专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

31. 发明申请

US20130280091A1 GAS TURBINE ENGINE AIRFOIL IMPINGEMENT COOLING 有权
标题翻译：气体涡轮发动机空气流动冷却
公开(公告)号：US20130280091A1
公开(公告)日：2013-10-24
申请号：US13454197
申请日：2012-04-24
申请人： Tracy A. Propheter-Hinckley , Mark F. Zelesky , Dominic J. Mongillo, JR. , Matthew A. Devore , Steven Bruce Gautschi , Benjamin T. Fisk
发明人： Tracy A. Propheter-Hinckley , Mark F. Zelesky , Dominic J. Mongillo, JR. , Matthew A. Devore , Steven Bruce Gautschi , Benjamin T. Fisk
IPC分类号： F01D5/18 , B05D1/36
CPC分类号： B22C9/04 , B22C9/10 , B22C9/24 , B22F3/1017 , B22F3/105 , B22F3/1055 , B22F5/04 , B23K15/0086 , B33Y10/00 , B33Y80/00 , C21D9/0068 , F01D5/187 , F05D2240/303 , F05D2260/201 , F05D2260/202 , F05D2260/205 , Y02P10/292 , Y02P10/295
摘要： An airfoil has a body that includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. A leading edge wall provides the exterior airfoil surface at the leading edge. An impingement wall is integrally formed with the leading edge wall to provide an impingement cavity between the leading edge wall and the impingement wall and multiple impingement holes are provided in the impingement wall. The impingement holes are spaced laterally across the impingement wall. A method of manufacturing an airfoil includes the steps of depositing multiple layers of powdered metal onto one another, joining the layers to one another with reference to CAD data relating to a particular cross-section of an airfoil, and producing the airfoil.
摘要翻译：机翼具有主体，其包括通过间隔开的压力和吸力侧连接的前缘和后缘以提供外部翼面表面。前缘壁在前缘提供外部翼型表面。冲击壁与前缘壁一体地形成，以在前缘壁和冲击壁之间提供冲击腔，并且多个冲击孔设置在冲击壁中。冲击孔横向穿过冲击壁间隔开。一种制造翼型件的方法包括以下步骤：将多层粉末金属沉积到彼此上，参考与翼型的特定横截面相关的CAD数据并将翼片相互连接，并产生翼型件。

32. 发明申请

US20130205791A1 COOLING HOLE WITH CURVED METERING SECTION 有权
标题翻译：冷凝孔与弯曲计量段
公开(公告)号：US20130205791A1
公开(公告)日：2013-08-15
申请号：US13544125
申请日：2012-07-09
申请人： Dominic J. Mongillo, JR. , Matthew S. Gleiner
发明人： Dominic J. Mongillo, JR. , Matthew S. Gleiner
IPC分类号： F02C7/18 , F01D25/12 , F04D29/58 , F01D5/18
CPC分类号： F01D25/12 , F01D5/186 , F01D9/065 , F05D2240/35 , F05D2240/81 , F05D2250/71 , F05D2260/202 , F23R2900/03042 , Y02T50/676
摘要： A gas turbine engine component includes a cooling hole. The component includes a first wall having an inlet, a second wall having an outlet and a metering section extending downstream from the inlet and having a substantially convex first surface and a substantially concave second surface. The component also includes a diffusing section extending from the metering section to the outlet. A gas turbine engine wall includes first and second surfaces and a cooling hole extending between an inlet at the first surface and an outlet at the second surface. The cooling hole includes a metering section commencing at the inlet and a diffusing section in communication with the metering section and terminating at the outlet. The metering section includes a top portion having a first arcuate surface and a bottom portion having a second arcuate surface. The first and second arcuate surfaces have arcs extending in substantially similar directions.
摘要翻译：燃气涡轮发动机部件包括冷却孔。该部件包括具有入口的第一壁，具有出口的第二壁和从入口的下游延伸并具有基本上凸起的第一表面和基本上凹入的第二表面的计量部分。该部件还包括从计量部分延伸到出口的扩散部分。燃气涡轮发动机壁包括第一和第二表面以及在第一表面处的入口与第二表面的出口之间延伸的冷却孔。冷却孔包括从入口开始的计量部分和与计量部分连通并终止于出口的扩散部分。计量部分包括具有第一弧形表面的顶部部分和具有第二弓形表面的底部部分。第一和第二弧形表面具有基本上相似的方向延伸的弧。

33. 发明授权

US06939107B2 Spanwisely variable density pedestal array 有权
标题翻译：跨度可变密度基座阵列
公开(公告)号：US06939107B2
公开(公告)日：2005-09-06
申请号：US10717806
申请日：2003-11-19
申请人： Dominic J. Mongillo, Jr. , Young H. Chon
发明人： Dominic J. Mongillo, Jr. , Young H. Chon
IPC分类号： F01D9/02 , F01D5/18 , F02C7/18 , F01D25/12
CPC分类号： F01D5/187 , F05D2260/2212
摘要： A turbine engine component, such as a blade or vane, has a system for cooling a trailing edge portion thereof. The system includes a plurality of rows of pedestals which vary in density along a span of the component. In a preferred embodiment of the present invention, the number of rows of pedestals increases as one moves along the span of the component from an inner diameter region to an outer diameter region.
摘要翻译：诸如叶片或叶片的涡轮发动机部件具有用于冷却其后缘部分的系统。该系统包括沿着部件的跨度而沿密度变化的多排基座。在本发明的优选实施例中，随着沿着部件的跨度从内径区域到外径区域移动，基座的行数增加。

34. 发明授权

US06234754B1 Coolable airfoil structure 有权
标题翻译：冷却翼型结构
公开(公告)号：US06234754B1
公开(公告)日：2001-05-22
申请号：US09371138
申请日：1999-08-09
申请人： Mark F. Zelesky , Dominic J. Mongillo, Jr.
发明人： Mark F. Zelesky , Dominic J. Mongillo, Jr.
IPC分类号： F01D518
CPC分类号： F01D5/187 , B22C9/10 , F05D2230/21 , F05D2260/2212 , F05D2260/2214 , F05D2260/22141 , Y02T50/673 , Y02T50/676
摘要： A coolable airfoil structure having internal heat transfer features through which cooling air is flowed under operative conditions is disclosed. Various construction details and features are developed which affect the castability and core strength during manufacture and strength and cooling effectiveness of the airfoil after manufacture. In one particular embodiment, the airfoil has a plurality of heat transfer members disposed in the rearmost section of the trailing edge region which comprises a single impingement rib, a single row of pedestals and a single row of chordwisely extending flow dividers.
摘要翻译：公开了一种具有内部传热特征的可冷却翼型结构，冷却空气在操作条件下流过。开发了各种构造细节和特征，其影响制造过程中的铸造性和芯强度，以及制造后翼型的强度和冷却效果。在一个具体实施例中，翼型件具有多个传热构件，其布置在后缘区域的最后部分中，其包括单个冲击肋，单排基座和单排弦向延伸分流器。

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