公开(公告)号：US10329937B2

公开(公告)日：2019-06-25

申请号：US15267632

申请日：2016-09-16

Applicant: United Technologies Corporation

Inventor： Mark A. Boeke ,  Jeffrey J. DeGray ,  Richard M. Salzillo, Jr.

IPC: F02C3/04 ,  F01D11/00 ,  F01D5/06 ,  F01D9/04

Abstract: A flow path component includes a platform having at least one radially aligned face. A chordal seal extends axially from the radially aligned face. The chordal seal includes a first curved face configured to prevent edge line contact under deflection conditions while the flow path component is installed in an engine.

公开(公告)号：US10294806B2

公开(公告)日：2019-05-21

申请号：US14770189

申请日：2014-03-11

Applicant: United Technologies Corporation

Inventor： Sarah Riley ,  Jeffrey R. Levine ,  Mark A. Boeke

IPC: F01D9/04 ,  C23C14/04 ,  C23C4/02 ,  C23C4/11 ,  C23C4/01 ,  C23C4/12 ,  C23C14/22 ,  C23C4/134 ,  F01D5/28 ,  C23C14/30

Abstract: An article includes a body that has a coating thereon. The coating has a first portion disposed on a first section of the body and a second portion disposed on a second, different section of the body. The first portion has a first microstructure and the second portion has a second, different microstructure.

公开(公告)号：US20180106156A1

公开(公告)日：2018-04-19

申请号：US15295268

申请日：2016-10-17

Applicant: United Technologies Corporation

Inventor： Nicholas M. LoRicco ,  Mark A. Boeke ,  Jeffrey J. DeGray ,  Richard M. Salzillo ,  Dominic J. Mongillo

IPC: F01D9/04 ,  F01D25/12

CPC classification number: F01D9/065 ,  F05D2240/81 ,  F05D2250/74 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

Abstract: A vane includes a pair of airfoils that have a plurality of film cooling holes that extend through an exterior surface of the airfoils. Each plurality of film cooling holes break through the exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Table 1. Each geometric coordinates is measured from a reference point on a leading edge rail of a platform of the vane.

公开(公告)号：US20180066524A1

公开(公告)日：2018-03-08

申请号：US15255187

申请日：2016-09-02

Applicant: United Technologies Corporation

Inventor： Nicholas M. LoRicco ,  Mark A. Boeke ,  Richard M. Salzillo, JR. ,  Jeffrey J. DeGray

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

CPC classification number: F01D5/187 ,  F01D5/186 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/10 ,  F05D2230/21 ,  F05D2260/202 ,  F05D2260/221 ,  Y02T50/676

Abstract: A cooled component for a gas turbine engine includes a plurality of internal ribs extending substantially parallel to a longitudinal axis of the gas turbine engine. The internal ribs are disposed within an internal cavity defining cooling air passages within the cooled component. A plurality of cooling holes are arranged in rows with axial orientations alternating between a radially outboard bias directing cooling air radially outward and a radially inboard bias directing cooling air radially inward. Each of the cooling holes includes an internal opening in communication with one of the cooling air passages and an external opening open to an outer surface of the cooled component. The external opening of each of the plurality of cooling holes is disposed on a side opposite the internal rib relative to a corresponding internal opening. A gas turbine engine and a method of fabricating a turbine airfoil are also disclosed.

公开(公告)号：US20160333712A1

公开(公告)日：2016-11-17

申请号：US14708939

申请日：2015-05-11

Applicant: United Technologies Corporation

Inventor： Mark A. Boeke ,  Kevin Rajchel ,  Mosheshe Camara-khary Blake ,  Vincent E. Simms

IPC: F01D11/00 ,  F01D9/04

CPC classification number: F01D9/042 ,  F01D11/006 ,  F01D25/246 ,  F05D2240/57

Abstract: An airfoil for a gas turbine engine includes a first airfoil. A first chordal seal is located adjacent a first end of the airfoil. A second chordal seal is located adjacent a second end of the airfoil. The first chordal seal includes a first edge parallel to a first edge on the second chordal seal.

Abstract translation: 用于燃气涡轮发动机的翼型件包括第一翼型件。 第一和弦密封件位于翼型件的第一端附近。 第二弦编密封位于翼型的第二端附近。 第一弦音密封包括平行于第二弦音密封件上的第一边缘的第一边缘。

公开(公告)号：US20160251969A1

公开(公告)日：2016-09-01

申请号：US14634006

申请日：2015-02-27

Applicant: United Technologies Corporation

Inventor： Mark A. Boeke ,  Richard M. Salzillo ,  Jeffrey J. DeGray ,  Shawn J. Gregg

IPC: F01D5/18 ,  F01D9/04 ,  F01D25/12 ,  F01D5/14

CPC classification number: F01D5/189 ,  F01D5/141 ,  F01D5/147 ,  F01D9/041 ,  F01D9/065 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/20 ,  F05D2230/60 ,  F05D2240/126 ,  F05D2240/301 ,  F05D2240/81 ,  F05D2260/221 ,  Y02T50/676

Abstract: An airfoil includes an airfoil wall including an exterior airfoil surface and at least partially defines an airfoil cavity. A fillet is on the exterior airfoil surface. A recess is in an interior surface of the airfoil wall adjacent the fillet. A baffle tube is located in the airfoil cavity spaced from the recess.

Abstract translation: 翼型件包括包括外部翼型件表面的翼型件壁，并且至少部分地限定翼型腔。 一个圆角在外部翼面上。 凹槽位于靠近圆角的翼型壁的内表面。 挡板管位于与凹槽间隔开的翼型腔中。

公开(公告)号：US20160153304A1

公开(公告)日：2016-06-02

申请号：US14942484

申请日：2015-11-16

Applicant: United Technologies Corporation

Inventor： Andrew S. Aggarwala ,  Russell J. Bergman ,  Mark A. Boeke ,  Kyle C. Lana ,  Daniel A. Snyder

IPC: F01D11/00 ,  F01D5/22

CPC classification number: F01D11/006 ,  F01D5/22 ,  F01D11/001 ,  F01D11/02

Abstract: An airfoil stage of a turbine engine includes an upstream airfoil assembly, a downstream airfoil assembly in rotational relationship to the upstream airfoil assembly and a rim seal assembly integrated therebetween. The rim seal assembly may include a sloped downstream portion of a platform of the upstream airfoil assembly, an upstream segment of a platform of the downstream airfoil assembly and a nub that projects radially outward from the upstream segment. The downstream portion and the upstream segment are spaced from one-another defining a cooling cavity therebetween for the flow of cooling air. The portion and segment overlap axially such that the nub is axially aligned to the downstream portion for improved cooling effectiveness and a reduction of core airflow into the cooling cavity.

Abstract translation: 涡轮发动机的翼型段包括上游翼型组件，与上游翼型组件成旋转关系的下游翼型组件和集成在其间的边缘密封组件。 轮辋密封组件可以包括上游翼型组件的平台的倾斜下游部分，下游翼型组件的平台的上游部分和从上游部分径向向外突出的凸块。 下游部分和上游段彼此间隔开，在其间限定冷却空气的流动。 该部分和部分轴向重叠，使得该凸块与下游部分轴向对齐，以改善冷却效果并减少进入冷却腔的芯气流。

公开(公告)号：US20140219778A1

公开(公告)日：2014-08-07

申请号：US13630419

申请日：2012-09-28

Applicant: United Technologies Corporation

Inventor： Mark A. Boeke ,  Shawn J. Gregg ,  Sarah Riley ,  Jeffrey J. DeGray ,  Richard M. Salzillo

IPC: F01D5/18 ,  F01D9/02

CPC classification number: F01D5/186 ,  F01D5/187 ,  F01D9/02 ,  F01D25/12 ,  F01D25/246 ,  F05D2240/12 ,  F05D2240/81 ,  F05D2260/204 ,  Y02T50/672 ,  Y02T50/676

Abstract: A stator vane for a gas turbine engine includes an airfoil extending in a radial direction and supported by a platform having a gas flowpath surface. A cooling passage is arranged in the platform and includes a circumferential passage that is fluidly connected to an inlet passage extending through and edge of the platform, and film cooling holes extending from the gas flowpath surface to the circumferential passage, radial extending passage through the edge of the platform. A void is interconnected to at least one of the radially extending passage and the inlet passage.

Abstract translation: 用于燃气涡轮发动机的定子叶片包括沿径向延伸并由具有气体流路表面的平台支撑的翼型件。 冷却通道布置在平台中，并且包括流体连接到延伸通过平台的边缘的入口通道的圆周通道，以及从气体流路表面延伸到周向通道的膜冷却孔，通过边缘的径向延伸通道 的平台。 空隙与径向延伸通道和入口通道中的至少一个相互连接。