专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

EP3054094B1 GAS TURBINE ENGINE TURBINE VANE BAFFLE AND SERPENTINE COOLING PASSAGE 有权转让
标题翻译：燃气涡轮发动机涡轮叶片挡板和蛇形冷却通道
公开(公告)号：EP3054094B1
公开(公告)日：2018-04-04
申请号：EP16154523.1
申请日：2016-02-05
申请人： United Technologies Corporation
发明人： SPANGLER, Brandon W. , WAITE, Ryan Alan , GAUTSCHI, Steven Bruce , HAGAN, Benjamin F.
IPC分类号： F01D5/18
CPC分类号： F01D9/065 , F01D5/186 , F01D5/187 , F01D25/12 , F01D25/14 , F05D2240/126 , F05D2260/20 , F05D2260/202 , F05D2260/204 , Y02T50/672 , Y02T50/673 , Y02T50/676
摘要： An airfoil (78) for a gas turbine engine includes pressure and suction side walls (90, 92) joined to one another at leading and trailing edges (82, 84). The pressure and suction side walls (90, 92) surround an airfoil cavity (96) and provide an exterior airfoil surface (94). A baffle (98) is arranged in the airfoil cavity (96) and includes a supply hole (120). Ribs (100-108) extend from the pressure and suction side walls (90, 92) into the airfoil cavity (96) and engage the baffle (98). The ribs (100-108) are configured to provide a serpentine cooling passage (112) between the baffle (98) and at least one of the pressure and suction side walls (90, 92). The serpentine cooling passage (112) has first and second passes (116, 118) joined by a bend (117). The ribs (100-108) form a film cooling cavity (110) between the first and second passes (116, 118). The supply hole (120) fluidly connects the baffle (98) to the film cooling cavity (110). Film cooling holes (122) extend through at least one of the pressure and suction side walls (90, 92). The film cooling holes (122) are in fluid communication with the film cooling cavity (110).

2. 发明公开

EP3184751A1 CROSSOVER CONFIGURATION FOR A FLOWPATH COMPONENT IN A GAS TURBINE ENGINE 有权转让
标题翻译：燃气涡轮发动机流道组件的分叉配置
公开(公告)号：EP3184751A1
公开(公告)日：2017-06-28
申请号：EP16205997.6
申请日：2016-12-21
申请人： United Technologies Corporation
发明人： HAGAN, Benjamin F. , DEVORE, Matthew A. , MONGILLO, Dominic J. , WAITE, Ryan Alan
IPC分类号： F01D9/06
CPC分类号： F01D5/187 , F01D9/041 , F01D9/065 , F01D25/12 , F01D25/24 , F02C3/04 , F05D2220/32 , F05D2240/121 , F05D2240/303 , F05D2240/35 , F05D2250/232 , F05D2250/323 , F05D2260/201 , F05D2260/202 , F05D2260/205 , Y02T50/676
摘要： A flowpath component (200) for a gas turbine engine (20) includes a leading edge, a trailing edge (212) connected to the leading edge (212) via a first surface and a second surface, an impingement cavity (250) internal to the flowpath component (200), the impingement cavity (250) being aligned with one of the leading edge (212) and the trailing edge, a cooling passage (240) extending at least partially through the flowpath component (200), and a plurality of crossover holes (260) connecting the cooling passage (240) to the impingement cavity (250). At least one of the crossover holes (260) is aligned normal to an expected direction of fluid flow through the cooling passage (240) and is unaligned with an axial line drawn perpendicular to a stacking line of the flowpath component (200).
摘要翻译：用于燃气涡轮发动机（20）的流路部件（200）包括前缘，经由第一表面和第二表面连接到前缘（212）的后缘（212），冲击腔（250）（200），所述冲击腔（250）与所述前缘（212）和所述后缘中的一个对齐，至少部分地延伸穿过所述流路部件（200）的冷却通道（240），以及多个（260）将冷却通道（240）连接到冲击腔（250）的交叉孔（260）。至少一个交叉孔（260）垂直于通过冷却通道（240）的流体流动的预期方向对齐，并且与垂直于流动路径组件（200）的堆叠线绘制的轴线不对齐。

3. 发明授权

EP3060760B1 AIRFOIL WITH SKIN CORE COOLING 有权转让
公开(公告)号：EP3060760B1
公开(公告)日：2018-12-05
申请号：EP14855974.3
申请日：2014-10-16
申请人： United Technologies Corporation
发明人： HAGAN, Benjamin F. , WAITE, Ryan Alan
IPC分类号： F01D5/18 , F01D25/12 , F02C7/18
CPC分类号： F01D25/12 , F01D5/187 , F01D9/041 , F01D9/065 , F04D29/542 , F04D29/5846 , F05D2220/32 , F05D2240/81 , F05D2260/202 , F05D2260/204 , Y02T50/676
摘要： A gas turbine engine component has an airfoil extending radially inwardly of an outer platform to an inner platform. A central passage is formed within the airfoil and has an inlet end for receiving cooling air. An outlet end in the inner platform delivers cooling air to a downstream use. The airfoil has a suction wall and a pressure wall, and extends in an axial direction from a leading edge to a trailing edge. A suction skin core is between the central passage and the suction wall. A pressure skin core is between the central passage and the pressure wall.

4. 发明公开

EP3112599A1 TRANSFER TUBE AND TURBINE SECTION COMPRISING TRANSFER TUBE 有权转让
标题翻译： TRANSPORTROHR UND TRANSPORTROHR ENTHALTENDER TURBINENABSCHNITT
公开(公告)号：EP3112599A1
公开(公告)日：2017-01-04
申请号：EP16167690.3
申请日：2016-04-29
申请人： United Technologies Corporation
发明人： WAITE, Ryan Alan , JACQUES, Jeffrey Michael , HAGAN, Benjamin F.
IPC分类号： F01D9/06 , F01D25/12
CPC分类号： F01D9/065 , F01D9/02 , F01D9/06 , F01D25/12 , F05D2220/32 , F05D2240/12 , F05D2260/20 , F16L9/006 , Y02T50/675
摘要： What is described is a transfer tube (200) for use with an airfoil of a gas turbine engine (20) coupled to a platform (110). The transfer tube (200) includes a main body (340) having a first end (304) defining an inlet (300) configured to receive a flow of fluid and a second end (306) defining an outlet (302) for the flow of fluid, the main body (340) having a curved section (312). The transfer tube (200) also includes a first mating face (324) coupled to the first end (304) of the main body (340). The transfer tube (200) also includes a second mating face (326) coupled to the second end (306) of the main body (340). At least one of the first mating face (324) or the second mating face (326) is configured to be coupled to a platform body (208) of the outer diameter platform (110B).
摘要翻译：所描述的是用于与联接到平台（110）的燃气涡轮发动机（20）的翼型一起使用的传送管（200）。输送管（200）包括主体（340），主体（340）具有限定入口（300）的第一端（304），该入口构造成接收流体流;以及限定出口（302）的第二端（306）流体，主体（340）具有弯曲部分（312）。传送管（200）还包括联接到主体（340）的第一端（304）的第一配合面（324）。传送管（200）还包括联接到主体（340）的第二端（306）的第二配合面（326）。第一配合面（324）或第二配合面（326）中的至少一个被构造成联接到外径平台（110B）的平台主体（208）。

5. 发明公开

EP3067521A1 TOLERANCE RESISTANCE COVERPLATES 有权转让
标题翻译： ABDECKPLATTENFÜRVARIIERENDE TOLERANZEN
公开(公告)号：EP3067521A1
公开(公告)日：2016-09-14
申请号：EP16159496.5
申请日：2016-03-09
申请人： United Technologies Corporation
发明人： SPANGLER, Brandon W. , VU, Ky H. , DeGRAY, Jeffrey J. , WAITE, Ryan Alan , CAVALLO, Gina , DZIUBA, Thomas P.
IPC分类号： F01D5/18 , F01D9/04
CPC分类号： F01D9/041 , F01D5/02 , F01D5/186 , F01D5/189 , F01D9/065 , F01D25/12 , F04D29/321 , F05D2220/32 , F05D2230/21 , F05D2230/642 , F05D2240/126 , F05D2240/80 , F05D2260/20 , F05D2260/30 , Y02T50/676
摘要： A gas turbine engine component assembly comprises a first component (62a 1 ) and a second component (62a 2 ) circumferentially spaced from the first component (62a 1 ) relative to an engine center axis (A). A first baffle (72) is associated with the first component (62a 1 ). A second baffle (72) is associated with the second component (62a 2 ). Each of the first and second baffles (72) includes at least one radial baffle tab (206). A gap (212) is between the first and second baffles (72) to define a cooling air inlet. A first coverplate (200) is associated with the first baffle (72) to cover a first portion of the gap (212). A second coverplate (200) is associated with the second baffle (72) to cover a second portion of the gap (212). The first and second coverplates (200) are separate from each other, and include at least one coverplate radial tab (204) that cooperates with an associated at least one baffle radial tab (206) to prevent leakage gaps between the first and second baffle plates (72) and the first and second coverplates (200).
摘要翻译：燃气涡轮发动机部件组件包括相对于发动机中心轴线（A）与第一部件（62a 1）周向间隔开的第一部件（62a 1）和第二部件（62a 2）。第一挡板（72）与第一部件（62a 1）相关联。第二挡板（72）与第二部件（62a 2）相关联。第一和第二挡板（72）中的每一个包括至少一个径向挡板（206）。间隙（212）位于第一和第二挡板（72）之间，以限定冷却空气入口。第一盖板（200）与第一挡板（72）相关联以覆盖间隙（212）的第一部分。第二盖板（200）与第二挡板（72）相关联以覆盖间隙（212）的第二部分。第一和第二盖板（200）彼此分离，并且包括与相关联的至少一个挡板径向突片（206）配合的至少一个盖板径向突片（204），以防止第一和第二挡板之间的泄漏间隙（72）和第一和第二盖板（200）。

6. 发明公开

EP3060760A1 AIRFOIL WITH SKIN CORE COOLING 有权转让
标题翻译：勺含有OUTSIDE堆芯冷却
公开(公告)号：EP3060760A1
公开(公告)日：2016-08-31
申请号：EP14855974.3
申请日：2014-10-16
申请人： United Technologies Corporation
发明人： HAGAN, Benjamin F. , WAITE, Ryan Alan
IPC分类号： F01D5/18 , F01D25/12 , F02C7/18
CPC分类号： F01D25/12 , F01D5/187 , F01D9/041 , F01D9/065 , F04D29/542 , F04D29/5846 , F05D2220/32 , F05D2240/81 , F05D2260/202 , F05D2260/204 , Y02T50/676
摘要： A gas turbine engine component has an airfoil extending radially inwardly of an outer platform to an inner platform. A central passage is formed within the airfoil and has an inlet end for receiving cooling air. An outlet end in the inner platform delivers cooling air to a downstream use. The airfoil has a suction wall and a pressure wall, and extends in an axial direction from a leading edge to a trailing edge. A suction skin core is between the central passage and the suction wall. A pressure skin core is between the central passage and the pressure wall.

7. 发明公开

EP3054113A1 IMPINGEMENT COOLED COMPONENT, CORRESPONDING COOLING METHOD AND GAS TURBINE ENGINE COMPONENT 有权转让
标题翻译： PRALLGEKÜHLTESBAUTEIL，ZUGEHÖRIGESKÜHLVERFAHRENUND BAUTEIL EINES GASTURBINENTRIEBWERKS
公开(公告)号：EP3054113A1
公开(公告)日：2016-08-10
申请号：EP16154904.3
申请日：2016-02-09
申请人： United Technologies Corporation
发明人： WAITE, Ryan Alan , DEVORE, Matthew A.
IPC分类号： F01D25/12 , F23R3/00 , F01D5/18
CPC分类号： F01D25/12 , F01D5/186 , F01D5/187 , F05D2240/11 , F05D2240/81 , F05D2250/182 , F05D2250/183 , F05D2250/184 , F05D2250/21 , F05D2250/28 , F05D2250/611 , F05D2260/201 , F05D2260/202 , F05D2260/205 , F05D2260/22141 , F23R3/002 , F23R2900/03044 , Y02T50/676
摘要： An impingement cooled component includes a first wall having a plurality of impingement holes (112) and a second wall spaced apart from the first wall. The second wall is downstream of the first wall, relative to a cooling flow (130), the second wall has a contoured surface (122) facing the first wall. The contoured surface (122) includes a plurality of contours defined by at least one of a plurality of peaks (128) and a plurality of valleys (126), and at least one of the contours in the plurality of contours is aligned with an axis (112a) defined by one of the impingement holes (112) in the plurality of impingement holes (112).
摘要翻译：冲击冷却部件包括具有多个冲击孔（112）的第一壁和与第一壁间隔开的第二壁。第二壁相对于冷却流（130）在第一壁的下游，第二壁具有面向第一壁的轮廓表面（122）。轮廓表面（122）包括由多个峰（128）和多个谷（126）中的至少一个限定的多个轮廓，并且多个轮廓中的至少一个轮廓与轴对齐（112a）由多个冲击孔（112）中的一个冲击孔（112）限定的（112a）。

8. 发明授权

EP3101228B1 FLOW SPLITTING BAFFLE 有权
公开(公告)号：EP3101228B1
公开(公告)日：2019-07-10
申请号：EP16159262.1
申请日：2016-03-08
申请人： United Technologies Corporation
发明人： HAGEN, Benjamin F. , WAITE, Ryan Alan , MONGILLO, Dominic J.
IPC分类号： F01D5/18 , B01D53/00 , F01D9/06 , F02C7/18 , F01D5/14 , F01D25/00 , F01D25/12

9. 发明公开

EP3061913A1 GAS TURBINE ENGINE AIRFOIL COOLING CONFIGURATION WITH PRESSURE GRADIENT SEPARATORS 有权转让
标题翻译： GASTURBINENTRIEBWERKSSCHAUFEL-KÜHLKONFIGURATIONMITDRUCKGEFÄLLESEPARATOREN
公开(公告)号：EP3061913A1
公开(公告)日：2016-08-31
申请号：EP16157740.8
申请日：2016-02-26
申请人： United Technologies Corporation
发明人： QUACH, San , WAITE, Ryan Alan , KING, Christopher , GAUTSCHI, Steven Bruce
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/147 , F01D9/041 , F01D11/08 , F01D25/30 , F05D2220/32 , F05D2240/122 , F05D2240/127 , F05D2240/304 , F05D2240/307 , F05D2240/35 , F05D2240/55 , F05D2260/221 , F05D2260/2212 , F05D2260/2214 , F23R3/002 , Y02T50/673 , Y02T50/676
摘要： A turbine blade (64) for a gas turbine engine (20) comprises an airfoil (78; 164) including spaced apart pressure and suction side walls (86, 88) joined at leading and trailing edges (82; 84; 182) to provide an exterior airfoil surface that extends in a radial direction (R) from a platform (76) to a tip (80; 180). A cavity (94; 194) is provided between the pressure and suction side walls (86, 88) near the trailing edge (84). The cavity (94; 194) includes an interior region (96) bounded by first and second exit regions (98, 100) arranged at an angle (102) relative to one another to form a cooling configuration used to effectively turn the cooling fluid at the adjacent cooling fluid exits. The first and second exit regions (98, 100) are respectively in low and high pressure regions (104, 106) relative to one another. First and second pedestal groups (110, 112; 210, 212) respectively are arranged at the first and second exit regions (98, 100). The second pedestal group (112; 212) has first and second pedestals (114, 116; 214, 216) each terminating in an end (120, 122). The ends (122) of the second pedestals (116; 216) extend beyond the ends (120) of first pedestals (114; 214).
摘要翻译：一种用于燃气涡轮发动机（20）的涡轮机叶片（64）包括翼型件（78; 164），其包括在前缘和后缘（82; 84; 182）处连接的间隔开的压力和吸力侧壁（86,88），以提供外部翼型表面，其从径向方向（R）从平台（76）延伸到尖端（80; 180）。在后缘（84）附近的压力侧和吸力侧壁（86,88）之间设置空腔（94; 194）。空腔（94; 194）包括由相对于彼此成角度（102）布置的第一和第二出口区域（98,100）限定的内部区域（96），以形成用于有效地将冷却流体相邻的冷却流体离开。第一和第二出口区域（98,100）分别相对于彼此在低压区和高压区（104,106）中。第一和第二基座组（110,112; 210,212）分别布置在第一和第二出口区域（98,100）处。第二基座组（112; 212）具有分别终止在端部（120,122）中的第一和第二基座（114,116; 214,216）。第二基座（116; 216）的端部（122）延伸超过第一基座（114; 214）的端部（120）。

10. 发明公开

EP3054094A1 GAS TURBINE ENGINE TURBINE VANE BAFFLE AND SERPENTINE COOLING PASSAGE 有权转让
标题翻译：燃气涡轮发动机涡轮叶片挡板和蛇形冷却通道
公开(公告)号：EP3054094A1
公开(公告)日：2016-08-10
申请号：EP16154523.1
申请日：2016-02-05
申请人： United Technologies Corporation
发明人： SPANGLER, Brandon W. , WAITE, Ryan Alan , GAUTSCHI, Steven Bruce , HAGAN, Benjamin F.
IPC分类号： F01D5/18
CPC分类号： F01D9/065 , F01D5/186 , F01D5/187 , F01D25/12 , F01D25/14 , F05D2240/126 , F05D2260/20 , F05D2260/202 , F05D2260/204 , Y02T50/672 , Y02T50/676
摘要： An airfoil (78) for a gas turbine engine includes pressure and suction side walls (90, 92) joined to one another at leading and trailing edges (82, 84). The pressure and suction side walls (90, 92) surround an airfoil cavity (96) and provide an exterior airfoil surface (94). A baffle (98) is arranged in the airfoil cavity (96) and includes a supply hole (120). Ribs (100-108) extend from the pressure and suction side walls (90, 92) into the airfoil cavity (96) and engage the baffle (98). The ribs (100-108) are configured to provide a serpentine cooling passage (112) between the baffle (98) and at least one of the pressure and suction side walls (90, 92). The serpentine cooling passage (112) has first and second passes (116, 118) joined by a bend (117). The ribs (100-108) form a film cooling cavity (110) between the first and second passes (116, 118). The supply hole (120) fluidly connects the baffle (98) to the film cooling cavity (110). Film cooling holes (122) extend through at least one of the pressure and suction side walls (90, 92). The film cooling holes (122) are in fluid communication with the film cooling cavity (110).
摘要翻译：用于燃气涡轮发动机的翼型件（78）包括在前缘和后缘（82,84）处彼此连接的压力侧壁和吸力侧壁（90,92）。压力和吸入侧壁（90,92）围绕翼型腔（96）并且提供外部翼型表面（94）。挡板（98）布置在翼型腔（96）中并且包括供应孔（120）。肋（100-108）从压力和吸入侧壁（90,92）延伸到翼型腔（96）中并与挡板（98）接合。肋（100-108）构造成在挡板（98）与压力侧壁和吸力侧壁（90,92）中的至少一个之间提供蛇形冷却通道（112）。蛇形冷却通道（112）具有由弯头（117）连接的第一和第二通道（116,118）。肋（100-108）在第一和第二通道（116,118）之间形成薄膜冷却腔（110）。供应孔（120）将挡板（98）流体连接到膜冷却腔（110）。薄膜冷却孔（122）延伸穿过压力侧壁和吸入侧壁（90,92）中的至少一个。膜冷却孔（122）与膜冷却腔（110）流体连通。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式