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1. 发明申请

US20130251539A1 TRAILING EDGE OR TIP FLAG ANTIFLOW SEPARATION 有权
标题翻译：跟踪边缘或提示标签防流动分离
公开(公告)号：US20130251539A1
公开(公告)日：2013-09-26
申请号：US13424765
申请日：2012-03-20
申请人： Steven Bruce Gautschi , Brandon W. Spangler , San Quach , Dominic J. Mongillo, JR.
发明人： Steven Bruce Gautschi , Brandon W. Spangler , San Quach , Dominic J. Mongillo, JR.
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/122 , F05D2240/125 , F05D2240/304 , F05D2240/307 , F05D2250/314 , F05D2250/324 , F05D2260/22141 , Y02T50/676
摘要： An airfoil includes a leading edge, a trailing edge region, a suction surface, a pressure surface, a cooling passageway, and a column of flow separators. The suction surface and the pressure surface both extend axially between the leading edge and the trailing edge region, as well as radially from a root section of the airfoil to a tip section of the airfoil to define a central cavity of the airfoil. The cooling passageway is located within the central cavity at the trailing edge region. The column of flow separators is located in the cooling passageway adjacent the trailing edge and includes a first flow separator having a first longitudinal axis and a second flow separator having a second longitudinal axis. The first longitudinal axis is offset at an angle with respect to the first longitudinal axis.
摘要翻译：翼型件包括前缘，后缘区域，吸力表面，压力表面，冷却通道和流动隔板柱。吸力表面和压力表面都在前缘和后缘区域之间轴向延伸，并且从翼型的根部径向延伸到翼型的尖端部分，以限定翼型的中心腔。冷却通道位于后缘区域的中心腔内。流动分离器柱位于靠近后缘的冷却通道中，并且包括具有第一纵向轴线的第一流动分离器和具有第二纵向轴线的第二流动分离器。第一纵向轴线相对于第一纵向轴线以一定角度偏移。

2. 发明授权

US09328617B2 Trailing edge or tip flag antiflow separation 有权
标题翻译：后缘或尖端标志防潮隔离
公开(公告)号：US09328617B2
公开(公告)日：2016-05-03
申请号：US13424765
申请日：2012-03-20
申请人： Steven Bruce Gautschi , Brandon W. Spangler , San Quach , Dominic J. Mongillo, Jr.
发明人： Steven Bruce Gautschi , Brandon W. Spangler , San Quach , Dominic J. Mongillo, Jr.
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/122 , F05D2240/125 , F05D2240/304 , F05D2240/307 , F05D2250/314 , F05D2250/324 , F05D2260/22141 , Y02T50/676
摘要： An airfoil includes a leading edge, a trailing edge region, a suction surface, a pressure surface, a cooling passageway, and a column of flow separators. The suction surface and the pressure surface both extend axially between the leading edge and the trailing edge region, as well as radially from a root section of the airfoil to a tip section of the airfoil to define a central cavity of the airfoil. The cooling passageway is located within the central cavity at the trailing edge region. The column of flow separators is located in the cooling passageway adjacent the trailing edge and includes a first flow separator having a first longitudinal axis and a second flow separator having a second longitudinal axis. The first longitudinal axis is offset at an angle with respect to the first longitudinal axis.
摘要翻译：翼型件包括前缘，后缘区域，吸力表面，压力表面，冷却通道和流动隔板柱。吸力表面和压力表面都在前缘和后缘区域之间轴向延伸，并且从翼型的根部径向延伸到翼型的尖端部分，以限定翼型的中心腔。冷却通道位于后缘区域的中心腔内。流动分离器柱位于靠近后缘的冷却通道中，并且包括具有第一纵向轴线的第一流动分离器和具有第二纵向轴线的第二流动分离器。第一纵向轴线相对于第一纵向轴线以一定角度偏移。

3. 发明授权

US09228442B2 Turbine airfoil tip shelf and squealer pocket cooling 有权
标题翻译：涡轮机翼尖架和尖叫口袋冷却
公开(公告)号：US09228442B2
公开(公告)日：2016-01-05
申请号：US13440297
申请日：2012-04-05
申请人： Dominic J. Mongillo, Jr. , Steven Bruce Gautschi , San Quach
发明人： Dominic J. Mongillo, Jr. , Steven Bruce Gautschi , San Quach
IPC分类号： F01D5/08 , F01D5/20
CPC分类号： F01D5/20 , Y02T50/673
摘要： An airfoil comprises leading and trailing edges with pressure and suction surfaces defining a chord length therebetween. The pressure and suction surfaces extend from a root section of the airfoil to a tip section. A tip shelf is formed along the tip section between the pressure surface and a tip shelf wall spaced between the pressure surface and the suction surface. A squealer pocket is formed along the tip section between the tip shelf wall and a squealer tip wall extending from the suction surface. The tip shelf extends from within 10% of the cord length measured from the leading edge to within 10% of the chord length measured from the trailing edge. The squealer pocket extends from within 10% of the chord length measured from the leading edge to terminate between 10% and 25% of the chord length measured from the trailing edge.
摘要翻译：机翼包括前缘和后缘，其中压力和吸力表面之间限定弦长。压力和吸力表面从机翼的根部部分延伸到尖端部分。在压力表面和与压力表面和抽吸表面间隔开的尖端搁板壁之间的尖端部分形成有尖端架。沿尖端搁架壁和从抽吸面延伸的尖叫尖端壁之间的尖端部分形成一个尖叫口袋。尖端架从从前缘测量的绳索长度的10％范围内延伸到从后缘测量的弦长的10％以内。尖叫口袋从前缘测量的弦长的10％以内延伸，终止于从后缘测量的弦长的10％至25％之间。

4. 发明申请

US20130266454A1 TURBINE AIRFOIL TIP SHELF AND SQUEALER POCKET COOLING 有权
标题翻译： TURBINE AIRFOIL TIP SHELF和SQUEALER POCKET COOLING
公开(公告)号：US20130266454A1
公开(公告)日：2013-10-10
申请号：US13440297
申请日：2012-04-05
申请人： Dominic J. Mongillo, JR. , Steven Bruce Gautschi , San Quach
发明人： Dominic J. Mongillo, JR. , Steven Bruce Gautschi , San Quach
IPC分类号： F01D5/18
CPC分类号： F01D5/20 , Y02T50/673
摘要： An airfoil comprises leading and trailing edges with pressure and suction surfaces defining a chord length therebetween. The pressure and suction surfaces extend from a root section of the airfoil to a tip section. A tip shelf is formed along the tip section between the pressure surface and a tip shelf wall spaced between the pressure surface and the suction surface. A squealer pocket is formed along the tip section between the tip shelf wall and a squealer tip wall extending from the suction surface. The tip shelf extends from within 10% of the cord length measured from the leading edge to within 10% of the chord length measured from the trailing edge. The squealer pocket extends from within 10% of the chord length measured from the leading edge to terminate between 10% and 25% of the chord length measured from the trailing edge.
摘要翻译：机翼包括前缘和后缘，其中压力和吸力表面之间限定弦长。压力和吸力表面从翼型的根部部分延伸到尖端部分。在压力表面和与压力表面和抽吸表面间隔开的尖端搁板壁之间的尖端部分形成有尖端架。沿尖端搁架壁和从抽吸面延伸的尖叫尖端壁之间的尖端部分形成一个尖叫口袋。尖端架从从前缘测量的绳索长度的10％范围内延伸到从后缘测量的弦长的10％以内。尖叫口袋从前缘测量的弦长的10％以内延伸，终止于从后缘测量的弦长的10％至25％之间。

5. 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。

6. 发明授权

US09296039B2 Gas turbine engine airfoil impingement cooling 有权
标题翻译：燃气涡轮发动机翼型冲击冷却
公开(公告)号：US09296039B2
公开(公告)日：2016-03-29
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 , B22C9/04 , B22C9/10 , B22F5/04 , B22F3/105
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。

7. 发明申请

US20130280081A1 GAS TURBINE ENGINE AIRFOIL GEOMETRIES AND CORES FOR MANUFACTURING PROCESS 审中-公开
标题翻译：气体涡轮发动机空气动力学几何和制造过程的方法
公开(公告)号：US20130280081A1
公开(公告)日：2013-10-24
申请号：US13454221
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： F03B3/12 , B22F3/02
CPC分类号： F01D5/187 , B22C9/10 , B22C9/101 , B22C9/24 , B22F3/1055 , B22F5/10 , B33Y10/00 , B33Y80/00 , C22C28/00 , F05D2220/32 , F05D2230/21 , F05D2230/31 , F05D2260/20 , F05D2300/131 , Y02P10/292 , Y02P10/295
摘要： A core for an airfoil includes a refractory metal structure having a variable thickness. An airfoil includes a body having leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface defined by a perimeter wall. An interior wall is arranged interiorly and adjacent to the perimeter wall to provide a cooling passage there between. A cooling passage with first and second portions is tapered and respectively has first and second thicknesses. The first thickness is greater than the second thickness, and the second thickness is less than 0.060 inch (1.52 mm). A method of manufacturing a refractory metal core includes 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 a refractory metal core, and producing the core having a variable thickness.
摘要翻译：用于翼型的芯部包括具有可变厚度的难熔金属结构。翼型件包括主体，其具有通过间隔开的压力和吸力侧连接的前缘和后缘，以提供由周边壁限定的外部翼型表面。内壁布置在周边壁的内部和附近，以在其间提供冷却通道。具有第一和第二部分的冷却通道是锥形的并且分别具有第一和第二厚度。第一厚度大于第二厚度，第二厚度小于0.060英寸（1.52mm）。制造难熔金属芯的方法包括将多层粉末状金属彼此沉积，参照与难熔金属芯的特定横截面相关的CAD数据将层彼此接合，并且制造具有可变的厚度。

8. 发明申请

US20140033736A1 GAS TURBINE ENGINE COMPONENT COOLING CIRCUIT 审中-公开
标题翻译：气体涡轮发动机组件冷却电路
公开(公告)号：US20140033736A1
公开(公告)日：2014-02-06
申请号：US13565877
申请日：2012-08-03
申请人： Tracy A. Propheter-Hinckley , Steven Bruce Gautschi , San Quach
发明人： Tracy A. Propheter-Hinckley , Steven Bruce Gautschi , San Quach
IPC分类号： F01D25/12 , F01D9/02 , F02C6/00 , B23P17/00 , F28F7/00 , F01D5/18 , F01D11/08
CPC分类号： F01D5/186 , B22C9/04 , B22C9/10 , B23P15/02 , F05D2230/14 , F05D2230/211 , F05D2260/204 , F28F7/00 , Y10T29/49234
摘要： A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a body portion, a cooling circuit disposed within the body portion and including at least a first cavity and a microcircuit in fluid communication with the first cavity. A plunged hole intersects at least a portion of the microcircuit.
摘要翻译：根据本公开的示例性方面的用于燃气涡轮发动机的部件包括主体部分，设置在主体部分内的冷却回路，并且至少包括第一腔体和与第一腔体流体连通的微电路腔。突出的孔与微电路的至少一部分相交。

9. 发明授权

US10100646B2 Gas turbine engine component cooling circuit 有权
公开(公告)号：US10100646B2
公开(公告)日：2018-10-16
申请号：US13565877
申请日：2012-08-03
申请人： Tracy A. Propheter-Hinckley , Steven Bruce Gautschi , San Quach
发明人： Tracy A. Propheter-Hinckley , Steven Bruce Gautschi , San Quach
IPC分类号： F01D5/18 , B22C9/04 , B22C9/10 , F28F7/00 , B23P15/02
摘要： A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a body portion, a cooling circuit disposed within the body portion and including at least a first cavity and a microcircuit in fluid communication with the first cavity. A plunged hole intersects at least a portion of the microcircuit.

10. 发明授权

US09482098B2 Convective shielding cooling hole pattern 有权
标题翻译：对流屏蔽冷却孔图案
公开(公告)号：US09482098B2
公开(公告)日：2016-11-01
申请号：US13469647
申请日：2012-05-11
申请人： San Quach , Steven Bruce Gautschi , Christina E. Botnick
发明人： San Quach , Steven Bruce Gautschi , Christina E. Botnick
IPC分类号： F01D5/14 , F01D5/18
CPC分类号： F01D5/145 , F01D5/187 , F05D2240/81 , F05D2250/23 , F05D2250/231 , F05D2250/232 , F05D2250/324 , F05D2260/201
摘要： The cooling system for a turbine may include a plurality of platform cooling openings positioned in a platform of the turbine airfoil. In particular, the first set of cooling openings may create a first cooling path and a second set of cooling openings may be placed in the path of the first cooling path where the first cooling flow will cool the second set of cooling openings.
摘要翻译：涡轮机的冷却系统可以包括定位在涡轮机翼型平台中的多个平台冷却开口。特别地，第一组冷却开口可以产生第一冷却路径，并且第二组冷却开口可以放置在第一冷却路径的路径中，其中第一冷却流将冷却第二组冷却开口。

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