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1. 发明公开

EP3656983A1 THERMAL GRADIENT REDUCING DEVICE FOR GAS TURBINE ENGINE COMPONENT 有权转让
公开(公告)号：EP3656983A1
公开(公告)日：2020-05-27
申请号：EP19210480.0
申请日：2019-11-20
申请人： United Technologies Corporation
发明人： GENERALE, Adam P. , DUBE, Bryan P.
IPC分类号： F01D5/18 , F01D9/06 , F01D11/00
摘要： An internally cooled component for a gas turbine engine (20) includes a component having one or more exterior walls defining an internal component cavity (98) configured for a cooling airflow (82) to flow therethrough. An internal component rib (96) extends into the internal component cavity from the one or more exterior walls. An insert (100) is positioned in the internal component cavity, and a flow discourager (102) is positioned at the insert and is configured to prevent the cooling airflow from flowing past the internal component rib.

2. 发明公开

EP3009608A1 VANE ASSEMBLY WITH TRAPPED SEGMENTED VANE STRUCTURES 有权转让
标题翻译： SCHAUFELANORDNUNG MIT EINGESCHLOSSENEN，SEGMENTIERTEN SCHAUFELSTRUKTUREN
公开(公告)号：EP3009608A1
公开(公告)日：2016-04-20
申请号：EP15187544.0
申请日：2015-09-30
申请人： United Technologies Corporation
发明人： CARR, Jesse M. , DUBE, Bryan P. , DUELM, Shelton O.
IPC分类号： F01D9/04
摘要： A vane assembly (60;... 560) includes inner and outer rings (62a, 62b; 162a, 162b), a plurality of segmented vane structures (64; 164) circumferentially-spaced around a central axis (A) and between the inner and outer rings (62a, 62b; 162a, 162b), and at least one spring (74;... 674) that mechanically traps the segmented vane structures (64; 164) in radial compression between the inner and outer rings (62a, 62b; 162a, 162b). Corresponding method for a vane assembly (60;... 560).
摘要翻译：叶片组件（60; ... 560）包括内环和外环（62a，62b; 162a，162b），围绕中心轴线（A）周向间隔开的多个分段叶片结构（64; 164）内部和外部环（62a，62b; 162a，162b）以及至少一个弹簧（74; ... 674），其在所述内圈和外圈（62a）之间以径向压缩机械地捕集所述分段的叶片结构（64; 164），62b; 162a，162b）。叶片组件（60; ... 560）的相应方法。

3. 发明公开

EP2995777A1 ATTACHMENT FACES FOR CLAMPED TURBINE STATOR OF A GAS TURBINE ENGINE 审中-实审转让
标题翻译： BEFESTIGUNGSFLÄCHENFÜREINGESPANNTEN TURBINENSTATOR EINES GASTURBINENMOTORS
公开(公告)号：EP2995777A1
公开(公告)日：2016-03-16
申请号：EP15184339.8
申请日：2015-09-08
申请人： United Technologies Corporation
发明人： CARR, Jesse M. , DUBE, Bryan P.
IPC分类号： F01D9/04 , F01D25/24 , F04D29/64
CPC分类号： F01D9/042 , F01D9/041 , F01D25/246 , F04D29/542 , F04D29/644 , F05D2230/51 , F05D2260/30 , Y02T50/673
摘要： An airfoil fairing shell (106) for a gas turbine engine includes an airfoil section (72) between an outer vane endwall (80) and an inner vane endwall (76), at least one of the outer vane endwall (80) and the inner vane endwall (76) including a radial attachment face (150), a suction side tangential attachment face (152), a pressure side tangential attachment face (154), and an axial attachment face (156). Lugs (160) of a structural support (110) interface with at least one of the attachment faces. An airfoil faring shell (106) with a plurality of attachment faces (150, 152, 154, 156) made by a thicker region on the endwalls forming mating surfaces with the other fairings.
摘要翻译：用于燃气涡轮发动机的翼型整流罩（106）包括在外叶片端壁（80）和内叶片端壁（76）之间的翼型部分（72），外叶片端壁（80）和内叶片端壁（76），包括径向附接面（150），吸力侧切向附接面（152），压力侧切向附接面（154）和轴向附接面（156）。结构支撑件（110）的凸缘（160）与至少一个附接面接合。具有多个附接面（150,152,154,156）的翼型制动壳体（106）由端壁上较厚的区域制成，与其它整流罩形成配合表面。

4. 发明授权

EP3009608B1 VANE ASSEMBLY WITH TRAPPED SEGMENTED VANE STRUCTURES 有权转让
公开(公告)号：EP3009608B1
公开(公告)日：2019-10-30
申请号：EP15187544.0
申请日：2015-09-30
申请人： United Technologies Corporation
发明人： CARR, Jesse M. , DUBE, Bryan P. , DUELM, Shelton O.
IPC分类号： F01D9/04

5. 发明授权

EP3009601B1 AIRFOIL ASSEMBLY WITH SPACER AND TIE-SPAR 有权转让
公开(公告)号：EP3009601B1
公开(公告)日：2019-08-14
申请号：EP15187602.6
申请日：2015-09-30
申请人： United Technologies Corporation
发明人： CARR, Jesse M. , DUBE, Bryan P.
IPC分类号： F01D5/28 , F01D9/04 , F01D25/24

6. 发明公开

EP3382147A1 ASYMMETRIC VANE ASSEMBLY 审中-实审转让
公开(公告)号：EP3382147A1
公开(公告)日：2018-10-03
申请号：EP18153055.1
申请日：2018-01-23
申请人： United Technologies Corporation
发明人： ESTES, Matthew B. , DUBE, Bryan P.
IPC分类号： F01D5/14 , F01D9/04
CPC分类号： F01D9/041 , F04D29/666 , F05D2250/38 , F05D2250/73 , F05D2260/961 , Y02T50/672 , Y02T50/673
摘要： An asymmetric vane assembly (350) includes a high count vane section including a first plurality of vanes (358A) oriented in a first position. The asymmetric vane assembly (350) also includes a low count vane section including a second plurality of vanes (358B) oriented in a second position, a total number of vanes in the first plurality of vanes (358A) being greater than a total number of vanes in the second plurality of vanes (358B), and each vane of the high count vane section and each vane of the low count vane section having substantially similar internal core geometry.

7. 发明公开

EP3683405A1 FRUSTIC LOAD TRANSMISSION FEATURE FOR COMPOSITE STRUCTURES 有权转让
公开(公告)号：EP3683405A1
公开(公告)日：2020-07-22
申请号：EP20152063.2
申请日：2020-01-15
申请人： United Technologies Corporation
发明人： FARRAR, Bryan H. , LAZUR, Andrew J. , LILES, Howard J. , DUBE, Bryan P.
IPC分类号： F01D9/04 , F01D25/00 , F01D25/24
摘要： A stator vane (200) may comprise an airfoil (206) extending between a first platform (204) and a second platform (202), the airfoil (206) including a core (216) extending relatively orthogonal to the first platform (204) and the second platform (202), at least one of the first platform (204) or second platform (202) comprising a frustic load transmission feature (400), wherein the frustic load transmission feature (400) comprises at least a first angular surface (402) disposed proximate a platform edge, wherein the first angular surface is defined by a non-orthogonal angle θ with respect to an outer platform surface (212).

8. 发明公开

EP3287605A1 RIM SEAL FOR GAS TURBINE ENGINE 有权转让
标题翻译：用于燃气轮机的RIM密封件
公开(公告)号：EP3287605A1
公开(公告)日：2018-02-28
申请号：EP17177520.8
申请日：2017-06-22
申请人： United Technologies Corporation
发明人： BANKS, Anton G. , CORCORAN, Christopher , DUBE, Bryan P.
IPC分类号： F01D11/00 , F01D5/02 , F01D5/30 , F01D5/08 , F02C7/28
CPC分类号： F01D11/006 , F01D5/02 , F01D5/08 , F01D5/088 , F01D5/30 , F01D11/00 , F01D11/005 , F02C3/04 , F02C7/28 , F04D29/083 , F04D29/322 , F05D2220/323 , F05D2240/35 , Y02T50/676
摘要： A rim seal (70) for a rotor (48; 90) of a gas turbine engine (10) includes a seal portion (74) extending circumferentially across a rim cavity (68) of a rotor, the seal portion configured to seal the rim cavity and a first foot portion (76) extending radially inwardly from a first end (78) of the seal portion. A rotor assembly for a gas turbine engine includes a rotor disc (50; 94) and a plurality of rotor blades (52; 92) secured to the rotor disc defining a rim cavity between the rotor disc and a rim portion (66) of the plurality of rotor blades. A rim seal is located in the rim cavity and includes a seal portion extending circumferentially across the rim cavity, the seal portion configured to seal the rim cavity. The seal portion has an increasing radial thickness with increasing distance from a first end (78) of the rim seal and from a second end (78) opposite the first end.
摘要翻译：用于燃气涡轮发动机（10）的转子（48; 90）的轮辋密封件（70）包括密封部分（74），该密封部分（74）横跨转子的轮辋腔体（68）周向延伸，该密封部分构造成密封轮辋腔和从密封部分的第一端（78）径向向内延伸的第一脚部（76）。用于燃气涡轮发动机的转子组件包括转子盘（50; 94）和固定到转子盘的多个转子叶片（52; 92），限定转子盘和转子盘的边缘部分（66）之间的边缘腔，多个转子叶片。轮辋密封件位于轮辋腔体中并且包括密封部分，该密封部分横跨轮辋腔体周向地延伸，该密封部分构造成密封轮辋腔体。密封部分随着距轮辋密封件的第一端部（78）和与第一端部相对的第二端部（78）的距离增加而具有增加的径向厚度。

9. 发明公开

EP3051065A1 CORED AIRFOIL PLATFORM WITH OUTLET SLOTS 有权转让
标题翻译：麻省理工大学麻省理工学院麻省理工学院麻省理工学院
公开(公告)号：EP3051065A1
公开(公告)日：2016-08-03
申请号：EP16152007.7
申请日：2016-01-20
申请人： United Technologies Corporation
发明人： HAGAN, Benjamin F. , WAITE, Ryan Alan , DUBE, Bryan P. , MONGILLO Jr., Dominic J.
IPC分类号： F01D5/18 , F01D5/22
CPC分类号： F01D5/187 , F01D5/147 , F01D5/18 , F01D5/225 , F01D9/041 , F01D9/065 , F01D25/12 , F05D2220/32 , F05D2230/211 , F05D2240/12 , F05D2240/30 , F05D2240/81 , F05D2260/202 , F05D2260/22141
摘要： An airfoil (20) includes a platform (22) that has platform leading and trailing ends (28,30), lateral side faces (32,34), and inner and outer faces (36,38). An airfoil portion (24) extends outwardly from the inner face (36) of the platform (22). The airfoil portion (24) includes airfoil leading and trailing ends (40,42) and side walls (44,46) that join the airfoil leading and trailing ends (40,42). The platform (22) includes a cooling passage (50) that has an inlet (54) at a forward location, outlet slots (56) at the platform trailing end (30), and an intermediate passage portion (58) that extends from the inlet (54) to the outlet slots (56). The intermediate passage portion (58) includes a common manifold region (60) that feeds the outlet slots (56).
摘要翻译：机翼（20）包括具有平台前端和后端（28,30），横向侧面（32,34）以及内表面（36,38）的平台（22）。机翼部分（24）从平台（22）的内表面（36）向外延伸。机翼部分（24）包括连接翼型件前端和后端（40,42）的翼型件前端和后端（40,42）和侧壁（44,46）。平台（22）包括在前部位置具有入口（54）的冷却通道（50），平台尾端（30）处的出口狭槽（56）和从中间通道部分（58）延伸的中间通道部分入口（54）到出口槽（56）。中间通道部分（58）包括供给出口槽（56）的公共歧管区域（60）。

10. 发明公开

EP3009601A1 AIRFOIL ASSEMBLY WITH SPACER AND TIE-SPAR 有权转让
标题翻译：佐治亚州麻省理工学院
公开(公告)号：EP3009601A1
公开(公告)日：2016-04-20
申请号：EP15187602.6
申请日：2015-09-30
申请人： United Technologies Corporation
发明人： CARR, Jesse M. , DUBE, Bryan P.
IPC分类号： F01D5/28 , F01D9/04 , F01D25/24
CPC分类号： F01D9/041 , F01D5/284 , F01D9/042 , F01D25/246 , F05D2220/32 , F05D2230/51 , F05D2230/60 , F05D2230/642 , F05D2240/12 , F05D2240/80 , F05D2260/31 , F05D2300/5021 , Y02T50/672 , Y02T50/673 , Y02T50/6765
摘要： An airfoil assembly (60) includes at least one airfoil (62) that has a hollow interior (64) and first and second platforms (66, 68). At least one tie-spar (70) extends along an axis (A1) through the first platform (66), the hollow interior (64) of the airfoil (62), and the second platform (68). There is a thermal expansion difference (D) between a thermal expansion (T1) of the tie-spar (70) in the axial direction and the combined thermal expansion (T2) of the airfoil (62) and the first and second platforms (66, 68) in the axial direction. At least one spacer portion (72) is arranged on the tie-spar (70), and has a thermal expansion (T3) in the axial direction that is greater than the thermal expansion difference (D) such that the spacer portion (72) maintains the tie-spar (70) under tension and clamps the first and second platforms (66, 68) on the airfoil (62).
摘要翻译：机翼组件（60）包括具有中空内部（64）和第一和第二平台（66,68）的至少一个翼型件（62）。至少一个连接翼梁（70）沿着轴线（A1）延伸穿过第一平台（66），翼型件（62）的中空内部（64）和第二平台（68）。在轴向上的连接翼梁（70）的热膨胀（T1）与翼型件（62）和第一和第二平台（66）的组合热膨胀（T2）之间存在热膨胀差（D），68）。至少一个间隔部分（72）布置在连接翼梁（70）上，并且在轴向上具有大于热膨胀差（D）的热膨胀（T3），使得间隔部分（72）将扎带翼（70）保持在张力下并夹紧翼型件（62）上的第一和第二平台（66,68）。

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