-
公开(公告)号：US10821500B2
公开(公告)日：2020-11-03
申请号：US15960857
申请日：2018-04-24
发明人： Lane Thornton , San Quach , Steven Bruce Gautschi
摘要： In a featured embodiment, a lost core assembly includes a ceramic component having a tapered shape in a radial direction. A refractory metal component extends radially from the ceramic core component. A method of molding a gas turbine engine component is also disclosed.
-
公开(公告)号：US10273809B2
公开(公告)日：2019-04-30
申请号：US15100925
申请日：2014-12-08
发明人： Lane Thornton , Thomas N. Slavens
摘要： In one example embodiment, a blade includes an attachment region, an airfoil extending from the attachment region, and a blade cooling arrangement. The blade cooling arrangement includes at least a first feed passage disposed through the attachment region, which is connected to a first cooling passage disposed in the airfoil. A passively actuated first coolant valve is disposed in or proximate the first feed passage. A plurality of such blades can be disposed in a turbine section of an engine.
-
公开(公告)号：US20160348525A1
公开(公告)日：2016-12-01
申请号：US14726722
申请日：2015-06-01
发明人： Lane Thornton
CPC分类号： F01D11/006 , F01D5/147 , F01D5/22 , F01D5/225 , F01D11/00 , F01D11/005 , F01D11/008 , F05D2220/32 , F05D2240/55 , F05D2240/80 , F05D2260/941 , F05D2300/173 , F05D2300/174 , F05D2300/177
摘要： A platform trailing edge seal for a turbomachine airfoil (e.g., a blade or vane) assembly includes a body configured to extend into an aft portion of a mateface gap defined between a circumferentially adjacent pair of turbomachine airfoil platforms to minimize flow from entering a blade-vane cavity through the aft portion of the mateface gap.
摘要翻译： 用于涡轮机翼型件（例如，叶片或叶片）组件的平台后缘密封件包括构造成延伸到限定在周向相邻的一对涡轮机翼型平台之间的配合间隙的后部的主体，以最小化进入叶片 - 通过叶片间隙的后部分的叶片腔。
-
公开(公告)号：US20160326883A1
公开(公告)日：2016-11-10
申请号：US15107493
申请日：2015-01-02
IPC分类号： F01D5/18
摘要： A gas turbine engine component comprises an airfoil with a suction side and pressure side extending from a leading edge to a trailing edge. There are a plurality of cooling holes adjacent the leading edge, with the cooling holes having a non-circular shape, with a longer dimension and a smaller dimension. The airfoil defines a radial direction from a radially outer end to a radially inner end, and radially outer of the cooling holes spaced toward the radially outer end, which have the longer dimension extending closer to parallel to the radial direction. Radially inner cooling holes closer to the radially inner end having the longer dimension extend to be closer to perpendicular relative to the radial direction compared to the radially outer cooling holes.
摘要翻译： 燃气涡轮发动机部件包括具有从前缘延伸到后缘的吸力侧和压力侧的翼型件。 在前缘附近有多个冷却孔，冷却孔具有非圆形形状，具有较长的尺寸和较小的尺寸。 翼型件限定从径向外端到径向内端的径向方向，并且冷却孔的径向外部与径向外端间隔开，其具有更靠近平行于径向的较长尺寸。 与径向外侧冷却孔相比，更靠近具有较长尺寸的径向内端的径向内部冷却孔相对于径向更接近垂直。
-
公开(公告)号：US20160312619A1
公开(公告)日：2016-10-27
申请号：US14697329
申请日：2015-04-27
CPC分类号： F01D5/186 , F01D9/02 , F01D9/041 , F01D9/065 , F01D11/08 , F01D25/12 , F02C3/04 , F05D2220/32 , F05D2230/90 , F05D2240/12 , F05D2240/30 , F05D2240/35 , F05D2240/55 , F05D2240/81 , F05D2250/33 , F05D2250/72 , F05D2250/73 , F05D2260/202 , F05D2260/2212 , F23R3/002 , F23R2900/03042 , Y02T50/676
摘要： A film cooled component may comprise a cooling chamber and a first ligament centered about a first axis. The first ligament may be in fluid communication with the cooling chamber. A first meter may be disposed at an end of the first ligament. A first diffuser may extend from the first meter to a surface of the film cooled component. The first diffuser may comprise a first tapered sidewall oriented at an angle of between 5 degrees to 15 degrees relative to the first axis. The first diffuser may further comprise a first non-tapered sidewall oriented at an angle less than 5 degrees relative to the first axis.
摘要翻译： 薄膜冷却部件可以包括冷却室和围绕第一轴线居中的第一韧带。 第一韧带可以与冷却室流体连通。 第一米可以设置在第一韧带的末端。 第一扩散器可以从第一米延伸到薄膜冷却部件的表面。 第一扩散器可以包括相对于第一轴线以5度至15度的角度定向的第一锥形侧壁。 第一扩散器还可以包括相对于第一轴线以小于5度的角度定向的第一非锥形侧壁。
-
公开(公告)号：US20160305252A1
公开(公告)日：2016-10-20
申请号：US15100925
申请日：2014-12-08
发明人： Lane Thornton , Thomas N. Slavens
CPC分类号： F01D5/186 , F01D5/187 , F01D5/28 , F02C3/04 , F02C7/12 , F05D2220/32 , F05D2240/303 , F05D2240/304 , F05D2260/201 , F05D2260/202 , F05D2300/175 , F05D2300/505 , Y02T50/676
摘要： In one example embodiment, a blade includes an attachment region, an airfoil extending from the attachment region, and a blade cooling arrangement. The blade cooling arrangement includes at least a first feed passage disposed through the attachment region, which is connected to a first cooling passage disposed in the airfoil. A passively actuated first coolant valve is disposed in or proximate the first feed passage. A plurality of such blades can be disposed in a turbine section of an engine.
摘要翻译： 在一个示例性实施例中，叶片包括附接区域，从连接区域延伸的翼型件和叶片冷却装置。 叶片冷却装置包括至少一个穿过安装区域设置的第一进料通道，其连接到设置在翼型件中的第一冷却通道。 被动地驱动的第一冷却剂阀设置在第一进料通道中或其附近。 多个这样的叶片可以设置在发动机的涡轮机部分中。
-
公开(公告)号：US10465543B2
公开(公告)日：2019-11-05
申请号：US15810279
申请日：2017-11-13
摘要： An assembly for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil including a radial end, a first passageway having an outlet at the radial end, and a second passageway having an inlet at the radial end. The assembly further includes a cover having at least one turning cavity configured to direct fluid expelled from the outlet of the first passageway into the inlet of the second passageway.
-
公开(公告)号：US20190176228A1
公开(公告)日：2019-06-13
申请号：US16275468
申请日：2019-02-14
摘要： A gas turbine engine includes a structure that has walls that provide a cooling passage and a cooling surface. A non-ferrous obstruction is relative to the walls. The obstruction includes a portion spaced from the cooling surface to provide a gap which is configured to receive a cooling fluid.
-
公开(公告)号：US10196915B2
公开(公告)日：2019-02-05
申请号：US14726722
申请日：2015-06-01
发明人： Lane Thornton
摘要： A platform trailing edge seal for a turbomachine airfoil (e.g., a blade or vane) assembly includes a body configured to extend into an aft portion of a mateface gap defined between a circumferentially adjacent pair of turbomachine airfoil platforms to minimize flow from entering a blade-vane cavity through the aft portion of the mateface gap.
-
10.发明申请GAS TURBINE ENGINE COMPONENT WITH SEPARATION RIB FOR COOLING PASSAGES 审中-公开具有用于冷却通道的分离RIB的气体涡轮发动机部件公开(公告)号：US20160326909A1
公开(公告)日：2016-11-10
申请号：US15111517
申请日：2015-01-21
发明人： Charles Thistle , Lane Thornton
CPC分类号： F01D25/12 , F01D5/187 , F01D11/08 , F01D11/24 , F02C3/10 , F02C7/12 , F02K3/06 , F05D2240/11 , F05D2250/11 , F05D2250/121 , F05D2250/22 , F05D2250/23 , F05D2250/25 , F05D2260/2212 , F05D2260/2214 , Y02T50/676
摘要： A gas turbine engine component comprises a body extending between two ends and having at least two cooling passages. The body has a first wall and second wall. At least two cooling passages include a first passage that is closer to the first wall than is a second of the passages at upstream locations along a flow path. The second passage has upstream locations that are closer to the second wall than are upstream portions of the first passage. The first and second passages cross along a length of the flow path such that downstream portions of the second passage are closer to the first wall than are downstream portions of the first passage, and downstream portions of the first passage are closer to the second wall than are downstream portions of the second passage.
摘要翻译： 燃气涡轮发动机部件包括在两端之间延伸并且具有至少两个冷却通道的主体。 身体有第一个墙壁和第二个墙壁。 至少两个冷却通道包括比沿着流动路径的上游位置处的第二通道更靠近第一壁的第一通道。 第二通道具有比第一通道的上游部分更靠近第二壁的上游位置。 所述第一通道和所述第二通道沿所述流动路径的长度交叉，使得所述第二通道的下游部分比所述第一通道的下游部分更靠近所述第一壁，并且所述第一通道的下游部分比所述第一通道的下游部分更靠近所述第二壁 是第二通道的下游部分。
-
-
-
-
-
-
-
-
-
搜索结果
35 条记录 (耗时 0.018 秒)
