-
81.发明公开
公开(公告)号：EP2290193A3
公开(公告)日：2014-07-16
申请号：EP10251435.3
申请日：2010-08-12
CPC分类号： F01D5/187 , F01D5/081 , F01D9/06 , F05D2240/81 , F05D2260/201
摘要： A vane (60) for use in a gas turbine engine has a platform (64) connected to an airfoil (66). There is a cooling passage (68) for supplying cooling air to the platform (64). A cooling chamber (74) supplies cooling air to a plurality of cooling slots (86) at the platform (64). The cooling slots (86) have a non-uniform cross section.
-
公开(公告)号：EP2471613A3
公开(公告)日：2014-05-21
申请号：EP11195322.0
申请日：2011-12-22
发明人： Farris, John R , Propheter-Hinckley, Tracy A. , Jenne, Douglas C. , Glenier, Matthew S. , Thomas, Peter H.
IPC分类号： B22C9/10
摘要： A casting core assembly includes a metallic core (28) and a ceramic core (26). The process for forming the casting core assembly includes inserting a ceramic plug (140) of a metallic core and ceramic plug core subassembly into a compartment (160) of the ceramic core (26). The ceramic plug (140) is secured to the ceramic core (26), preferably by a ceramic adhesive.
-
83.发明授权A turbine vane segment, the corresponding nozzle assembly and method of cooling this vane 有权一种涡轮叶片，用于冷却叶片的相应的冷却通道布置和方法
公开(公告)号：EP2093376B1
公开(公告)日：2014-03-12
申请号：EP09250151.9
申请日：2009-01-20
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F05D2250/185 , F05D2270/301
-
公开(公告)号：EP2213839A3
公开(公告)日：2013-12-25
申请号：EP10250001.4
申请日：2010-01-04
CPC分类号： F01D5/284 , F01D5/3015 , F05D2240/80 , Y02T50/672 , Y02T50/673
摘要： A segmented component (12, 14) for use with a gas turbine engine comprises a radially extending gas path portion (12B). The gas path portion is for interacting with gas flow from the gas turbine engine. The component is divided into axially aligned segments comprising a forward segment (24A), an aft segment (24B), and a plurality of middle segments (24C) disposed between the forward segment and the aft segment. The middle segments comprise radially elongate ceramic matrix composite material plates. In one embodiment, the gas path portion comprises an airfoil for a turbine blade. In another embodiment, the gas path portion comprises a removable platform for a turbine blade. In another embodiment, the gas path portion comprises an airfoil for a turbine vane.
-
公开(公告)号：EP2532457A2
公开(公告)日：2012-12-12
申请号：EP12170605.5
申请日：2012-06-01
IPC分类号： B22C9/10
CPC分类号： B22C9/103
摘要： A hybrid core assembly (46) for a casting process includes a ceramic core portion (48), a refractory metal core portion (50) and a plate (62) positioned between the ceramic core portion (48) and the refractory metal core portion (50). The ceramic core portion (48) includes a trough (56). A portion of the refractory metal core portion (50) is received in the trough (56).
-
86.发明公开A turbine vane segment, the corresponding nozzle assembly and method of cooling this vane 有权一种涡轮叶片，用于冷却叶片的相应的冷却通道布置和方法
公开(公告)号：EP2093376A3
公开(公告)日：2012-11-14
申请号：EP09250151.9
申请日：2009-01-20
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F05D2250/185 , F05D2270/301
摘要： A nozzle assembly for directing cooling fluid in a vane (10) comprising a hollow airfoil (12) containing at least two cooling chambers (34;36). The chambers (34,36) are separated by a generally radial rib (35). A metering plate mount (56) is attached to the rib (35). A metering plate (70), having at least one aperture (76) for tuning the cooling fluid flow within the airfoil (12), is adjacent the metering plate mount (56).
-
公开(公告)号：EP2101041A3
公开(公告)日：2012-10-24
申请号：EP09250679.9
申请日：2009-03-11
摘要： Cooling air manifold splash plates and gas turbine engine systems involving such splash plates are provided. In this regard, a representative cooling air manifold splash plate (124) includes: a base (140) having an aperture (144); and an air deflector (128) supported by the base, the air deflector being positioned relative to the base to receive, from the aperture, a radial flow of gas turbine engine cooling air, the air deflector being operative to redirect at least some of the air received circumferentially.
-
88.发明公开Method of forming a turbine component by brazing using a wedge member ; turbine component with such brazed wedge 有权使用楔制造涡轮部件的方法; 与这样的焊接楔vollringformiger涡轮机部件
公开(公告)号：EP2484475A2
公开(公告)日：2012-08-08
申请号：EP12154079.3
申请日：2012-02-06
CPC分类号： B23K1/0018 , B23K2201/001 , F01D9/044 , F05D2230/237 , Y10T29/49229
摘要： A turbine component is formed of at least a plurality of adjacent turbine subcomponents (30). Each turbine component (30) has a mate face (32) secured to the mate face (32) of an opposed turbine subcomponent (30). A wedge member is positioned between the mate faces (32) of the turbine subcomponents (30). A braze material (47) is between outer faces of the wedge (40) and the mate faces (32) of each of the turbine subcomponents (30).
摘要翻译： 涡轮构件中形成至少在相邻涡轮子组件（30）中的多个。 每个涡轮机部件（30）具有固定于相对的涡轮子组件（30）的配合面（32）伴侣面（32）。 楔形构件被所述涡轮机的子组件（30）的配合面（32）之间定位。 铜焊材料（47）是楔形（40），并且每个子组件的涡轮（30）的所述配合面（32）的外表面之间。
-
89.发明公开Method and casting core for forming a landing for welding a baffle inserted into an airfoil 审中-公开用于焊接的挡板用于翼型件形成颈部的方法和铸造型芯
公开(公告)号：EP2471612A1
公开(公告)日：2012-07-04
申请号：EP11195564.7
申请日：2011-12-23
CPC分类号： B22D25/02 , B22C1/00 , B22C9/04 , B22C9/10 , B22C9/103 , B22C9/108 , B22C9/18 , B22C9/24 , B22D29/001 , F01D5/188 , F01D9/041 , F01D25/12 , F05D2230/211 , F05D2230/232 , F05D2240/12 , F05D2240/126 , F05D2240/30 , F05D2260/201 , F05D2300/13
摘要： A method and casting core (310) for forming a landing (13) for welding a baffle (40) inserted into an airfoil (20) are disclosed. The baffle landing (13) of the blade or vane is formed in investment casting by the casting core (310) rather than by wax, reducing tolerances and variability in the location of the baffle (40) inserted into the cooling cavity (30) of airfoil (20) when the baffle (40) is welded to the baffle landing (13).
摘要翻译： 用于形成用于焊接在翼型件（20）插入到挡板（40）的到达（13）一种方法和铸造型芯（310）的游离缺失光盘。 叶片或轮叶的挡板着陆（13）在熔模铸造由铸造型芯（310），而不是由蜡，减少在挡板的位置公差和变异FORMED（40）插入的冷却腔（30） 翼型件（20），当所述挡板（40）被焊接到所述挡板着陆（13）。
-
公开(公告)号：EP2048328A3
公开(公告)日：2012-01-18
申请号：EP08252654.2
申请日：2008-08-08
CPC分类号： F16J15/0887 , F01D9/041 , F01D11/005 , F01D11/008 , F02C7/28 , F05D2240/80
摘要： A seal assembly includes a body (46) having two circumferential sides, a leading end, and a trailing end. At least one of the circumferential sides includes a first channel sidewall (60), a second channel sidewall (62), and a channel bottom wall that together define a seal channel for receiving a seal (79). The seal channel includes a slot that cooperates with a tab (78) on the seal to facilitate securing the seal within the seal channel.
-
-
-
-
-
-
-
-
-
搜索结果
95 条记录 (耗时 0.016 秒)
