公开(公告)号：EP2961962A1

公开(公告)日：2016-01-06

申请号：EP14756718.4

申请日：2014-02-25

Applicant: United Technologies Corporation

Inventor： XU, JinQuan

IPC: F02C7/12 ,  F01D25/12

Abstract: A thermal management system for a gas turbine engine includes a heat exchanger in fluid communication with a geared architecture and a heating compartment.

公开(公告)号：EP2935789A2

公开(公告)日：2015-10-28

申请号：EP13867536.8

申请日：2013-11-06

Applicant: United Technologies Corporation

Inventor： XU, JinQuan

IPC: F01D5/14 ,  F01D5/30 ,  F01D9/02

CPC classification number: F01D9/041 ,  F01D5/143 ,  Y02T50/673

Abstract: An airfoil assembly is disclosed. The airfoil assembly may comprise a series of airfoils such as vanes radially extending between an ID endwall and a substantially concentric OD endwall. The airfoils are circumferentially spaced apart and define a plurality of fluid flow passages between adjacent airfoils. The ID endwall and the OD endwall define contoured regions to optimize fluid flow through the passages. A geometric relationship between the ID endwall contoured regions and the OD endwall contoured regions assures that the throat area generally increases or decreases in the direction of fluid flow.

Abstract translation: 公开了一种翼型组件。 翼型组件可以包括一系列翼型件，例如在ID端壁和基本同心的OD端壁之间径向延伸的叶片。 翼型件沿周向间隔开并在相邻翼型件之间限定多个流体流动通道。 ID端壁和OD端壁限定轮廓区域以优化通过通道的流体流动。 ID端壁轮廓区域与OD端壁轮廓区域之间的几何关系确保喉部区域在流体流动方向上通常增加或减小。

公开(公告)号：EP2870344A2

公开(公告)日：2015-05-13

申请号：EP13855260.9

申请日：2013-07-02

Applicant: United Technologies Corporation

Inventor： XU, JinQuan ,  PIETRASZKIEWICZ, Edward, F. ,  ZELESKY, Mark, F. ,  LEVASSEUR, Glenn ,  MONGILLO, Dominic, J.

IPC: F02C7/12 ,  F01D5/18

CPC classification number: B24C1/045 ,  B23K26/0622 ,  B23K26/082 ,  B23K26/146 ,  B23K26/389 ,  B23K2201/001 ,  B26F3/004 ,  F01D5/186 ,  F01D5/288 ,  F01D9/041 ,  F05D2240/81 ,  F05D2250/52 ,  F05D2250/70 ,  F05D2260/202 ,  F23R3/06 ,  F23R2900/00018 ,  F23R2900/03042 ,  Y02T50/676

Abstract: A gas turbine engine component includes a wall with an inner face and an outer skin. A plurality of cooling air holes extend from the inner face to the outer skin. The cooling holes include an inlet merging into a metering section, and a diffusion section downstream of the metering section, and extend to an outlet at the outer skin. The diffusion section includes a plurality of lobes. A coating layer is formed on the outer skin, with at least a portion of the plurality of lobes formed within the thermal barrier coating. A method of forming such a component is also disclosed.

公开(公告)号：EP2815110A2

公开(公告)日：2014-12-24

申请号：EP13785160.6

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 ,  F01D9/041 ,  F01D9/065 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/24 ,  F05D2240/81 ,  F05D2260/202 ,  F23R2900/03042 ,  Y02T50/676

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.

Abstract translation: 用于燃气涡轮发动机的部件包括具有第一表面，暴露于热气流的第二表面和延伸穿过气体通道壁的冷却孔的气体通道壁。 冷却孔包括形成在第一表面中的入口，形成在第二表面中的出口，限定入口和出口之间的冷却孔的冷却孔表面以及沿着至少一个冷却孔表面形成的纵向脊。 纵向脊将冷却孔分成第一和第二裂片。 冷却孔通过气路壁分开，使得冷却孔的横截面积从入口通过冷却孔连续地增加到出口。

公开(公告)号：EP2815105A2

公开(公告)日：2014-12-24

申请号：EP13784655.6

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部件包括壁和冷却孔。 该壁具有第一表面和第二表面。 第二个表面暴露于热气流。 冷却孔延伸穿过墙壁。 所述冷却孔包括从所述壁的所述第一表面中的入口延伸到过渡部的计量部分，从所述过渡部延伸到所述壁的第二表面中的出口的扩散部分，所述过渡部分处的尖端，以及第一纵向 脊沿着扩散部分在过渡部分和出口之间延伸。 第一纵向脊将扩散部分分成第一和第二瓣。

公开(公告)号：EP2815103B1

公开(公告)日：2020-11-11

申请号：EP13784334.8

申请日：2013-02-12

Applicant: United Technologies Corporation

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

IPC: F01D5/18 ,  F01D9/06 ,  F23R3/00

公开(公告)号：EP2986760B1

公开(公告)日：2020-05-27

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: C30B29/52 ,  C30B11/00 ,  C30B21/00 ,  C30B21/02 ,  B22F5/04 ,  B22F3/105 ,  B22C7/02 ,  B22C9/02 ,  B22D23/06 ,  B22D25/02 ,  B22D27/04 ,  F01D5/18 ,  F01D9/04 ,  F01D9/02 ,  B33Y10/00 ,  B33Y80/00 ,  B22F3/24

公开(公告)号：EP3388633B1

公开(公告)日：2020-04-15

申请号：EP18174950.8

申请日：2015-11-18

Applicant: United Technologies Corporation

Inventor： XU, JinQuan ,  LEWIS Scott D.

IPC: F01D5/18

公开(公告)号：EP3381584A1

公开(公告)日：2018-10-03

申请号：EP18161676.4

申请日：2018-03-14

Applicant: United Technologies Corporation

Inventor： XU, JinQuan ,  LEVASSEUR, Glenn

IPC: B22C9/04 ,  B22C9/10

CPC classification number: B22C9/04 ,  B22C9/10 ,  B28B1/261 ,  B28B7/342 ,  F01D5/187 ,  F05D2230/211

Abstract: A method of forming an integral casting core (52) includes adding a disposable insert (50) to a core die (48) with the disposable insert (50) defining an inner wall in a two-circuit airfoil. A slurry is disposed into the core die (48) and fired to form an integral casting core (52). The disposable insert (50) is removed from the integral casting core (52).

公开(公告)号：EP3381583A1

公开(公告)日：2018-10-03

申请号：EP18161592.3

申请日：2018-03-13

Applicant: United Technologies Corporation

Inventor： XU, JinQuan ,  LEVASSEUR, Glenn ,  VERNER, Carl R.

IPC: B22C7/06 ,  B22C9/04 ,  B22C9/10 ,  B22C9/12 ,  B22D29/00 ,  B22C7/02

CPC classification number: B22C7/06 ,  B22C7/026 ,  B22C9/043 ,  B22C9/046 ,  B22C9/10 ,  B22C9/12 ,  B22D29/002 ,  B22D29/005

Abstract: A method of forming an integral casting core (52) includes adding a disposable insert (50) to a core die (48) with the disposable insert (50) defining an inner wall in a multi-wall airfoil (16). The core die (48) includes at least one of epoxy, ceramic, silicone, polysiloxane, polydimethylsiloxane, polyimide, epoxysilanes, phenolics, polyurethanes, polysilsesquioxanes, organic matrix composites, metal matrix composites, and a hybrid material. A slurry is disposed into the core die (48) and fired to form an integral casting core (52). The disposable insert (50) is removed from the integral casting core (52).