公开(公告)号：WO2013123012A1

公开(公告)日：2013-08-22

申请号：PCT/US2013/025887

申请日：2013-02-13

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： XU, JinQuan

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

CPC classification number: F01D5/187 ,  F01D5/186 ,  F01D9/041 ,  F01D9/065 ,  F01D25/12 ,  F01D25/24 ,  F01D25/30 ,  F02C3/04 ,  F04D29/324 ,  F04D29/522 ,  F04D29/542 ,  F04D29/582 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2240/81 ,  F05D2250/70 ,  F05D2250/71 ,  F05D2260/202 ,  F23R3/002 ,  F23R2900/03042 ,  Y02T50/676

Abstract: A component for a gas turbine engine including a gas path wall having a first surface and a second surface. A cooling hole extends through the gas path wall from an inlet in the first surface through a transition to an outlet in the second surface. Cusps are formed on the transition.

Abstract translation: 一种用于燃气涡轮发动机的部件，其包括具有第一表面和第二表面的气体通道壁。 冷却孔从第一表面中的入口穿过气体通道壁延伸穿过第二表面中的出口。 尖峰形成在过渡处。

公开(公告)号：EP2971666B1

公开(公告)日：2020-10-21

申请号：EP14767556.5

申请日：2014-03-11

Applicant: United Technologies Corporation

Inventor： XU, JinQuan

IPC: F01D5/18

公开(公告)号：EP2815077B1

公开(公告)日：2020-05-06

申请号：EP13748741.9

申请日：2013-02-12

Applicant: United Technologies Corporation

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

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

公开(公告)号：EP3587734A1

公开(公告)日：2020-01-01

申请号：EP19181025.8

申请日：2019-06-18

Applicant: United Technologies Corporation

Inventor： XU, JinQuan ,  LEVASSEUR, Glenn

IPC: F01D5/18 ,  F01D9/06 ,  F23R3/00

Abstract: A gas turbine engine component (161;261) according to an example of the present disclosure includes, among other things, a wall (162E;261A) between first and second wall surfaces (261B,261C). The wall (261B,261C) defines at least one cooling passage (174;274;374;474;574;674;774) extending between an inlet (176;276) along the first wall surface (261B) and an outlet (178;278;378;478;578;678) along the second wall surface (261C). The outlet (178;278;378;478;578;678) has an upstream edge (278U;378U;478U;578U;678U;778U) and a downstream edge (278D,378D,478D,578D) with respect to a general direction of flow through the at least one cooling passage (174;274;374;474;574;674;774). The wall (162E;261A) defines a plurality of crenellation features (280;380;480;580;680;780) along at least the upstream edge (278U;378U;478U;578U;678U;778U). The upstream edge (278U;378U;478U;578U;678U;778U) has a first profile established by the plurality of crenellation features (280;380;480;580;680;780), and the downstream edge (278D,378D,478D,578D) has a second profile that differs from the first profile. A method of cooling is also disclosed.

公开(公告)号：EP2938829B1

公开(公告)日：2019-10-09

申请号：EP13868671.2

申请日：2013-02-12

Applicant: United Technologies Corporation

Inventor： XU, JinQuan

IPC: F01D5/14 ,  F01D9/04

公开(公告)号：EP2986414B1

公开(公告)日：2019-06-05

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: C30B29/52 ,  C30B11/00 ,  C30B21/00 ,  C30B21/02 ,  B22F5/04 ,  B22F3/105 ,  B22C9/10 ,  B22C9/02 ,  B22C9/22 ,  B22C9/24 ,  B22D23/06 ,  B22D25/02 ,  B22D27/04

公开(公告)号：EP3388633A1

公开(公告)日：2018-10-17

申请号：EP18174950.8

申请日：2015-11-18

Applicant: United Technologies Corporation

Inventor： XU, JinQuan ,  LEWIS Scott D.

IPC: F01D5/18

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). The plurality of crossover passages includes a first set of crossover passages and a second set of crossover passages positioned on opposite sides of the first reference plane, and at least one of the first set of crossover passages includes a helical geometry.

公开(公告)号：EP3032035B1

公开(公告)日：2018-09-19

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：EP2815105B1

公开(公告)日：2018-05-30

申请号：EP13784655.6

申请日：2013-02-13

Applicant: United Technologies Corporation

Inventor： XU, JinQuan

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

CPC classification number: F01D5/186 ,  F01D9/065 ,  F05D2240/81 ,  F05D2260/202 ,  F23R3/06 ,  F23R2900/00018 ,  F23R2900/03042 ,  Y02T50/673 ,  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 extending from the transition along the metering section of the cooling hole toward the inlet.

公开(公告)号：EP2815101B1

公开(公告)日：2018-05-30

申请号：EP13749742.6

申请日：2013-02-13

Applicant: United Technologies Corporation ,  Xu, Jinquan

Inventor： XU, JinQuan

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

CPC classification number: F01D5/186 ,  F01D9/065 ,  F05D2240/81 ,  F05D2250/20 ,  F05D2250/52 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

Abstract: A component for a gas turbine engine includes a wall and a cooling hole extending through the wall. The wall has a first surface and a second surface. The cooling hole includes a metering section that extends from an inlet in the first surface of the wall to a transition, a diffusing section that extends from the transition to an outlet in the second surface of the wall, and a cusp on the transition.