公开(公告)号：WO2013122910A1

公开(公告)日：2013-08-22

申请号：PCT/US2013/025697

申请日：2013-02-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： XU, JinQuan ,  ZELESKY, Mark F. ,  KOHLI, Atul ,  GLEINER, Matthew S.

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

CPC classification number: F23R3/06 ,  F01D5/186 ,  F01D9/065 ,  F05D2240/81 ,  F23R2900/03042 ,  Y02T50/676

Abstract: A gas turbine engine component includes a cooling hole. The cooling hole includes an inlet, an outlet, a metering section and a diffusing section. The diffusing section extends from the metering section to the outlet and includes a first lobe diverging longitudinally and laterally from the metering section, a second lobe adjacent the first lobe and diverging longitudinally and laterally from the metering section, and a transition region having a portion that extends between the first and second lobes and an end adjacent the outlet.

Abstract translation: 燃气涡轮发动机部件包括冷却孔。 冷却孔包括入口，出口，计量部分和扩散部分。 扩散部分从计量部分延伸到出口并且包括从计量部分纵向和横向发散的第一凸角，邻近第一凸角并从计量部分纵向和横向发散的第二凸角，以及过渡区域，其具有 在第一和第二凸角之间延伸，并且邻近出口延伸。

公开(公告)号：WO2015112583A1

公开(公告)日：2015-07-30

申请号：PCT/US2015/012221

申请日：2015-01-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： XU, JinQuan

IPC: B22F7/02 ,  B22F5/04 ,  B22F3/105 ,  B33Y70/00 ,  F01D5/14 ,  F01D5/28

CPC classification number: F01D5/28 ,  B22C7/02 ,  B22C9/04 ,  B22C9/10 ,  B22D27/045 ,  B22F3/1055 ,  B22F5/007 ,  B22F5/04 ,  B22F2999/00 ,  B33Y10/00 ,  B33Y70/00 ,  B33Y80/00 ,  C30B11/00 ,  C30B29/52 ,  F01D5/18 ,  F01D5/187 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2230/50 ,  F05D2260/204 ,  F05D2300/10 ,  F05D2300/607 ,  Y02P10/292 ,  Y02P10/295

Abstract: A method is provided for manufacturing a component. This method includes additively manufacturing a crucible for casting of the component. A metal material is directionally solidified within the crucible to form a metal single crystal material. A sacrificial core is removed to reveal a metal single crystal component with internal passageways. A component is provided for a gas turbine engine that includes a metal single crystal material component with internal passageways. The metal single crystal material component was additively manufactured of a metal material concurrently with a core that forms the internal passageways. The metal material was also remelted and directionally solidified.

Abstract translation: 提供了用于制造部件的方法。 该方法包括相加地制造用于铸造组件的坩埚。 金属材料在坩埚内定向凝固，形成金属单晶材料。 去除牺牲芯以露出具有内部通道的金属单晶组件。 为包括具有内部通道的金属单晶材料部件的燃气涡轮发动机提供部件。 金属单晶材料成分与形成内部通道的芯体同时地由金属材料制成。 金属材料也被重熔并定向凝固。

公开(公告)号：WO2015017095A2

公开(公告)日：2015-02-05

申请号：PCT/US2014/045985

申请日：2014-07-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： ROACH, James, T. ,  KLING, Colin, J. ,  COOK, Grant, O., III ,  MCPHAIL, James, J. ,  BUGAJ, Shari, L. ,  O'BRIEN, James, F. ,  DEHLAVI, Majidullah ,  SMITH, Scott, A. ,  RADER, Matthew, R. ,  TURNER, Matthew, A. ,  XU, JinQuan

IPC: F01D25/00 ,  F01D25/24 ,  F02C7/20 ,  B29D22/00

CPC classification number: B64D29/00 ,  B29D22/00 ,  F01D5/02 ,  F01D25/28 ,  F02K3/04 ,  F05D2220/32 ,  F05D2230/30 ,  F05D2230/90 ,  F05D2300/10 ,  F05D2300/43 ,  F05D2300/603 ,  Y02T50/672

Abstract: Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure.

Abstract translation: 公开了用于制造轻质电镀聚合物燃气涡轮发动机部件的电镀聚合物燃气涡轮发动机部件和方法。 这些部件包括镀有一个或多个金属层的聚合物基材。 聚合物基材的聚合材料可以用可以包括碳，金属或玻璃的材料在结构上加强。 聚合物基底还可以包括多个层以形成复合铺层结构。

公开(公告)号：WO2015006433A3

公开(公告)日：2015-01-15

申请号：PCT/US2014/045928

申请日：2014-07-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： ROACH, James, T. ,  BARNETT, Barry ,  COOK III, Grant, O. ,  WATSON, Charles, R. ,  BUGAJ, Shari, L. ,  LEVASSEUR, Glenn ,  TWELVES, Wendell, V., Jr. ,  HERTEL, Christopher, J. ,  KLING, Colin, J. ,  TURNER, Matthew, A. ,  XU, JinQuan ,  CLARKSON, Steven ,  CAULFIELD, Michael

IPC: F01D25/00 ,  F01D5/28 ,  F01D5/30 ,  F01D9/02 ,  F02C7/05 ,  B32B7/02 ,  B32B27/00

Abstract: Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure.

公开(公告)号：WO2014204570A2

公开(公告)日：2014-12-24

申请号：PCT/US2014/034455

申请日：2014-04-17

Applicant: UNITED TECHNOLOGIES CORPORATION

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

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: One embodiment includes a method to regenerate a component (10). The method includes additively manufacturing a component (10) to have voids greater than 0 percent but less than approximately 15 percent in a near finished shape. The component (10) is encased in a shell mold (22). The shell mold (22) is cured. The encased component (10) is placed in a furnace and the component (10) is melted. The component (10) is solidified in the shell mold (22). The shell mold (22) is removed from the solidified component (10).

Abstract translation: 一个实施例包括再生组件（10）的方法。 该方法包括在接近完成的形状中相加地制造具有大于0％但小于约15％的空隙的部件（10）。 组件（10）被封装在壳模（22）中。 壳模（22）固化。 被封装的部件（10）被放置在炉中并且部件（10）熔化。 组分（10）在壳模（22）中固化。 从凝固组分（10）中除去壳模（22）。

公开(公告)号：WO2014204569A3

公开(公告)日：2014-12-24

申请号：PCT/US2014/034453

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: One embodiment includes a method to regenerate a component. The method includes additively manufacturing the component with at least a portion of the component in a near finished shape. The component is encased in a shell mold, the shell mold is cured, the encased component is placed in a furnace and the component is melted, the component is solidified in the shell mold, and the shell mold is removed from the solidified component.

公开(公告)号：WO2013165518A3

公开(公告)日：2013-11-07

申请号：PCT/US2013/025879

申请日：2013-02-13

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： XU, JinQuan

IPC: F02C7/18 ,  F01D5/08 ,  F01D25/12 ,  F02K3/00

Abstract: A component for a gas turbine engine includes a wall and a cooling hole. The wall has a first surface and a second surface. The second surface is exposed to hot gas flow. The cooling hole extends through the wall. The cooling hole includes a metering section extending from an inlet in the first surface of the wall to a transition, a diffusing section extending from the transition to an outlet in the second surface of the wall, a cusp on the transition, and a first longitudinal ridge extending along the diffusing section between the transition and the outlet. The first longitudinal ridge divides the diffusing section into first and second lobes.

公开(公告)号：WO2013165518A2

公开(公告)日：2013-11-07

申请号：PCT/US2013/025879

申请日：2013-02-13

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： XU, JinQuan

IPC: F02C7/18 ,  F01D5/08 ,  F01D25/12 ,  F02K3/00

CPC classification number: F01D5/186 ,  F01D9/065 ,  F05D2240/81 ,  F05D2260/202 ,  F23R3/06 ,  F23R2900/00018 ,  F23R2900/03042 ,  Y02T50/676

Abstract: A component for a gas turbine engine includes a wall and a cooling hole. The wall has a first surface and a second surface. The second surface is exposed to hot gas flow. The cooling hole extends through the wall. The cooling hole includes a metering section extending from an inlet in the first surface of the wall to a transition, a diffusing section extending from the transition to an outlet in the second surface of the wall, a cusp on the transition, and a first longitudinal ridge extending along the diffusing section between the transition and the outlet. The first longitudinal ridge divides the diffusing section into first and second lobes.

Abstract translation: 用于燃气涡轮发动机的组件包括壁和冷却孔。 墙壁具有第一表面和第二表面。 第二个表面暴露于热气流中。 散热孔延伸穿过墙壁。 冷却孔包括计量部分，该计量部分从壁的第一表面中的入口延伸到过渡部分，扩散部分从过渡部分延伸到壁的第二表面中的出口，过渡部分上的尖端以及第一纵向 脊沿着过渡部分和出口之间的扩散部分延伸。 第一纵向脊将漫射部分分成第一和第二瓣。

公开(公告)号：WO2013165517A3

公开(公告)日：2013-11-07

申请号：PCT/US2013/025876

申请日：2013-02-13

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： XU, JinQuan

IPC: F02C7/18 ,  F01D5/08 ,  F01D25/12 ,  F02K3/00

Abstract: A component for a gas turbine engine has a cooling hole extending through a gas path wall. The gas path wall has a first surface and second surface, where the second surface is exposed to hot gas flow. The cooling hole includes a passage extending through the gas path wall from an inlet in the first surface to an outlet in the second surface, and a longitudinal divider separates the passage into lobes. The passage diverges through the gas path wall, such that cross-sectional area of the cooling hole increases continuously from the inlet through the passage to the outlet.

公开(公告)号：WO2013165502A2

公开(公告)日：2013-11-07

申请号：PCT/US2013/025680

申请日：2013-02-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： KOHLI, Atul ,  GLEINER, Matthew, S. ,  ZELESKY, Mark, F. ,  XU, JinQuan

IPC: F02C7/18 ,  F01D25/12 ,  F02K3/00 ,  F01D5/08

CPC classification number: F23R3/06 ,  F01D5/186 ,  F01D9/065 ,  F05D2240/81 ,  F05D2260/202 ,  F23R2900/03042 ,  Y02T50/676

Abstract: A gas turbine engine includes a wall having first and second wall surfaces and a cooling hole extending through the wall. 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, a second lobe diverging longitudinally and laterally from the metering section, an upstream end located at the outlet, a trailing edge located at the outlet opposite the upstream end and generally opposite first and second sidewalls. Each sidewall has an edge extending along the outlet between the upstream end and the trailing edge. Each edge diverges laterally from the upstream end and converges laterally before reaching the trailing edge.

Abstract translation: 燃气涡轮发动机包括具有第一和第二壁表面的壁和延伸穿过壁的冷却孔。 冷却孔包括位于第一壁表面的入口，位于第二壁表面处的出口，从入口下游延伸的计量部分和从计量部分延伸到出口的扩散部分。 扩散部分包括从计量部分纵向和横向分叉的第一凸角，从计量部分纵向和横向分开的第二凸角，位于出口处的上游端，位于与上游端相对的出口处的后缘， 第一和第二侧壁。 每个侧壁具有沿着上游端和后缘之间的出口延伸的边缘。 每个边缘从上游端横向分开，并在到达后缘之前横向会聚。