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1. 发明授权

US11384841B2 Brush seal with crossing bristles 有权
公开(公告)号：US11384841B2
公开(公告)日：2022-07-12
申请号：US16706183
申请日：2019-12-06
申请人： United Technologies Corporation
发明人： Jose R. Paulino , Neil L. Tatman , Paul J. Burgess
IPC分类号： F16J15/3288
摘要： A seal joint assembly is provided that includes a stationary seal carrier, a stationary seal land and a brush seal. The stationary seal land includes a seal land surface. The brush seal is mounted to the stationary seal carrier. The brush seal includes a first set of bristles and a second set of bristles. The first set of bristles includes a first bristle that contacts the seal land surface. The second set of bristles includes a second bristle that contacts the seal land surface. The second bristle crosses the first bristle.

2. 发明授权

US10138748B2 Gas turbine engine components with optimized leading edge geometry 有权
公开(公告)号：US10138748B2
公开(公告)日：2018-11-27
申请号：US14997323
申请日：2016-01-15
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Thomas J. Praisner , Paul M. Lutjen , Ken F. Blaney , Anthony B. Swift , Neil L. Tatman , Christopher M. Jarochym
IPC分类号： F01D11/08 , F01D5/14 , F01D25/24 , F01D5/12 , F01D11/00
摘要： A gas turbine engine component is provided. The gas turbine engine component comprises a main body having a leading edge and a leading edge wall including an elongated transition portion extending between the leading edge and a proximate flowpath surface of the main body. The elongated transition portion has an axial length that is greater than a radial height. A gas turbine engine is also provided.

3. 发明授权

US11035470B2 Multi-plane brush seal 有权
公开(公告)号：US11035470B2
公开(公告)日：2021-06-15
申请号：US15946093
申请日：2018-04-05
申请人： United Technologies Corporation
发明人： Neil L. Tatman , Shawn K. Hamilton
IPC分类号： F16J15/3288 , F01D11/02 , F01D11/00
摘要： A multi-plane annular brush seal is provided. The brush seal includes a plurality of bristles attached to a front plate and a back plate. The back plate has a BP base end, a first BP inner side surface, a BP transition surface, a second BP inner side surface, and a BP tip end. The first BP inner side surface extends from the BP base end to the BP transition surface, and the second BP inner surface extends from the BP transition surface to the BP tip end. At any given circumferential position of the brush seal, the first BP inner side surface extends substantially parallel to a first plane, and the second BP inner side surface extends substantially parallel to a second plane. The first plane is skewed from the second plane by an obtuse angle.

4. 发明申请

US20170211415A1 VARIABLE THICKNESS CORE FOR GAS TURBINE ENGINE COMPONENT 审中-公开
公开(公告)号：US20170211415A1
公开(公告)日：2017-07-27
申请号：US15005061
申请日：2016-01-25
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Anthony B Swift , Ken F. Blaney , Paul M. Lutjen , Neil L. Tatman , Dominic J. Mongillo
IPC分类号： F01D25/12 , F01D9/04 , F01D5/14 , F02C7/12 , F01D11/08
摘要： A gas turbine engine component has a body extending between two circumferential sides, and between a leading edge and a trailing edge. A refractory metal core within the body forms at least one cooling circuit to utilize fluid to cool the body. When the refractory metal core is removed from the body, the at least one cooling circuit includes an inlet, an outlet, and a passage that varies in cross-sectional area between the inlet and outlet. A method of manufacturing a gas turbine engine, a method of manufacturing a core, and a refractory metal core are also disclosed.

5. 发明申请

US20160312661A1 BLADE OUTER AIR SEAL SPRING CLIPS 有权
标题翻译：叶片外密封弹簧夹
公开(公告)号：US20160312661A1
公开(公告)日：2016-10-27
申请号：US14696862
申请日：2015-04-27
申请人： United Technologies Corporation
发明人： Brian Duguay , Neil L. Tatman
IPC分类号： F01D25/28 , F16B2/22 , F01D11/08
CPC分类号： F01D25/28 , F01D11/08 , F01D25/246 , F05D2220/36 , F05D2240/55 , F05D2260/30 , F16B2/22
摘要： A spring clip for a blade outer air seal (BOAS) includes a clip body defining a first end configured to operatively engage with a BOAS retaining structure on a BOAS and a second end configured to engage with at least one of a mounting hook of a BOAS and a BOAS mount.
摘要翻译：用于叶片外部空气密封件（BOAS）的弹簧夹包括限定构造成与BOAS上的BOAS保持结构可操作地接合的第一端的夹子主体，以及构造成与BOAS的安装钩中的至少一个接合的第二端和一个BOAS安装。

6. 发明申请

US20160273376A1 TAILORED THERMAL CONTROL SYSTEM FOR GAS TURBINE ENGINE BLADE OUTER AIR SEAL ARRAY 审中-公开
标题翻译：用于气体涡轮发动机叶片外部空气密封阵列的定制热控制系统
公开(公告)号：US20160273376A1
公开(公告)日：2016-09-22
申请号：US15023593
申请日：2014-10-06
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Philip R. Rioux , Neil L. Tatman
IPC分类号： F01D11/18 , F01D25/24
摘要： A clearance control ring for a clearance control system of a gas turbine engine includes a contoured radial outer portion that defines a multiple of fins and a multiple of slots. A clearance control system of a gas turbine engine includes a clearance control ring with a radial inner portion from which a contoured radial outer portion extends. The contoured radial outer portion defines a multiple of fins and a multiple of slots. A blade outer air seal assembly with a clearance control ring land which receives the radial inner portion. A method of controlling a radial tip clearance within a gas turbine engine includes tailoring a multiple of fins and a multiple of slots of a clearance control ring for both steady state and transient clearance operations.
摘要翻译：用于燃气涡轮发动机的间隙控制系统的间隙控制环包括限定多个翅片和多个槽的轮廓径向外部部分。燃气涡轮发动机的间隙控制系统包括具有径向内部部分的间隙控制环，轮廓径向外部部分从该径向内部部分延伸。轮廓的径向外部部分限定了多个翅片和多个狭槽。叶片外部空气密封组件，其具有容纳径向内部的间隙控制环形凸台。控制燃气涡轮发动机内的径向顶端间隙的方法包括为稳态和瞬时间隙操作调节多个叶片和间隙控制环的多个槽。

7. 发明申请

US20160169016A1 REVERSIBLE FLOW BLADE OUTER AIR SEAL 审中-公开
标题翻译：可逆流动叶片外部空气密封
公开(公告)号：US20160169016A1
公开(公告)日：2016-06-16
申请号：US14880403
申请日：2015-10-12
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Ken F. Blaney , Anthony B. Swift , Neil L. Tatman , Paul M. Lutjen , Christopher M. Jarochym
IPC分类号： F01D9/06 , B22C9/10 , F01D11/08
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 for a Blade Outer Air Seal includes a heat exchange cavity core section in communication with a first plenum section and a second plenum section, the first plenum and the second plenum section are of a thickness greater than the heat exchange cavity section.
摘要翻译：用于叶片外部空气密封件的铸造芯部包括与第一增压部分和第二增压部分连通的热交换腔芯部分，第一增压室和第二增压部分的厚度大于热交换腔部分。

8. 发明授权

US10815827B2 Variable thickness core for gas turbine engine component 有权
公开(公告)号：US10815827B2
公开(公告)日：2020-10-27
申请号：US15005061
申请日：2016-01-25
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Anthony B. Swift , Ken F. Blaney , Paul M. Lutjen , Neil L. Tatman , Dominic J. Mongillo
IPC分类号： F01D25/12 , B22C9/10 , F01D5/18 , F01D5/14 , F01D9/04 , F01D11/08 , F02C7/12
摘要： A gas turbine engine component has a body extending between two circumferential sides, and between a leading edge and a trailing edge. A refractory metal core within the body forms at least one cooling circuit to utilize fluid to cool the body. When the refractory metal core is removed from the body, the at least one cooling circuit includes an inlet, an outlet, and a passage that varies in cross-sectional area between the inlet and outlet. A method of manufacturing a gas turbine engine, a method of manufacturing a core, and a refractory metal core are also disclosed.

9. 发明申请

US20190309855A1 MULTI-PLANE BRUSH SEAL 审中-公开
公开(公告)号：US20190309855A1
公开(公告)日：2019-10-10
申请号：US15946093
申请日：2018-04-05
申请人： United Technologies Corporation
发明人： Neil L. Tatman , Shawn K. Hamilton
IPC分类号： F16J15/3288 , F01D11/02
摘要： A multi-plane annular brush seal is provided. The brush seal includes a plurality of bristles attached to a front plate and a back plate. The back plate has a BP base end, a first BP inner side surface, a BP transition surface, a second BP inner side surface, and a BP tip end. The first BP inner side surface extends from the BP base end to the BP transition surface, and the second BP inner surface extends from the BP transition surface to the BP tip end. At any given circumferential position of the brush seal, the first BP inner side surface extends substantially parallel to a first plane, and the second BP inner side surface extends substantially parallel to a second plane. The first plane is skewed from the second plane by an obtuse angle.

10. 发明授权

US10100667B2 Axial flowing cooling passages for gas turbine engine components 有权
公开(公告)号：US10100667B2
公开(公告)日：2018-10-16
申请号：US14997315
申请日：2016-01-15
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Anthony B. Swift , Paul M. Lutjen , Neil L. Tatman , Dominic J. Mongillo, Jr. , Matthew A. Devore , Ken F. Blaney
IPC分类号： F01D25/12 , F01D11/08 , F01D25/24
摘要： A gas turbine engine component is provided. The gas turbine engine component comprises a main body and a leading edge cooling passage defined within the main body. The main body has a leading edge and a leading edge wall including an elongated transition portion extending between the leading edge and a proximate flowpath surface of the main body. The leading edge cooling passage comprises an axial flow cooling passage defined within the main body and adjacent to the leading edge wall and has a leading edge periphery that generally conforms to the elongated transition portion of the leading edge wall.

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