公开(公告)号：US10821500B2

公开(公告)日：2020-11-03

申请号：US15960857

申请日：2018-04-24

Applicant: United Technologies Corporation

Inventor： Lane Thornton ,  San Quach ,  Steven Bruce Gautschi

IPC: B22C9/10 ,  B22C9/24

Abstract: In a featured embodiment, a lost core assembly includes a ceramic component having a tapered shape in a radial direction. A refractory metal component extends radially from the ceramic core component. A method of molding a gas turbine engine component is also disclosed.

公开(公告)号：US10273809B2

公开(公告)日：2019-04-30

申请号：US15100925

申请日：2014-12-08

Applicant: United Technologies Corporation

Inventor： Lane Thornton ,  Thomas N. Slavens

IPC: F01D5/18 ,  F01D5/28 ,  F02C3/04 ,  F02C7/12

Abstract: In one example embodiment, a blade includes an attachment region, an airfoil extending from the attachment region, and a blade cooling arrangement. The blade cooling arrangement includes at least a first feed passage disposed through the attachment region, which is connected to a first cooling passage disposed in the airfoil. A passively actuated first coolant valve is disposed in or proximate the first feed passage. A plurality of such blades can be disposed in a turbine section of an engine.

公开(公告)号：US20160348525A1

公开(公告)日：2016-12-01

申请号：US14726722

申请日：2015-06-01

Applicant: United Technologies Corporation

Inventor： Lane Thornton

IPC: F01D11/00 ,  F01D5/22 ,  F01D5/14

CPC classification number: F01D11/006 ,  F01D5/147 ,  F01D5/22 ,  F01D5/225 ,  F01D11/00 ,  F01D11/005 ,  F01D11/008 ,  F05D2220/32 ,  F05D2240/55 ,  F05D2240/80 ,  F05D2260/941 ,  F05D2300/173 ,  F05D2300/174 ,  F05D2300/177

Abstract: A platform trailing edge seal for a turbomachine airfoil (e.g., a blade or vane) assembly includes a body configured to extend into an aft portion of a mateface gap defined between a circumferentially adjacent pair of turbomachine airfoil platforms to minimize flow from entering a blade-vane cavity through the aft portion of the mateface gap.

Abstract translation: 用于涡轮机翼型件（例如，叶片或叶片）组件的平台后缘密封件包括构造成延伸到限定在周向相邻的一对涡轮机翼型平台之间的配合间隙的后部的主体，以最小化进入叶片 - 通过叶片间隙的后部分的叶片腔。

公开(公告)号：US20160326883A1

公开(公告)日：2016-11-10

申请号：US15107493

申请日：2015-01-02

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Lane Thornton ,  Matthew A. Devore ,  Dominic J. Mongillo ,  Steven Bruce Gautschi

IPC: F01D5/18

Abstract: A gas turbine engine component comprises an airfoil with a suction side and pressure side extending from a leading edge to a trailing edge. There are a plurality of cooling holes adjacent the leading edge, with the cooling holes having a non-circular shape, with a longer dimension and a smaller dimension. The airfoil defines a radial direction from a radially outer end to a radially inner end, and radially outer of the cooling holes spaced toward the radially outer end, which have the longer dimension extending closer to parallel to the radial direction. Radially inner cooling holes closer to the radially inner end having the longer dimension extend to be closer to perpendicular relative to the radial direction compared to the radially outer cooling holes.

Abstract translation: 燃气涡轮发动机部件包括具有从前缘延伸到后缘的吸力侧和压力侧的翼型件。 在前缘附近有多个冷却孔，冷却孔具有非圆形形状，具有较长的尺寸和较小的尺寸。 翼型件限定从径向外端到径向内端的径向方向，并且冷却孔的径向外部与径向外端间隔开，其具有更靠近平行于径向的较长尺寸。 与径向外侧冷却孔相比，更靠近具有较长尺寸的径向内端的径向内部冷却孔相对于径向更接近垂直。

公开(公告)号：US20160312619A1

公开(公告)日：2016-10-27

申请号：US14697329

申请日：2015-04-27

Applicant: United Technologies Corporation

Inventor： Lane Thornton ,  Ryan Alan Waite ,  Peter Balawajder ,  Benjamin F. Hagan

IPC: F01D5/18 ,  F02C3/04 ,  F01D25/12 ,  F01D9/04 ,  F01D11/08

CPC classification number: F01D5/186 ,  F01D9/02 ,  F01D9/041 ,  F01D9/065 ,  F01D11/08 ,  F01D25/12 ,  F02C3/04 ,  F05D2220/32 ,  F05D2230/90 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2240/35 ,  F05D2240/55 ,  F05D2240/81 ,  F05D2250/33 ,  F05D2250/72 ,  F05D2250/73 ,  F05D2260/202 ,  F05D2260/2212 ,  F23R3/002 ,  F23R2900/03042 ,  Y02T50/676

Abstract: A film cooled component may comprise a cooling chamber and a first ligament centered about a first axis. The first ligament may be in fluid communication with the cooling chamber. A first meter may be disposed at an end of the first ligament. A first diffuser may extend from the first meter to a surface of the film cooled component. The first diffuser may comprise a first tapered sidewall oriented at an angle of between 5 degrees to 15 degrees relative to the first axis. The first diffuser may further comprise a first non-tapered sidewall oriented at an angle less than 5 degrees relative to the first axis.

Abstract translation: 薄膜冷却部件可以包括冷却室和围绕第一轴线居中的第一韧带。 第一韧带可以与冷却室流体连通。 第一米可以设置在第一韧带的末端。 第一扩散器可以从第一米延伸到薄膜冷却部件的表面。 第一扩散器可以包括相对于第一轴线以5度至15度的角度定向的第一锥形侧壁。 第一扩散器还可以包括相对于第一轴线以小于5度的角度定向的第一非锥形侧壁。

公开(公告)号：US20160305252A1

公开(公告)日：2016-10-20

申请号：US15100925

申请日：2014-12-08

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Lane Thornton ,  Thomas N. Slavens

IPC: F01D5/18 ,  F02C7/12 ,  F01D5/28 ,  F02C3/04

CPC classification number: F01D5/186 ,  F01D5/187 ,  F01D5/28 ,  F02C3/04 ,  F02C7/12 ,  F05D2220/32 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2300/175 ,  F05D2300/505 ,  Y02T50/676

Abstract: In one example embodiment, a blade includes an attachment region, an airfoil extending from the attachment region, and a blade cooling arrangement. The blade cooling arrangement includes at least a first feed passage disposed through the attachment region, which is connected to a first cooling passage disposed in the airfoil. A passively actuated first coolant valve is disposed in or proximate the first feed passage. A plurality of such blades can be disposed in a turbine section of an engine.

Abstract translation: 在一个示例性实施例中，叶片包括附接区域，从连接区域延伸的翼型件和叶片冷却装置。 叶片冷却装置包括至少一个穿过安装区域设置的第一进料通道，其连接到设置在翼型件中的第一冷却通道。 被动地驱动的第一冷却剂阀设置在第一进料通道中或其附近。 多个这样的叶片可以设置在发动机的涡轮机部分中。

公开(公告)号：US10738619B2

公开(公告)日：2020-08-11

申请号：US15107493

申请日：2015-01-02

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Lane Thornton ,  Matthew A. Devore ,  Dominic J. Mongillo ,  Steven Bruce Gautschi

IPC: F01D5/18

Abstract: A gas turbine engine component comprises an airfoil with a suction side and pressure side extending from a leading edge to a trailing edge. There are a plurality of cooling holes adjacent the leading edge, with the cooling holes having a non-circular shape, with a longer dimension and a smaller dimension. The airfoil defines a radial direction from a radially outer end to a radially inner end, and radially outer of the cooling holes spaced toward the radially outer end, which have the longer dimension extending closer to parallel to the radial direction. Radially inner cooling holes closer to the radially inner end having the longer dimension extend to be closer to perpendicular relative to the radial direction compared to the radially outer cooling holes.

公开(公告)号：US10400607B2

公开(公告)日：2019-09-03

申请号：US14627587

申请日：2015-02-20

Applicant: United Technologies Corporation

Inventor： Lane Thornton ,  Scott D. Lewis ,  Matthew A. Devore

IPC: F01D5/08 ,  F01D5/18 ,  F01D9/04 ,  F01D25/12

Abstract: A cooling hole for a component includes a meter section and a diffuser section. The diffuser section has a footprint region defined by five sides, a first side of the five sides extending along substantially an entire height of the diffuser section and second and third sides of the five sides meeting in an obtuse angle opposite the first side. A component having the cooling hole and a method of forming the cooling hole are also disclosed.

公开(公告)号：US20170145833A1

公开(公告)日：2017-05-25

申请号：US14948511

申请日：2015-11-23

Applicant: United Technologies Corporation

Inventor： Lane Thornton

IPC: F01D5/18 ,  F01D25/12 ,  F01D9/04

CPC classification number: F01D5/187 ,  F01D5/189 ,  F01D9/041 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/80 ,  F05D2240/12 ,  F05D2240/122 ,  F05D2240/126 ,  F05D2240/301 ,  F05D2240/304 ,  F05D2260/202 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676

Abstract: An airfoil according to an example of the present disclosure includes, among other things, an airfoil body defining a cavity, and a baffle including a baffle body including sidewalls and defining an internal passage for conveying coolant. The baffle body is situated in the cavity such that a majority of external surfaces of the sidewalls abut the cavity.

公开(公告)号：US20160326898A1

公开(公告)日：2016-11-10

申请号：US14704278

申请日：2015-05-05

Applicant: United Technologies Corporation

Inventor： Dominic J. Mongillo, JR. ,  Brandon W. Spangler ,  Lane Thornton

IPC: F01D11/00

CPC classification number: F01D11/006 ,  F01D11/005 ,  F01D25/246 ,  F05D2240/11 ,  F05D2240/57 ,  F05D2250/182 ,  Y02T50/672

Abstract: A component for a gas turbine engine according to an example of the present disclosure includes, among other things, a body including a cold side surface adjacent to a mate face. A plurality of ridges extends from the cold side surface. A seal member abuts the plurality of ridges to define a plurality of cooling passages. The seal member is configured to move between a first position and a second position relative to the plurality of ridges. Each of the plurality of cooling passages includes a first inlet defined at the first position and a second, different inlet defined at the second position. A method of sealing between adjacent components of a gas turbine engine is also disclosed.

Abstract translation: 根据本公开的示例的用于燃气涡轮发动机的部件包括包括邻近配合面的冷侧表面的主体。 多个脊从冷侧表面延伸。 密封构件邻接多个脊以限定多个冷却通道。 密封构件被构造成相对于多个脊在第一位置和第二位置之间移动。 多个冷却通道中的每一个包括限定在第一位置处的第一入口和限定在第二位置处的第二不同入口。 还公开了一种在燃气涡轮发动机的相邻部件之间的密封方法。