05-01

申请号：EP16158692.0

申请日：2016-03-04

Applicant: United Technologies Corporation

Inventor： WINN, Joshua David ,  CHEROLIS, Anthony P. ,  PORTER, Steven D. ,  TREAT, Christopher ,  ZACCHERA, Kevin

IPC: F01D9/06 ,  F01D25/28

公开(公告)号：EP3211277A1

公开(公告)日：2017-08-30

申请号：EP17157485.8

申请日：2017-02-22

Applicant: United Technologies Corporation

Inventor： TREAT, Christopher ,  KANTANY, Nicholas W. ,  BURDICK, Andrew D. ,  PEZZETTI, Michael C.

IPC: F16J9/24 ,  F01D11/00 ,  F02C7/28 ,  F16J15/3272

Abstract: A method of limiting circumferential rotation of a split-ring seal (76, 78, 80, 82) for use in a gas turbine engine (20) includes inserting a retention block (90; 130) through a slot (116; 154) in a flange (102; 147) of a support structure (68; 70) and into a groove (108; 148) configured to hold a split-ring seal (76, 78, 80, 82), and engaging an end (110) of a split-ring seal (76, 78, 80, 82) in the groove (108; 148) with a surface of the retention block (90; 148).

Abstract translation: 一种限制在燃气涡轮发动机（20）中使用的开口环密封件（76,78,80,82）的周向旋转的方法包括将保持块（90; 130）插入到槽（116; 154）中的槽 （68; 70）的凸缘（102; 147）并进入构造成保持开口环密封件（76,78,80,82）并接合端部（110）的凹槽（108; 148） 在所述凹槽（108; 148）中与所述保持块（90; 148）的表面接合的开口环密封件（76,78,80,82）。

公开(公告)号：EP3054102A1

公开(公告)日：2016-08-10

申请号：EP16154799.7

申请日：2016-02-09

Applicant: United Technologies Corporation

Inventor： BROULIDAKIS, Alexander ,  CHEROLIS, Anthony P. ,  LEMOINE, Jonathan ,  PAREKH, Kalpendu J. ,  TRINKS, Steven W. ,  TREAT, Christopher ,  ZACCHERA, Kevin ,  MATEO, Alberto

IPC: F01D9/06 ,  F01D25/16 ,  F16B39/04

CPC classification number: F01D25/28 ,  F01D9/065 ,  F01D25/162 ,  F01D25/26 ,  F02C7/12 ,  F05D2220/32 ,  F05D2220/3213 ,  F05D2230/20 ,  F05D2230/64 ,  F05D2260/20 ,  F05D2260/30 ,  F05D2260/31 ,  Y02T50/671 ,  Y02T50/676

Abstract: A tie rod assembly for a mid-turbine frame of a gas turbine engine includes at least one tie rod (90A) for connecting an outer frame case (62) to an inner frame case (64). At least one tie rod includes a cooling airflow inlet passage (118) that branches into a first branch (120) and a second branch (124). A plug (128) is located in the first branch to block cooling airflow through a portion of the first branch. A method of forming a tie rod comprises forming a first portion of the inlet passage with a first diameter (D1) and a second portion with a second diameter (D2).

Abstract translation: 用于燃气涡轮发动机的中涡轮机架的拉杆组件包括用于将外框壳体（62）连接到内框架壳体（64）的至少一个拉杆（90A）。 至少一个拉杆包括分支到第一分支（120）和第二分支（124）中的冷却气流入口通道（118）。 插头（128）位于第一分支中以阻止通过第一分支的一部分的冷却气流。 形成拉杆的方法包括：形成具有第一直径（D1）的入口通道的第一部分和具有第二直径（D2）的第二部分。