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1. 发明授权

EP2877704B1 Turbine airfoil apparatus and corresponding manufacturing method 有权
标题翻译：其设备用于涡轮叶片轮廓，和制造方法
公开(公告)号：EP2877704B1
公开(公告)日：2016-08-17
申请号：EP13735101.1
申请日：2013-06-17
申请人： General Electric Company
发明人： MOLTER, Stephen, Mark , STEGEMILLER, Mark, Edward , PEARSON, Shawn, Michael , BRASSFIELD, Steven, Robert
IPC分类号： F01D5/18 , F01D5/22 , F01D9/04
CPC分类号： F01D5/186 , B23P15/02 , F01D5/187 , F01D5/20 , F01D5/225 , F01D9/041 , F05D2220/32 , F05D2230/10 , F05D2230/21 , F05D2240/81 , F05D2260/202 , Y10T29/49341
摘要： A turbine airfoil apparatus includes: an airfoil including a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and a trailing edge; an endwall projecting laterally outwardly from the airfoil at one spanwise end thereof, the endwall having an outer surface facing the airfoil and an opposing inner surface; a plenum defined within the endwall between the inner and outer surfaces wherein the plenum is forked in plan view, with at least two branches, each branch having a throat disposed at its upstream end; and at least one film cooling hole passing through the outer surface and communicating with the plenum.

2. 发明公开

EP2917493A1 AIR COOLED TURBINE BLADE AND CORRESPONDING METHOD OF COOLING A TURBINE BLADE 审中-公开
标题翻译： AIR冷却的涡轮叶片与相应的用于冷却涡轮叶片
公开(公告)号：EP2917493A1
公开(公告)日：2015-09-16
申请号：EP13773481.0
申请日：2013-09-19
申请人： General Electric Company
发明人： MOLTER, Stephen, Mark , BRASSFIELD, Steven, Robert , STEGEMILLER, Mark, Edward , PEARSON, Shawn, Michael
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/147 , F01D5/18 , F01D5/186 , F01D5/188 , F05D2250/185 , F05D2260/20 , F05D2260/202 , F05D2260/203 , F05D2260/2212 , Y02T50/67 , Y02T50/676
摘要： Apparatuses and methods are taught for cooling a turbine blade wherein at least one circuit is isolated along a cool suction side of the blade and the circuit turns aft toward a trailing edge.

3. 发明公开

EP2877706A1 ROTOR ASSEMBLY, CORRESPONDING GAS TURBINE ENGINE AND METHOD OF ASSEMBLING 审中-公开
标题翻译：转子设备，燃气轮机和正确的安装及其方法
公开(公告)号：EP2877706A1
公开(公告)日：2015-06-03
申请号：EP13734554.2
申请日：2013-06-14
申请人： General Electric Company
发明人： PEARSON, Shawn, Michael , BRASSFIELD, Steven, Robert , STEGEMILLER, Mark, Edward , FILIPA, Jonathan, Alan , DURSTOCK, Daniel Lee
IPC分类号： F01D5/22 , F01D11/00 , F01D5/30
CPC分类号： F01D5/30 , F01D5/22 , F01D5/3015 , F01D11/00 , F01D11/006 , F05D2240/57 , Y10T29/49321
摘要： A rotor assembly for use in a gas turbine engine having an axis of rotation includes a plurality of rotor blades. Each rotor blade includes a platform extending between opposing side faces, a shank extending radially inward from the platform, and a slot at least partially defined in each of the opposing side faces. A sealing member is configured to be inserted into each slot of a first rotor blade of the plurality of rotor blades such that at least a portion of each sealing member extends beyond one of the opposing side faces. A second rotor blade of the plurality of rotor blades is coupled adjacent the first rotor blade such that at least a portion of one sealing member is inserted into a corresponding second slot on the second rotor blade.

4. 发明公开

EP2867381A2 PROCESS FOR SELECTIVELY PRODUCING THERMAL BARRIER COATINGS ON TURBINE HARDWARE 有权
标题翻译：过程，以涡轮机部件热障涂层选择性地生产
公开(公告)号：EP2867381A2
公开(公告)日：2015-05-06
申请号：EP13725861.2
申请日：2013-05-09
申请人： General Electric Company
发明人： MANTKOWSKI, Thomas, Edward , CROW, John, Maynard , PEARSON, Shawn, Michael , MOLTER, Stephen, Mark
IPC分类号： C23C4/00 , C23C4/18 , C23C14/58 , F01D5/18 , F01D5/28
CPC分类号： F01D5/284 , B23K26/36 , C23C4/00 , C23C4/18 , F01D5/288 , F05D2300/611
摘要： A process of depositing a ceramic coating on an airfoil component and the component formed thereby is provided. The process includes depositing a bond coat on an airfoil component including on a trailing edge region thereof that defines a trailing edge of the airfoil component, within holes located within the trailing edge region and spaced apart from the trailing edge, and on lands located within the trailing edge region and between the holes. A ceramic coating is then deposited on the bond coat including on the trailing edge region of the airfoil component, within the holes located within the trailing edge region, and on the lands between the holes. The ceramic coating within the holes is selectively removed without completely removing the ceramic coating on the trailing edge region and the lands between the holes.

5. 发明公开

EP3149279A1 FASTBACK TURBULATOR 审中-公开
标题翻译： FastBack的湍流器
公开(公告)号：EP3149279A1
公开(公告)日：2017-04-05
申请号：EP15727287.3
申请日：2015-05-29
申请人： General Electric Company
发明人： BUNKER, Ronald, Scott , BRIGGS, Robert, David , PEARSON, Shawn, Michael
IPC分类号： F01D5/14 , F01D5/18 , F01D25/12 , F23R3/00 , F28F13/12
CPC分类号： F01D5/145 , F01D5/141 , F01D5/187 , F01D9/04 , F01D25/12 , F05D2220/30 , F05D2240/127 , F05D2260/2212 , F23R3/005 , F23R2900/03045 , Y02T50/673 , Y02T50/676
摘要： A structure for disrupting the flow of a fluid is provided, the structure comprising: a first lateral wall and a second lateral wall spaced apart from one another a distance across an X-axis; and a turbulator extending between the first lateral wall and the second lateral wall, the turbulator extending away from the floor. The turbulator includes a first front surface extending between the first lateral wall and the second lateral wall, a second front surface extending between the first lateral wall and the second lateral wall, a first rear surface extending between the first lateral wall and the second lateral wall, the first rear surface extending between the first front surface and the floor, and a second rear surface adjoining the first rear surface and extending between the first lateral wall and the second lateral wall, the second rear surface extending between the second front surface and the floor.
摘要翻译：提供了一种用于破坏流体流动的结构，该结构包括：第一侧壁和第二侧壁，彼此间隔开X轴的距离; 以及在所述第一侧壁和所述第二侧壁之间延伸的湍流器，所述湍流器远离所述地板延伸。所述湍流器包括在所述第一侧壁和所述第二侧壁之间延伸的第一前表面，在所述第一侧壁和所述第二侧壁之间延伸的第二前表面，在所述第一侧壁和所述第二侧壁之间延伸的第一后表面，所述第一后表面在所述第一前表面和所述地板之间延伸，以及邻接所述第一后表面并在所述第一侧壁和所述第二侧壁之间延伸的第二后表面，所述第二后表面在所述第二前表面和所述第二前表面之间延伸，地板。

6. 发明公开

EP2895696A1 ROTATING TURBINE COMPONENT WITH PREFERENTIAL HOLE ALIGNMENT 审中-公开
标题翻译： ROTIERENDE TURBINENKOMPONENTE MIT BEVORZUGTER LOCHAUSRICHTUNG
公开(公告)号：EP2895696A1
公开(公告)日：2015-07-22
申请号：EP13747744.4
申请日：2013-07-30
申请人： General Electric Company
发明人： PEARSON, Shawn, Michael , BRASSFIELD, Steven, Robert , MOLTER, Stephen, Mark , STEGEMILLER, Mark, Edward , ERTEL, Nicholas , CAMARILLO, Vanessa
IPC分类号： F01D5/14 , F01D5/18
CPC分类号： F01D5/185 , B23P15/04 , F01D5/147 , F01D5/187 , F05D2250/14 , Y10T29/49316 , Y10T29/49321
摘要： A turbine airfoil includes: a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and a trailing edge, and extending between a root and a tip; an internal rib extending between the pressure sidewall and the suction sidewall; and a crossover hole formed in the rib, the crossover hole having a noncircular cross-sectional shape with a major axis defining a maximum dimension of the cross-sectional shape; wherein the major axis of the crossover hole lies in plane with the rib and is non-parallel to an imaginary curvilinear lateral centerline which defines a locus of points lying halfway between the pressure and suction sidewalls. The orientation of the crossover holes minimizes stress concentration caused by the presence of the crossover holes.
摘要翻译：涡轮机翼片包括：在前缘和后缘处连接在一起并在根部和尖端之间延伸的凹形压力侧壁和凸形抽吸侧壁; 在所述压力侧壁和所述吸力侧壁之间延伸的内部肋; 以及形成在所述肋中的交叉孔，所述交叉孔具有非圆形横截面形状，所述横截面形状具有限定所述横截面形状的最大尺寸的长轴; 其中所述交叉孔的长轴与所述肋平行并且不平行于限定位于所述压力和抽吸侧壁之间的中心位置的虚拟曲线横向中心线。交叉孔的方向使由交叉孔的存在引起的应力集中最小化。

7. 发明公开

EP2877704A1 TURBINE AIRFOIL WITH CAST PLATFORM COOLING CIRCUIT 有权
标题翻译：其设备用于涡轮叶片轮廓，和制造方法
公开(公告)号：EP2877704A1
公开(公告)日：2015-06-03
申请号：EP13735101.1
申请日：2013-06-17
申请人： General Electric Company
发明人： MOLTER, Stephen, Mark , STEGEMILLER, Mark, Edward , PEARSON, Shawn, Michael , BRASSFIELD, Steven, Robert
IPC分类号： F01D5/18 , F01D5/22 , F01D9/04
CPC分类号： F01D5/186 , B23P15/02 , F01D5/187 , F01D5/20 , F01D5/225 , F01D9/041 , F05D2220/32 , F05D2230/10 , F05D2230/21 , F05D2240/81 , F05D2260/202 , Y10T29/49341
摘要： A turbine airfoil apparatus includes: an airfoil including a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and a trailing edge; an endwall projecting laterally outwardly from the airfoil at one spanwise end thereof, the endwall having an outer surface facing the airfoil and an opposing inner surface; a plenum defined within the endwall between the inner and outer surfaces wherein the plenum is forked in plan view, with at least two branches, each branch having a throat disposed at its upstream end; and at least one film cooling hole passing through the outer surface and communicating with the plenum.

8. 发明公开

EP2861909A2 GAS TURBINE ENGINE WALL 审中-公开
标题翻译：燃气涡轮发动机WALL
公开(公告)号：EP2861909A2
公开(公告)日：2015-04-22
申请号：EP13734549.2
申请日：2013-06-13
申请人： General Electric Company
发明人： PEARSON, Shawn, Michael , BERGHOLZ, Robert, Fredrick , SMITH, Douglas, Ray , BUCK, Frederick, Alan , MOLTER, Stephen, Mark , FELDMANN, Kevin, Robert
IPC分类号： F23R3/06
CPC分类号： F23R3/04 , F01D5/186 , F01D9/023 , F01D9/065 , F02K1/822 , F05D2240/11 , F05D2240/81 , F05D2260/202 , F23R3/002 , F23R3/06 , F23R2900/03042 , Y02T50/676
摘要： A gas turbine engine wall is provided. The wall includes an inner surface and an opposing outer surface having at least one film cooling hole defined therein. The at least one film cooling hole includes an inclined inlet bore that extends from the inner surface and a pair of channels that diverge laterally from an outlet end of the inclined inlet bore. The pair of channels have a substantially constant width and are separated by a ridge to form a boomerang cross-sectional shape.

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