公开(公告)号：EP3052292A4

公开(公告)日：2017-06-21

申请号：EP14851299

申请日：2014-09-29

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MCCAFFREY MICHAEL G

IPC: B29C70/48 ,  B29K309/02

CPC classification number: B29C73/025 ,  B29C45/14 ,  B29C70/06 ,  B29C70/42 ,  B29C70/48 ,  B29K2105/0872 ,  B29K2105/253 ,  B29K2309/02 ,  B29K2883/00 ,  C04B35/64 ,  C04B41/83

公开(公告)号：EP3008289A4

公开(公告)日：2017-04-19

申请号：EP14810799

申请日：2014-06-06

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MCCAFFREY MICHAEL G ,  PROPHETER-HINCKLEY TRACY A ,  SURACE RAYMOND

IPC: F01D5/14 ,  F01D5/18 ,  F01D5/30 ,  F01D17/16 ,  F02C7/20 ,  F04D29/38

CPC classification number: F01D9/02 ,  F01D5/18 ,  F01D17/162 ,  F05D2230/60 ,  F05D2260/201 ,  F05D2300/20

Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a shell defining an interior, a spar extending into the interior and a first flange attached to the spar. The spar is configured to pivot to change a positioning of the shell.

Abstract translation: 根据本公开的示例性方面的部件包括限定内部的外壳，延伸到内部的翼梁和附接到翼梁的第一凸缘。 翼梁构造成枢转以改变壳体的定位。

公开(公告)号：EP2981676A4

公开(公告)日：2016-12-07

申请号：EP14778857

申请日：2014-04-01

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MCCAFFREY MICHAEL G

IPC: F01D5/14 ,  C04B37/00 ,  F01D5/28 ,  F01D5/30

CPC classification number: F01D5/30 ,  B28B1/30 ,  C04B37/005 ,  C04B2237/08 ,  C04B2237/086 ,  C04B2237/16 ,  C04B2237/365 ,  C04B2237/38 ,  C04B2237/385 ,  F01D5/02 ,  F01D5/147 ,  F01D5/282 ,  F01D5/284 ,  F01D5/3007 ,  F01D5/3084 ,  F01D5/3092 ,  F01D9/041 ,  F02C3/04 ,  F05D2220/32 ,  F05D2230/30 ,  F05D2230/312 ,  F05D2240/80 ,  F05D2300/6033 ,  Y02T50/672

公开(公告)号：EP3039250A4

公开(公告)日：2016-08-31

申请号：EP14839747

申请日：2014-08-29

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MCCAFFREY MICHAEL G

IPC: F01D11/08 ,  F01D25/24 ,  F16J15/20

CPC classification number: F01D11/08 ,  F01D25/24 ,  F01D25/246 ,  F01D25/28 ,  F05D2220/32 ,  F05D2230/30 ,  F05D2240/11 ,  F05D2260/30 ,  F05D2300/6033 ,  Y02T50/672

Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine including an engine case, a retention block attached to the engine case, and a blade outer air seal (BOAS). The BOAS includes a plurality of layers formed of a ceramic matrix composite (CMC) material. At least one of the plurality of layers provides a slot receiving a portion of the retention block.

公开(公告)号：EP2935799A4

公开(公告)日：2016-08-03

申请号：EP13866382

申请日：2013-12-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DUELM SHELTON O ,  MCCAFFREY MICHAEL G

IPC: F01D9/04 ,  F01D9/02 ,  F01D25/16 ,  F02C7/00

CPC classification number: F01D5/284 ,  F01D9/041 ,  F01D25/162 ,  F05D2230/23 ,  F05D2300/6033 ,  Y02T50/672 ,  Y02T50/673

Abstract: A vane assembly for a gas turbine engine is disclosed and includes a plurality of individual vane segments forming an annular ring. Each of the plurality of vane segments is formed of a ceramic matrix composite including at least one airfoil extending between an inner platform and an outer platform. An outer wrap is disposed about an outer periphery of the annular ring and over an interface between outer platforms of adjacent ones of the plurality of vane segments.

Abstract translation: 公开了一种用于燃气涡轮发动机的叶片组件，并且包括形成环形环的多个单独的叶片段。 多个叶片段中的每一个由包括在内平台和外平台之间延伸的至少一个翼型的陶瓷基复合材料形成。 围绕环形圈的外周并且在多个叶片段中的相邻叶片段的外平台之间的界面上设置外包裹物。

公开(公告)号：EP3044425A4

公开(公告)日：2017-10-18

申请号：EP14843324

申请日：2014-08-28

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MCCAFFREY MICHAEL G

IPC: F01D11/18 ,  F01D25/24

CPC classification number: F01D25/28 ,  F01D11/08 ,  F01D11/18 ,  F01D25/24 ,  F01D25/246 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/11 ,  F05D2250/11 ,  F05D2250/23 ,  F05D2260/30

公开(公告)号：EP3033509A4

公开(公告)日：2017-07-26

申请号：EP14836394

申请日：2014-08-11

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CHANG HOYT Y ,  MCCAFFREY MICHAEL G

IPC: F02C7/24 ,  F23M5/04 ,  F23R3/42

CPC classification number: F23R3/002 ,  F01D11/08 ,  F02C7/24 ,  F02K1/822 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/11 ,  F05D2240/35 ,  F05D2300/6033 ,  F23M5/04 ,  F23R3/007 ,  F23R3/60 ,  F23R2900/00017 ,  Y02T50/672

Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine including a plate, a frame attached to the plate, and a panel. The panel is supported by the frame.

Abstract translation: 本公开的一个示例性实施例涉及一种燃气涡轮发动机，该燃气涡轮发动机包括板，附接到该板的框架和面板。 面板由框架支撑。

公开(公告)号：EP3055509A4

公开(公告)日：2016-11-16

申请号：EP14852996

申请日：2014-09-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HOLOWCZAK JOHN E ,  MCCAFFREY MICHAEL G

IPC: F01D5/28 ,  F01D5/30 ,  F01D11/00

CPC classification number: F01D5/282 ,  C04B35/00 ,  C04B2237/00 ,  F01D5/147 ,  F01D5/284 ,  F01D5/30 ,  F01D5/3007 ,  F01D5/3084 ,  F01D5/3092 ,  F01D11/008 ,  F05D2220/32 ,  F05D2240/80 ,  F05D2300/13 ,  F05D2300/2261 ,  F05D2300/2283 ,  F05D2300/6033 ,  F05D2300/606 ,  F05D2300/607

公开(公告)号：EP2961938A4

公开(公告)日：2016-11-16

申请号：EP14798232

申请日：2014-02-12

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DUELM SHELTON O ,  MCCAFFREY MICHAEL G

IPC: F01D9/02 ,  F01D5/28 ,  F01D9/04 ,  F01D9/06 ,  F01D25/16 ,  F04D29/38

CPC classification number: F01D9/02 ,  F01D5/28 ,  F01D5/282 ,  F01D5/284 ,  F01D5/286 ,  F01D5/288 ,  F01D9/041 ,  F01D9/065 ,  F01D25/162 ,  F05D2220/32 ,  F05D2230/30 ,  F05D2230/60 ,  F05D2240/12 ,  F05D2300/2261 ,  F05D2300/6033 ,  F05D2300/614 ,  F05D2300/615 ,  Y02T50/672 ,  Y02T50/673

Abstract: An airfoil for a gas turbine engine includes first pressure and suction side layers forming a cavity and terminating in ends near a trailing edge. The first and second suction side layers are constructed from a composite material. A bridge is wrapped about the ends.

Abstract translation: 用于燃气涡轮发动机的翼型件包括形成空腔的第一压力和吸力侧层，并且在靠近后缘的端部终止。 第一和第二吸力侧层由复合材料构成。 一个桥被包裹在两端。

公开(公告)号：EP2938840A4

公开(公告)日：2016-05-25

申请号：EP13876286

申请日：2013-12-16

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MCCAFFREY MICHAEL G ,  ROUSE BRANDON T ,  ALMY THOMAS ,  GARCIA IGOR S ,  FARRIS JOHN R ,  BORJA MARK

IPC: F01D11/18 ,  F02C7/28 ,  F04D29/08

CPC classification number: F01D11/18 ,  F05D2240/11 ,  F05D2300/50212 ,  Y02T50/671

Abstract: A blade outer air seal system for a gas turbine engine includes a plurality of ring carriers made of a first material having a first coefficient of thermal expansion. A plurality of seal segments are carried, respectively, on the plurality of ring carriers. A ring member is carried in the plurality of ring carriers. The ring member is made of a second material that is different from the first material in composition. The second material has a second coefficient of thermal expansion such that the first coefficient of thermal expansion is 75-175% of the second coefficient of thermal expansion.