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1. 发明申请

US20140010666A1 AIRFOIL COOLING CIRCUITS 有权
标题翻译：空气冷却电路
公开(公告)号：US20140010666A1
公开(公告)日：2014-01-09
申请号：US13529143
申请日：2012-06-21
申请人： Eric A. Hudson , Tracy A. Propheter-Hinckley , San Quach , Matthew A. Devore
发明人： Eric A. Hudson , Tracy A. Propheter-Hinckley , San Quach , Matthew A. Devore
IPC分类号： F01D5/18 , B22C9/10
CPC分类号： F01D5/187 , B22C9/10 , B22C9/108 , B22C9/24 , F01D5/186 , F05D2230/211 , F05D2260/204 , F05D2260/2212
摘要： An airfoil includes leading and trailing edges; first and second sides extending from the leading edge to the trailing edge, each side having an exterior surface; a core passage located between the first and second sides and the leading and trailing edges; and a wall structure located between the core passage and the exterior surface of the first side. The wall structure includes a plurality of cooling fluid inlets communicating with the core passage for receiving cooling fluid from the core passage, a plurality of cooling fluid outlets on the exterior surface of the first side for expelling cooling fluid and forming a cooling film along the exterior surface of the first side, and a plurality of cooling passages communicating with the plurality of cooling fluid inlets and the plurality of cooling fluid outlets. At least a portion of one cooling passage extends between adjacent cooling fluid outlets.
摘要翻译：机翼包括前缘和后缘; 第一和第二侧从前缘延伸到后缘，每个侧面具有外表面; 位于第一和第二侧之间以及前缘和后缘之间的芯通道; 以及位于所述芯通道和所述第一侧的外表面之间的壁结构。所述壁结构包括与所述芯通道连通的多个冷却流体入口，用于从所述芯通道接收冷却流体;在所述第一侧的外表面上的多个冷却流体出口，用于排出冷却流体，并沿着所述外部形成冷却膜第一侧的表面，以及与多个冷却流体入口和多个冷却流体出口连通的多个冷却通道。一个冷却通道的至少一部分在相邻的冷却流体出口之间延伸。

2. 发明授权

US09879546B2 Airfoil cooling circuits 有权
公开(公告)号：US09879546B2
公开(公告)日：2018-01-30
申请号：US13529143
申请日：2012-06-21
申请人： Eric A. Hudson , Tracy A. Propheter-Hinckley , San Quach , Matthew A. Devore
发明人： Eric A. Hudson , Tracy A. Propheter-Hinckley , San Quach , Matthew A. Devore
IPC分类号： F01D5/18 , B22C9/10 , B22C9/24
CPC分类号： F01D5/187 , B22C9/10 , B22C9/108 , B22C9/24 , F01D5/186 , F05D2230/211 , F05D2260/204 , F05D2260/2212
摘要： An airfoil includes leading and trailing edges; first and second sides extending from the leading edge to the trailing edge, each side having an exterior surface; a core passage located between the first and second sides and the leading and trailing edges; and a wall structure located between the core passage and the exterior surface of the first side. The wall structure includes a plurality of cooling fluid inlets communicating with the core passage for receiving cooling fluid from the core passage, a plurality of cooling fluid outlets on the exterior surface of the first side for expelling cooling fluid and forming a cooling film along the exterior surface of the first side, and a plurality of cooling passages communicating with the plurality of cooling fluid inlets and the plurality of cooling fluid outlets. At least a portion of one cooling passage extends between adjacent cooling fluid outlets.

3. 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。

4. 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.

5. 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。

6. 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。

7. 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。

8. 发明申请

US20130243596A1 SHARK-BITE TIP SHELF COOLING CONFIGURATION 有权
标题翻译： SHARK-BITE TIP SHELF冷却配置
公开(公告)号：US20130243596A1
公开(公告)日：2013-09-19
申请号：US13419900
申请日：2012-03-14
申请人： San Quach
发明人： San Quach
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/20 , F05D2240/305 , F05D2240/307 , F05D2250/11 , F05D2250/183 , F05D2260/202 , Y02T50/676
摘要： An airfoil includes a leading edge, a trailing edge, a suction surface, a pressure surface, and a tip shelf. The suction surface and the pressure surface both extend axially to connect the leading edge to the trailing edge. The suction surface and the pressure surface both extend radially from a root section of the airfoil a tip section of the airfoil. The tip shelf is formed along the tip section, and includes a triangular pocket.
摘要翻译：翼型件包括前缘，后缘，吸力表面，压力表面和尖端架。吸力表面和压力表面都轴向延伸，以将前缘连接到后缘。抽吸表面和压力表面都从翼型的根部径向延伸到翼型的尖端部分。尖端架沿着尖端部分形成，并且包括三角形袋。

9. 发明授权

US09091177B2 Shark-bite tip shelf cooling configuration 有权
标题翻译：鲨鱼尖架架冷却配置
公开(公告)号：US09091177B2
公开(公告)日：2015-07-28
申请号：US13419900
申请日：2012-03-14
申请人： San Quach
发明人： San Quach
IPC分类号： F01D5/18 , F01D5/20
CPC分类号： F01D5/187 , F01D5/20 , F05D2240/305 , F05D2240/307 , F05D2250/11 , F05D2250/183 , F05D2260/202 , Y02T50/676
摘要： An airfoil includes a leading edge, a trailing edge, a suction surface, a pressure surface, and a tip shelf. The suction surface and the pressure surface both extend axially to connect the leading edge to the trailing edge. The suction surface and the pressure surface both extend radially from a root section of the airfoil a tip section of the airfoil. The tip shelf is formed along the tip section, and includes a triangular pocket.
摘要翻译：翼型件包括前缘，后缘，吸力表面，压力表面和尖端架。吸力表面和压力表面都轴向延伸，以将前缘连接到后缘。抽吸表面和压力表面都从翼型的根部径向延伸到翼型的尖端部分。尖端架沿着尖端部分形成，并且包括三角形袋。

10. 发明申请

US20140064930A1 Turbine Engine Transmission Gutter 有权
标题翻译：涡轮发动机输气槽
公开(公告)号：US20140064930A1
公开(公告)日：2014-03-06
申请号：US13603252
申请日：2012-09-04
申请人： Fred NguyenLoc , San Quach
发明人： Fred NguyenLoc , San Quach
IPC分类号： F01D25/18 , F16N31/02 , F01D15/12
CPC分类号： F01D25/18 , F01D15/12 , F01D25/24 , F05D2260/602 , F16H57/0409 , F16H57/0423 , F16H57/0441 , F16H57/045 , F16N31/02
摘要： A turbine engine case defines a centerline and a gaspath within the engine case. A fan is coupled to a fan shaft. A transmission couples the shaft to the fan shaft to drive the fan and comprises a gear system. A gutter system is positioned to capture lubricating fluid slung from the gear system. The gutter system includes a gutter extending partially circumferentially about the centerline having a first circumferential end edge. An inlet channel has an inlet at the gutter first circumferential end edge and locally radially outboard of the gutter. At least one vane is spaced apart from the gutter first circumferential end edge.
摘要翻译：涡轮发动机壳体定义了发动机壳体内的中心线和气路。风扇连接到风扇轴。传动装置将轴连接到风扇轴以驱动风扇并且包括齿轮系统。排水沟系统被定位成捕获从齿轮系统悬挂的润滑液。沟槽系统包括围绕具有第一周向端边缘的中心线部分地周向延伸的沟槽。入口通道在沟槽的第一周向端边缘处具有入口，并且在沟槽中具有局部径向外侧的入口。至少一个叶片与沟槽第一周向端边缘间隔开。

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