公开(公告)号：EP2815113B1

公开(公告)日：2017-10-25

申请号：EP13785247.1

申请日：2013-02-12

Applicant: United Technologies Corporation

Inventor： XU, JinQuan ,  LEVASSEUR, Glenn

IPC: F01D5/18 ,  F01D9/06 ,  F23R3/00 ,  F23R3/06

CPC classification number: F01D5/186 ,  F01D9/065 ,  F05D2240/81 ,  F05D2260/202 ,  F23R2900/03042 ,  Y02T50/676

Abstract: A gas turbine engine component includes a wall having first and second wall surfaces, a cooling hole extending through the wall and a convexity. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally and laterally from the metering section and a second lobe adjacent the first lobe and diverging longitudinally and laterally from the metering section. The convexity is located near the outlet.

公开(公告)号：EP3032035A3

公开(公告)日：2016-10-26

申请号：EP15195125.8

申请日：2015-11-18

Applicant: United Technologies Corporation

Inventor： XU, JinQuan ,  LEWIS, Scott D.

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F01D5/187 ,  F01D9/065 ,  F05D2220/32 ,  F05D2250/25 ,  F05D2250/314 ,  F05D2260/202 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676

Abstract: An airfoil includes an airfoil section having an external wall and an internal wall (690). The internal wall (690) defines a first reference plane (663) extending in a spanwise direction and through a thickness of the internal wall (690). A first cavity (682) and a second cavity (684) are separated by the internal wall (690). A plurality of crossover passages (686) within the internal wall (690) connects the first cavity (682) to the second cavity (684). The plurality of crossover passages (686) are arranged such that the passage axis (687) of each of the plurality of cooling passages (686) intersects a surface of the second cavity (684).

公开(公告)号：EP3032035A2

公开(公告)日：2016-06-15

申请号：EP15195125.8

申请日：2015-11-18

Applicant: United Technologies Corporation

Inventor： XU, JinQuan ,  LEWIS, Scott D.

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F01D5/187 ,  F01D9/065 ,  F05D2220/32 ,  F05D2250/25 ,  F05D2250/314 ,  F05D2260/202 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676

Abstract: An airfoil includes an airfoil section having an external wall and an internal wall (690). The internal wall (690) defines a first reference plane (663) extending in a spanwise direction and through a thickness of the internal wall (690). A first cavity (682) and a second cavity (684) are separated by the internal wall (690). A plurality of crossover passages (686) within the internal wall (690) connects the first cavity (682) to the second cavity (684). The plurality of crossover passages (686) are arranged such that the passage axis (687) of each of the plurality of cooling passages (686) intersects a surface of the second cavity (684).

Abstract translation: 翼型件包括具有外壁和内壁（690）的翼型件区段。 内壁（690）限定第一参考平面（663），第一参考平面（663）沿翼展方向延伸并且穿过内壁（690）的厚度。 第一腔体（682）和第二腔体（684）由内壁（690）分开。 内壁（690）内的多个交叉通道（686）将第一腔体（682）连接至第二腔体（684）。 多个交叉通道（686）被布置为使得多个冷却通道（686）中的每一个的通道轴线（687）与第二腔体（684）的表面相交。

公开(公告)号：EP3015190A1

公开(公告)日：2016-05-04

申请号：EP15192305.9

申请日：2015-10-30

Applicant: United Technologies Corporation

Inventor： SLAVENS, Thomas N. ,  ZELESKY, Mark F. ,  XU, JinQuan ,  WAGNER, Joel H.

IPC: B22C9/10 ,  B29C67/00 ,  B22F3/105 ,  B22D29/00

CPC classification number: B22C9/24 ,  B22C1/00 ,  B22C9/02 ,  B22C9/10 ,  B22C9/106 ,  B22D29/002 ,  B22F3/1055 ,  B22F5/009 ,  B22F5/04 ,  B29C64/153 ,  B33Y10/00 ,  B33Y80/00 ,  F01D5/18 ,  F05D2230/30 ,  Y02P10/292 ,  Y02P10/295

Abstract: A casting article includes a circuit forming portion (98; 198) having an interior channel (91; 191) and an outer shell body (95; 195) that surrounds the interior channel (91; 191). An engineered failure feature (175) is formed in the outer shell body (95; 195) and is configured to increase compressibility of the casting article during a casting process.

Abstract translation: 铸造制品包括具有内部通道（91; 191）和围绕内部通道（91; 191）的外壳主体（95; 195）的电路形成部分（98; 198）。 设计的故障特征（175）形成在外壳体（95; 195）中，并且被配置成在铸造过程期间提高铸件的压缩性。

公开(公告)号：EP2986760A2

公开(公告)日：2016-02-24

申请号：EP14813859.7

申请日：2014-04-17

Applicant: United Technologies Corporation

Inventor： MCBRIEN, John ,  CASTLE, Lea, Kennard ,  SPANGLER, Brandon, W. ,  XU, JinQuan

IPC: C30B15/02 ,  C30B15/00

Abstract: A method of forming a metal single crystal turbine component (10) with internal passageways includes forming a polycrystalline turbine blade with internal passageways by additive manufacturing and filling the passageways with a core ceramic slurry. The ceramic slurry is then treated to harden the core (20) and the turbine component is encased in a ceramic shell which is treated to form a ceramic mold. The turbine component in the mold is then melted and directionally solidified in the form of a single crystal. The outer shell and inner ceramic core are then removed to form a finished single crystal turbine component with internal passageways.

Abstract translation: 形成具有内部通道的金属单晶涡轮机部件（10）的方法包括通过加成制造形成具有内部通道的多晶涡轮叶片和与核心陶瓷浆料填充所述通道。 然后将陶瓷浆液进行处理以硬化该处理，以形成一个陶瓷铸型的芯（20）和所述涡轮机部件是在陶瓷壳包裹全部。 然后在模具中的涡轮机部件被熔化并在一个单一的晶体形式定向凝固。 外壳体和内陶瓷芯然后被去除，以形成具有内部通道成品单晶涡轮机部件。

公开(公告)号：EP2986414A2

公开(公告)日：2016-02-24

申请号：EP14813832.4

申请日：2014-04-17

Applicant: United Technologies Corporation

Inventor： MCBRIEN, John ,  CASTLE, Lea, Kennard ,  SPANGLER, Brandon, W. ,  XU, JinQuan

IPC: B23K26/342 ,  B22F3/105 ,  C22C19/00

CPC classification number: F01D5/28 ,  B22C7/02 ,  B22C9/02 ,  B22C9/043 ,  B22C9/061 ,  B22C9/10 ,  B22C9/101 ,  B22C9/108 ,  B22C9/22 ,  B22C9/24 ,  B22D23/06 ,  B22D25/02 ,  B22D27/04 ,  B22D27/045 ,  B22F3/1055 ,  B22F3/11 ,  B22F3/24 ,  B22F5/04 ,  B22F2003/248 ,  B22F2998/00 ,  B22F2998/10 ,  B23K15/0006 ,  B23K15/0086 ,  B23K26/342 ,  B32B1/08 ,  B32B3/08 ,  B32B3/26 ,  B32B5/16 ,  B32B9/005 ,  B32B2250/03 ,  B32B2264/105 ,  B32B2603/00 ,  B33Y10/00 ,  B33Y80/00 ,  C30B11/00 ,  C30B29/52 ,  F01D5/147 ,  F01D5/18 ,  F01D5/187 ,  F01D5/282 ,  F01D9/02 ,  F01D9/041 ,  F01D9/065 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/31 ,  F05D2300/175 ,  F05D2300/211 ,  F05D2300/607 ,  F23R3/28 ,  Y02P10/292 ,  Y02P10/295 ,  B22F2003/242 ,  C30B11/14

Abstract: A method of forming a metal single crystal turbine component (10) with internal passageways includes forming a polycrystalline turbine blade with internal passageways by additive manufacturing and filling the passageways with a core ceramic slurry. The ceramic slurry is then treated to harden the core (20) and the turbine component is encased in a ceramic shell which is treated to form a ceramic mold. The turbine component in the mold is then melted and directionally solidified in the form of a single crystal. The outer shell and inner ceramic core are then removed to form a finished single crystal turbine component with internal passageways.

Abstract translation: 形成具有内部通道的金属单晶涡轮机部件（10）的方法包括通过添加剂制造形成具有内部通道的多晶涡轮机叶片，并用核心陶瓷浆料填充通道。 然后处理陶瓷浆料以使芯部（20）硬化，并将涡轮机部件封装在陶瓷壳体中，该陶瓷壳体被处理以形成陶瓷模具。 然后将模具中的涡轮机部件以单晶的形式熔化并定向凝固。 然后去除外壳和内陶瓷芯以形成具有内部通道的成品单晶涡轮机部件。

公开(公告)号：EP2981677A1

公开(公告)日：2016-02-10

申请号：EP14779289.9

申请日：2014-03-21

Applicant: United Technologies Corporation

Inventor： XU, JinQuan

IPC: F01D5/14 ,  F01D5/18 ,  B22F5/04 ,  B22F3/105

CPC classification number: F01D5/282 ,  B22C9/101 ,  B22C9/103 ,  B22D25/02 ,  B22F3/1055 ,  B22F5/009 ,  B22F5/04 ,  B22F5/10 ,  B33Y10/00 ,  B33Y80/00 ,  F01D5/147 ,  F01D5/18 ,  F01D5/187 ,  F01D9/041 ,  F05D2220/32 ,  F05D2230/13 ,  F05D2230/14 ,  F05D2230/21 ,  F05D2230/60 ,  F05D2240/304 ,  F05D2250/182 ,  F05D2260/202 ,  F05D2300/13 ,  F05D2300/20 ,  Y02P10/292 ,  Y02P10/295

Abstract: A method for forming an airfoil includes forming a ceramic core, forming a refractory metal core using additive manufacturing, joining the ceramic core and the refractory metal core to form a hybrid core, and casting the airfoil around the hybrid core. The ceramic core is used to define an internal cavity of the airfoil. The refractory metal core has an upstream end and a downstream end. The upstream end has a lateral thickness greater than a lateral thickness of the downstream end. The refractory metal core is used to define a trailing edge cavity within the airfoil. The trailing edge cavity is in flow communication with the internal cavity of the airfoil and trailing edge slots located on an outer surface of the airfoil near a trailing edge. This method provides for an airfoil having a trailing edge cavity of variably thickness and casting cores used for their manufacture.

公开(公告)号：EP2971667A2

公开(公告)日：2016-01-20

申请号：EP14806912.3

申请日：2014-03-13

Applicant: United Technologies Corporation

Inventor： XU, JinQuan

IPC: F02C7/12 ,  F01D25/12 ,  F01D5/18 ,  F04D29/58

CPC classification number: F01D5/186 ,  B22C9/10 ,  B22F3/1055 ,  B22F3/24 ,  B22F5/04 ,  B22F5/10 ,  B22F2005/103 ,  F05D2230/21 ,  F05D2240/81 ,  F05D2250/314 ,  F05D2260/202 ,  F05D2260/204 ,  F23R3/002 ,  F23R2900/03042 ,  Y02P10/292 ,  Y02P10/295

Abstract: A component for a gas turbine engine includes a wall that adjoins an interior cooling passage and provides an exterior surface. A film cooling hole fluidly connects the interior cooling passage and the exterior surface. The film cooling passage includes inlet and outlet passages that fluidly interconnect and adjoin one another in a misaligned non-line of sight relationship.

Abstract translation: 用于燃气涡轮发动机的部件包括邻接内部冷却通道并提供外表面的壁。 膜冷却孔流体连接内部冷却通道和外表面。 膜冷却通道包括入口通道和出口通道，其流体互连并且在不对准的非视线关系​​中彼此邻接。

公开(公告)号：EP2959108A1

公开(公告)日：2015-12-30

申请号：EP14754541.2

申请日：2014-02-13

Applicant: United Technologies Corporation

Inventor： XU, JinQuan ,  TENNEY, Frederic, Tisdall

IPC: F01D5/04 ,  F02C7/00

CPC classification number: F02C3/06 ,  F01D5/143 ,  F01D5/16 ,  F04D29/542 ,  F04D29/547 ,  F04D29/661 ,  F04D29/666 ,  F05D2260/961 ,  Y02T50/673

Abstract: A stage of a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a row of flow directing components circumferentially disposed about a centerline axis and at least one flow directing component of the row having at least one design characteristic that is dissimilar from a corresponding design characteristic of at least one other flow directing component of the row.

公开(公告)号：EP2956633A2

公开(公告)日：2015-12-23

申请号：EP14797457.0

申请日：2014-02-07

Applicant: United Technologies Corporation

Inventor： XU, JinQuan

IPC: F01D25/12 ,  F01D5/18 ,  F01D9/02 ,  F02C7/18 ,  F04D29/58

CPC classification number: F01D5/186 ,  F01D5/288 ,  F01D9/023 ,  F01D9/065 ,  F01D11/08 ,  F05D2240/81 ,  F05D2260/202 ,  F23R3/002 ,  F23R3/02 ,  F23R2900/03042

Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a wall having an internal surface, an outer skin and a cooling hole having an inlet extending from the internal surface and merging into a metering section, and a diffusion section downstream of the metering section that extends to an outlet located at the outer skin. At least two lobes are embedded within the diffusion section of the cooling hole. At least one surface of each of the at least two lobes is at least partially cylindrical.