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

US08753083B2 Curved cooling passages for a turbine component 有权
标题翻译：用于涡轮机部件的弯曲冷却通道
公开(公告)号：US08753083B2
公开(公告)日：2014-06-17
申请号：US13006914
申请日：2011-01-14
申请人： Benjamin Paul Lacy , Brian Peter Arness , Victor John Morgan
发明人： Benjamin Paul Lacy , Brian Peter Arness , Victor John Morgan
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D9/02 , F05D2250/71 , F05D2260/22141 , Y02T50/673 , Y02T50/676
摘要： A turbine component having a curved cooling passage is disclosed. The turbine component may generally comprise an airfoil having a base and a tip disposed opposite the base. The airfoil may further include a pressure side and a suction side extending between a leading edge and a trailing edge. An airfoil cooling circuit may be at least partially disposed within the airfoil and may be configured to direct a cooling medium through the airfoil. The curved cooling passage may generally be in flow communication with the airfoil cooling circuit such that the cooling medium flowing through the airfoil cooling circuit may be directed into the cooling passage. Additionally, the curved cooling passage may generally extend lengthwise within the airfoil between the leading and trialing edges along at least a portion of one of the pressure side and the suction side of the airfoil.
摘要翻译：公开了一种具有弯曲冷却通道的涡轮机部件。涡轮机部件通常可以包括具有基部和与基部相对设置的尖端的翼型件。翼型件还可以包括在前缘和后缘之间延伸的压力侧和吸力侧。翼型件冷却回路可以至少部分地设置在翼型内，并且可以被配置成引导冷却介质通过翼型件。弯曲的冷却通道通常可以与翼型件冷却回路流动连通，使得流过翼型件冷却回路的冷却介质可以被引导到冷却通道中。此外，弯曲的冷却通道可以沿翼型的压力侧和吸力侧中的一个的至少一部分大体上在翼型之间在引导和试验边缘之间的翼型内延伸。

2. 发明授权

US08231128B2 Integral seal and sealant packaging 失效
标题翻译：整体密封和密封剂包装
公开(公告)号：US08231128B2
公开(公告)日：2012-07-31
申请号：US12752380
申请日：2010-04-01
申请人： Victor John Morgan , Benjamin Paul Lacy
发明人： Victor John Morgan , Benjamin Paul Lacy
IPC分类号： F16J15/12 , B32B9/00 , B32B33/07
CPC分类号： F16J15/065 , F01D11/003 , F05D2300/601 , F16J15/104 , F16J15/14 , Y10T29/49297 , Y10T428/14 , Y10T428/1419 , Y10T428/1438
摘要： An integral seal and sealant package includes a prefabricated seal element having multiple surfaces; a high-temperature sealant composition engaged with one or more of the multiple surfaces; and a backer material enclosing the prefabricated seal element and the high-temperature sealant composition. The backer material has composition permitting the backer material to be installed with the seal element and the sealant composition between adjacent components to be sealed.
摘要翻译：整体密封和密封剂包装包括具有多个表面的预制密封元件; 与多个表面中的一个或多个接合的高温密封剂组合物; 以及封装预制密封元件和高温密封剂组合物的支撑材料。背衬材料具有允许背衬材料安装密封元件并且相邻部件之间的密封剂组合物被密封的组成。

3. 发明申请

US20120183412A1 CURVED COOLING PASSAGES FOR A TURBINE COMPONENT 有权
标题翻译：涡轮组件的弯道冷却通道
公开(公告)号：US20120183412A1
公开(公告)日：2012-07-19
申请号：US13006914
申请日：2011-01-14
申请人： Benjamin Paul Lacy , Brian Peter Arness , Victor John Morgan
发明人： Benjamin Paul Lacy , Brian Peter Arness , Victor John Morgan
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D9/02 , F05D2250/71 , F05D2260/22141 , Y02T50/673 , Y02T50/676
摘要： A turbine component having a curved cooling passage is disclosed. The turbine component may generally comprise an airfoil having a base and a tip disposed opposite the base. The airfoil may further include a pressure side and a suction side extending between a leading edge and a trailing edge. An airfoil cooling circuit may be at least partially disposed within the airfoil and may be configured to direct a cooling medium through the airfoil. The curved cooling passage may generally be in flow communication with the airfoil cooling circuit such that the cooling medium flowing through the airfoil cooling circuit may be directed into the cooling passage. Additionally, the curved cooling passage may generally extend lengthwise within the airfoil between the leading and trialing edges along at least a portion of one of the pressure side and the suction side of the airfoil.
摘要翻译：公开了一种具有弯曲冷却通道的涡轮机部件。涡轮机部件通常可以包括具有基部和与基部相对设置的尖端的翼型件。翼型件还可以包括在前缘和后缘之间延伸的压力侧和吸力侧。翼型件冷却回路可以至少部分地设置在翼型内，并且可以被配置成引导冷却介质通过翼型件。弯曲的冷却通道通常可以与翼型件冷却回路流动连通，使得流过翼型件冷却回路的冷却介质可以被引导到冷却通道中。此外，弯曲的冷却通道可以沿翼型的压力侧和吸力侧中的一个的至少一部分大体上在翼型之间在引导和试验边缘之间的翼型内延伸。

4. 发明申请

US20100072710A1 Gas Turbine Seal 审中-公开
标题翻译：燃气轮机密封
公开(公告)号：US20100072710A1
公开(公告)日：2010-03-25
申请号：US12234989
申请日：2008-09-22
申请人： Victor John Morgan , Kevin Thomas McGovern , David Richard Johns
发明人： Victor John Morgan , Kevin Thomas McGovern , David Richard Johns
IPC分类号： F16J15/16
CPC分类号： F16J15/0887 , F01D9/042 , F01D11/005 , F05D2220/3212
摘要： A seal is provided for sealing two adjacent components of a gas turbine engine. The seal has first and second sealing surfaces that operate to seal the adjacent components to create an effective seal therebetween. Additionally, the seal has a first end and a second end, with the second end having a necked down portion, which is configured to internally engage the first end in a sliding, overlapping manner.
摘要翻译：提供用于密封燃气涡轮发动机的两个相邻部件的密封件。密封件具有第一和第二密封表面，其操作以密封相邻部件以在其间产生有效的密封。此外，密封件具有第一端和第二端，其中第二端具有颈缩部分，其被构造成以滑动重叠的方式内部接合第一端。

5. 发明授权

US09528382B2 Airfoil heat shield 有权
标题翻译：翼型隔热罩
公开(公告)号：US09528382B2
公开(公告)日：2016-12-27
申请号：US12615674
申请日：2009-11-10
申请人： Victor John Morgan , David Richard Johns
发明人： Victor John Morgan , David Richard Johns
IPC分类号： F01D25/12 , F01D5/28 , F01D5/14
CPC分类号： F01D5/288 , F01D5/147 , F05D2230/80 , F05D2230/90 , F05D2260/202 , F05D2260/36
摘要： Exemplary embodiments include a multi-layer, modular and replaceable heat shield for gas turbines. The heat shield apparatus can include a base layer adjacent the airfoil and a thermal layer coupled to the base layer, wherein the base layer and the thermal layer match a contour of the airfoil.
摘要翻译：示例性实施例包括用于燃气轮机的多层，模块化和可更换的热屏蔽。隔热装置可以包括邻近翼型的基层和耦合到基层的热层，其中基层和热层匹配翼型的轮廓。

6. 发明授权

US08814526B2 Turbine nozzle airfoil profile 有权
公开(公告)号：US08814526B2
公开(公告)日：2014-08-26
申请号：US13304732
申请日：2011-11-28
申请人： Alexander Stein , Victor John Morgan , Thomas James Brunt , George Andrew Gergely
发明人： Alexander Stein , Victor John Morgan , Thomas James Brunt , George Andrew Gergely
IPC分类号： F01D5/14
CPC分类号： F01D9/02 , F05D2250/74
摘要： A turbine nozzle is provided including a nozzle airfoil having an airfoil shape, the nozzle airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.

7. 发明申请

US20130177411A1 SYSTEM AND METHOD FOR SEALING A GAS PATH IN A TURBINE 审中-公开
标题翻译：用于密封涡轮气体路径的系统和方法
公开(公告)号：US20130177411A1
公开(公告)日：2013-07-11
申请号：US13343935
申请日：2012-01-05
申请人： David Wayne Weber , Victor John Morgan
发明人： David Wayne Weber , Victor John Morgan
IPC分类号： F01D9/04 , B23P15/00
CPC分类号： F01D11/005 , F01D11/001 , F01D11/003 , F01D25/246 , F05D2300/211 , Y10T29/49323
摘要： A system for sealing a gas path in a turbine includes a stator ring segment, a shroud segment adjacent to the stator ring segment, and a first load-bearing surface between the stator ring segment and the shroud segment. A first non-metallic gasket is in contact with the first load-bearing surface between the stator ring segment and the shroud segment. A method for sealing a gas path in a turbine includes placing a non-metallic gasket between any two of a stator ring segment, a shroud segment, and a casing.
摘要翻译：用于密封涡轮机中的气体路径的系统包括定子环段，与定子环段相邻的护罩段，以及定子环段和护罩区段之间的第一承载表面。第一非金属垫圈与定子环段和护罩段之间的第一承载表面接触。用于密封涡轮机中的气体路径的方法包括将非金属垫圈放置在定子环段，护罩段和壳体中的任何两个之间。

8. 发明申请

US20130247580A1 SYSTEM AND METHOD FOR RECIRCULATING A HOT GAS FLOWING THROUGH A GAS TURBINE 有权
标题翻译：通过气体涡轮回送热气体的系统和方法
公开(公告)号：US20130247580A1
公开(公告)日：2013-09-26
申请号：US13424414
申请日：2012-03-20
申请人： Victor John Morgan , Thomas James Brunt , Richard William Johnson
发明人： Victor John Morgan , Thomas James Brunt , Richard William Johnson
IPC分类号： F02C7/12 , F02C6/08 , F04D29/08 , F01D11/00 , F01D25/12
CPC分类号： F01D9/023 , F23R2900/00012
摘要： A system for recirculating a hot gas flowing through a gas turbine generally includes a transition piece having a downstream surface, a stationary nozzle having a leading edge surface adjacent to the transition piece downstream surface, a gap defined between the transition piece downstream surface and the stationary nozzle leading edge surface, and a projection having an inner arcuate surface radially separated from an outer surface. The projection generally extends from the stationary nozzle leading edge surface towards the transition piece downstream surface and at least partially decreases the gap. A seal extends across the gap and may be in contact with the transition piece and the stationary nozzle leading edge surface. A recirculation zone may be at least partially defined between the projection inner arcuate surface, the stationary nozzle leading edge surface and the transition piece downstream surface.
摘要翻译：用于循环流过燃气轮机的热气体的系统通常包括具有下游表面的过渡件，具有与过渡件下游表面相邻的前缘表面的固定喷嘴，在过渡件下游表面和固定件之间限定的间隙喷嘴前缘表面，以及具有与外表面径向分离的内弧形表面的突起。突出部分大体上从固定喷嘴前缘表面延伸到过渡件下游表面并且至少部分地减小间隙。密封件延伸穿过间隙并且可以与过渡件和固定的喷嘴前缘表面接触。再循环区域可以至少部分地限定在突出内弧形表面，固定喷嘴前缘表面和过渡件下游表面之间。

9. 发明申请

US20110110771A1 AIRFOIL HEAT SHIELD 有权
标题翻译：空气温度传感器
公开(公告)号：US20110110771A1
公开(公告)日：2011-05-12
申请号：US12615674
申请日：2009-11-10
申请人： Victor John Morgan , David Richard Johns
发明人： Victor John Morgan , David Richard Johns
IPC分类号： F01D25/12 , F01D5/18
CPC分类号： F01D5/288 , F01D5/147 , F05D2230/80 , F05D2230/90 , F05D2260/202 , F05D2260/36
摘要： Exemplary embodiments include a multi-layer, modular and replaceable heat shield for gas turbines. The heat shield apparatus can include a base layer adjacent the airfoil and a thermal layer coupled to the base layer, wherein the base layer and the thermal layer match a contour of the airfoil.
摘要翻译：示例性实施例包括用于燃气轮机的多层，模块化和可更换的热屏蔽。隔热装置可以包括邻近翼型的基层和耦合到基层的热层，其中基层和热层匹配翼型的轮廓。

10. 发明申请

US20100247300A1 REDUCING INTER-SEAL GAP IN GAS TURBINE 有权
标题翻译：减少气体涡轮机中的间隙
公开(公告)号：US20100247300A1
公开(公告)日：2010-09-30
申请号：US12415081
申请日：2009-03-31
申请人： Victor John Morgan
发明人： Victor John Morgan
IPC分类号： F02C7/28
CPC分类号： F02C7/28 , F01D11/005 , F01D11/08 , F05D2240/11 , F05D2240/55
摘要： A device for reducing inter-seal gap in gas turbines. Embodiments of a gas turbine with a first arcuate component adjacent to a second arcuate component; a first slot and a connected second slot on an end of the first arcuate component; a first seal disposed into the first slot and a first adjacent slot on the second arcuate component; a second seal disposed into the second slot and a second adjacent slot on the second arcuate component, leaving a gap between the first seal and the second seal; and a connector coupled to the first seal and the second seal and substantially covering the gap between the first seal and the second seal.
摘要翻译：一种用于减少燃气轮机间间隙的装置。具有与第二弧形部件相邻的第一弓形部件的燃气轮机的实施例; 在所述第一弓形部件的端部上的第一槽和连接的第二槽; 设置在所述第一槽中的第一密封件和所述第二弓形部件上的第一相邻狭槽; 设置在所述第二槽中的第二密封件和所述第二弓形部件上的第二相邻狭槽，在所述第一密封件和所述第二密封件之间留下间隙; 以及连接到第一密封件和第二密封件并且基本上覆盖第一密封件和第二密封件之间的间隙的连接器。

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