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1. 发明公开

EP3620615A1 CMC BOAS AXIAL RETAINING CLIP 有权转让
公开(公告)号：EP3620615A1
公开(公告)日：2020-03-11
申请号：EP19195648.1
申请日：2019-09-05
申请人： United Technologies Corporation
发明人： BLANEY, Ken F. , CLARK, Thomas E.
IPC分类号： F01D11/08 , F01D25/24
摘要： A blade outer air seal assembly (105) contains a support structure (112). A blade outer air seal (106) extends circumferentially about an axis (A) and is mounted in the support structure (112). The support structure (112) has a first support member (118) that engages a first axial side (A1) of the blade outer air seal (106). A second support member (120) engages a second axial side (A2) of the blade outer air seal (106). A retaining clip (152, 252) secures the blade outer air seal (106) to the support structure (112). The retaining clip (152, 252) has a first leg (160, 260) and a second leg (158, 258) that extends in a generally radial direction. The first leg (160, 260) abuts the first axial side (A1) and the second leg (158, 258) abuts the first support member (118).

2. 发明授权

EP3030754B1 BOAS WITH RADIAL LOAD FEATURE 有权转让
公开(公告)号：EP3030754B1
公开(公告)日：2018-11-14
申请号：EP14834381.7
申请日：2014-08-05
申请人： United Technologies Corporation
发明人： BLANEY, Ken F. , PELLETIER, Brian R. , KNAPP, James N.
IPC分类号： F01D11/08 , F01D25/28 , F02C7/28 , F04D29/08 , F01D21/04 , F01D11/24 , F01D25/24 , F04D29/16
CPC分类号： F01D11/08 , F01D11/24 , F01D21/045 , F01D25/246 , F01D25/28 , F04D29/164 , F05D2220/32 , F05D2240/11
摘要： This disclosure relates to a gas turbine engine including a blade outer air seal (BOAS) having at least one attachment hook adjacent one of a leading edge and a trailing edge thereof. The BOAS further includes at least one radial standoff axially aligned with the at least one attachment hook.

3. 发明公开

EP3156613A3 BLADE OUTER AIR SEAL 有权转让
标题翻译：刀片外部空气密封
公开(公告)号：EP3156613A3
公开(公告)日：2017-06-14
申请号：EP16192466.7
申请日：2016-10-05
申请人： United Technologies Corporation
发明人： ROMANOV, Dmitriy A. , LUTJEN, Paul M. , RYAN, Kevin J. , BLANEY, Ken F.
IPC分类号： F01D11/08 , F01D25/12
CPC分类号： F01D11/08 , F01D11/02 , F01D25/12 , F05D2220/32 , F05D2240/11 , F05D2240/55 , F05D2250/314 , F05D2260/20 , F16J15/44 , Y02T50/675
摘要： According to various embodiments, disclosed is a blade outer air seal assembly (50) for a turbine engine (20) comprising a main body portion (54) that extends generally axially, with respect to a central axis (A) of the turbine engine (20), from a leading edge portion (56) of the main body portion (54) to a trailing edge portion (58) of the main body portion (54), wherein the leading edge portion (56) includes a leading edge wall (56a) having an undercut profile (56b) along at least a portion of the leading edge wall (56a), wherein the main body portion (54) comprises cooling passages (86) comprising a leading edge cooling passage (86a) adjacent to the leading edge wall (56a), having a leading edge periphery (87) on a side of the leading edge cooling passage (86a) adjacent to the leading edge wall (56a), which generally conforms to the undercut profile (56b) of the leading edge wall (56a).
摘要翻译：根据各种实施例，公开了一种用于涡轮发动机（20）的叶片外部气密组件（50），其包括主体部分（54），该主体部分相对于涡轮发动机的中心轴线（A）（56）从主体部分（54）的前缘部分（56）延伸到主体部分（54）的后缘部分（58），其中前缘部分（56）包括前缘壁 56a）沿着前缘壁（56a）的至少一部分具有底切轮廓（56b），其中主体部分（54）包括冷却通道（86），冷却通道（86）包括与前导壁（56a）相邻的前缘冷却通道在前缘冷却通道（86a）的与前缘壁（56a）相邻的一侧上具有前缘周边（87）的前缘壁（56a），其通常与前缘的底切轮廓（56b）墙（56a）。

4. 发明公开

EP2959134A1 AERATING FUEL INJECTOR SYSTEM FOR A GAS TURBINE ENGINE 审中-公开
标题翻译： VENT燃料喷射系统的燃气涡轮发动机
公开(公告)号：EP2959134A1
公开(公告)日：2015-12-30
申请号：EP14754245.0
申请日：2014-02-19
申请人： United Technologies Corporation
发明人： BLANEY, Ken F. , KRAMER, Stephen K.
IPC分类号： F02C7/232 , F02C7/22
CPC分类号： F23R3/286 , F02C7/22 , F05D2260/608 , F23D11/10 , F23R3/28
摘要： An aeration system for a fuel injector system of a gas turbine engine includes a air tank in communication with a fuel injector and method of operation thereof.

5. 发明公开

EP3620613A1 INTEGRATED SEAL AND WEAR LINER 有权转让
公开(公告)号：EP3620613A1
公开(公告)日：2020-03-11
申请号：EP19195726.5
申请日：2019-09-05
申请人： United Technologies Corporation
发明人： BLANEY, Ken F. , LUTJEN, Paul M. , CLARK, Thomas E.
IPC分类号： F01D11/00 , F01D25/24
摘要： A blade outer air seal assembly (106) includes a support structure (112). A blade outer air seal (105) extends circumferentially about an axis (A) and is mounted in the support structure (112). The blade outer air seal (105) has a lip (132) at an axial end engaged with the support structure. A seal structure (152) has a seal portion (154) and a wear liner portion (156) joined by a radially extending portion (158). The seal portion (154) is radially outward of the lip (132) and the wear liner portion (156) is radially inward of the lip (132).

6. 发明公开

EP3620612A1 CMC BOAS INTERSEGMENT SEAL 有权转让
公开(公告)号：EP3620612A1
公开(公告)日：2020-03-11
申请号：EP19195722.4
申请日：2019-09-05
申请人： United Technologies Corporation
发明人： BLANEY, Ken F. , CLARK, Thomas E.
IPC分类号： F01D11/00
摘要： A blade outer air seal assembly (105;205) includes a support structure. A blade outer air seal (106) extends circumferentially about an axis (A) and is mounted in the support structure (112). A flow guide (138) has a plurality of flow guide segments arranged between the blade outer air seal (106) and the support structure (112). An intersegment seal (152) is at a circumferential end (C1) of at least one of the flow guide segments.

7. 发明公开

EP3599347A1 ATTACHMENT BLOCK FOR BLADE OUTER AIR SEAL PROVIDING IMPINGEMENT COOLING 有权转让
公开(公告)号：EP3599347A1
公开(公告)日：2020-01-29
申请号：EP19187958.4
申请日：2019-07-23
申请人： United Technologies Corporation
发明人： BLANEY, Ken F. , CLARK, Thomas E.
IPC分类号： F01D5/22 , F01D9/04 , F01D11/00 , F01D11/08 , F01D25/24
摘要： A gas turbine engine (20) includes a compressor section (24) and a turbine section (28). The turbine section (28) includes at least one turbine rotor having a radially extending turbine blade (102). The turbine section (28) is rotatable about an axis of rotation (A). A blade outer air seal (104) is positioned radially outwardly of a radially outer tip of the at least one turbine blade (102). The blade outer air seal (104) has axially spaced forward and aft portions (106, 108) and a central web (99) between the axially spaced portions (106, 108). An attachment block (110, 136) is supported on structure within the engine (20). The attachment block (110, 136) mounts the blade outer air seal (104). A passage (118) extends into a central chamber (131) within the attachment block (110, 136), and communicates with cooling holes (120) through a radially inner face of the attachment block (110, 136) to direct cooling air at the central web (99) of the blade outer air seal (104).

8. 发明公开

EP3192976A1 GAS TURBINE ENGINE COMPONENT, CORRESPONDING BLADE OUTER AIR SEAL SEGMENT AND GAS TURBINE ENGINE 有权转让
标题翻译：燃气轮机发动机部件，相应的叶片外部空气密封部分和燃气轮机发动机
公开(公告)号：EP3192976A1
公开(公告)日：2017-07-19
申请号：EP16198829.0
申请日：2016-11-15
申请人： United Technologies Corporation
发明人： SWIFT, Anthony B. , LUTJEN, Paul M. , TATMAN, Neil L. , MONGILLO, Jr., Dominic J. , DEVORE, Matthew A. , BLANEY, Ken F.
IPC分类号： F01D11/08
CPC分类号： F01D25/12 , F01D11/08 , F01D25/246 , F05D2220/32 , F05D2240/11 , F05D2240/81 , F05D2260/202 , F05D2260/204 , Y02T50/676
摘要： A gas turbine engine component is provided. The gas turbine engine component comprises a main body (54) and a leading edge cooling passage (86a) defined within the main body (54). The main body (54) has a leading edge (76) and a leading edge wall (56a) including an elongated transition portion (56b) extending between the leading edge (76) and a proximate flowpath surface of the main body (54). The leading edge cooling passage (86a) comprises an axial flow cooling passage defined within the main body (54) and adjacent to the leading edge wall (56a) and has a leading edge periphery (87) that generally conforms to the elongated transition portion (56b) of the leading edge wall (56a).
摘要翻译：提供燃气涡轮发动机部件。燃气涡轮发动机部件包括主体（54）和限定在主体（54）内的前缘冷却通道（86a）。主体（54）具有前缘（76）和前缘壁（56a），前缘壁包括在主体（54）的前缘（76）和近端流路表面之间延伸的细长过渡部分（56b）。前缘冷却通道（86a）包括限定在主体（54）内并且与前缘壁（56a）相邻的轴向流冷却通道，并且具有大致与细长过渡部分（86a）一致的前缘周边（87） 56b）的前缘壁（56a）。

9. 发明公开

EP3192969A1 BLADE OUTER AIR SEAL (BOA) FOR A GAS TURBINE ENGINE WITH OPTIMIZED LEADING EDGE GEOMETRY 审中-实审转让
标题翻译：用于燃气轮机的叶片外部空气密封（BOA），具有优化的前沿几何形状
公开(公告)号：EP3192969A1
公开(公告)日：2017-07-19
申请号：EP16198828.2
申请日：2016-11-15
申请人： United Technologies Corporation
发明人： PRAISNER, Thomas J. , LUTJEN, Paul M. , BLANEY, Ken F. , SWIFT, Anthony B. , TATMAN, Neil L. , JAROCHYM, Christopher M.
IPC分类号： F01D5/14 , F01D11/08 , F01D25/24 , F01D11/00
CPC分类号： F01D11/08 , F01D5/12 , F01D5/143 , F01D11/001 , F01D25/246 , F05D2220/32 , F05D2240/11 , F05D2250/14 , F05D2250/70 , Y02T50/673
摘要： A gas turbine engine component is provided. The gas turbine engine component comprises a main body (54) having a leading edge (76) and a leading edge wall (56a) including an elongated transition portion (56b) extending between the leading edge (76) and a proximate flowpath surface (64) of the main body (54). The elongated transition portion (56b) has an axial length that is greater than a radial height. A gas turbine engine (20) is also provided.
摘要翻译：提供燃气涡轮发动机部件。燃气涡轮发动机部件包括具有前缘（76）和前缘壁（56a）的主体（54），前缘壁包括在前缘（76）和近端流路表面（64）之间延伸的细长过渡部分（56b））的主体（54）。细长的过渡部分（56b）具有大于径向高度的轴向长度。燃气涡轮发动机（20）也被提供。

10. 发明公开

EP3034808A3 CASTING CORE FOR BLADE OUTER AIR SEAL 有权转让
标题翻译：铸芯FOR铲子外侧密封
公开(公告)号：EP3034808A3
公开(公告)日：2016-08-24
申请号：EP15189830.1
申请日：2015-10-14
申请人： United Technologies Corporation
发明人： BLANEY, Ken F. , SWIFT, Anthony B. , TATMAN, Neil L. , LUTJEN, Paul M. , JAROCHYM, Christopher M.
IPC分类号： F01D11/08 , F01D11/12 , F01D25/24 , B22C9/10
CPC分类号： F01D9/065 , B22C9/10 , F01D11/08 , F01D11/122 , F01D25/246 , F05D2230/211 , F05D2240/11 , F05D2260/204 , Y02T50/676
摘要： A casting core (200) for a Blade Outer Air Seal includes a heat exchange cavity core section (152) in communication with a first plenum section (150) and a second plenum section (154), the first plenum section (150) and the second plenum section (154) being of a thickness greater than the heat exchange cavity section (152).

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