公开(公告)号：US20190145266A1

公开(公告)日：2019-05-16

申请号：US15810809

申请日：2017-11-13

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Daniel C. Crites ,  Michael Kahrs ,  Brandan Wakefield ,  Ardeshir Riahi

IPC: F01D5/18

Abstract: An airfoil for a rotor blade in a gas turbine engine includes a first side wall and a second side wall joined to the first side wall at a leading edge and a trailing edge. The airfoil further includes a tip cap extending between the first and second side walls such that the tip cap and at least portions of the first and second side walls form a blade tip and an internal cooling system. The internal cooling system includes a leading edge cooling circuit, a central cooling circuit, and a trailing edge cooling circuit. Each of the internal passages within the leading edge cooling circuit, the central cooling circuit, and the trailing edge cooling circuit is bounded in the radial outward direction with a surface that has at least one escape hole or that is positively angled in the radial outward direction relative to a chordwise axis.

公开(公告)号：US20180274377A1

公开(公告)日：2018-09-27

申请号：US15470471

申请日：2017-03-27

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Harry Lester Kington ,  Daniel C. Crites ,  Jeff Howe

IPC: F01D9/04 ,  F01D9/06

CPC classification number: F01D9/041 ,  F01D5/189 ,  F01D9/065 ,  F05D2240/127 ,  F05D2250/71 ,  F05D2260/201 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/676

Abstract: Vane impingement tubes having blockage deterrent features are provided, as turbine nozzles containing blockage-resistant vane impingement tubes. In an embodiment, the turbine nozzle includes inner and outer annular endwalls, and turbine nozzle vanes arranged in an annular array between the outer and inner annular endwalls. Vane impingement tubes are inserted into the turbine nozzle vanes. The vane impingement tubes each includes a tube body, an impingement outlet formed in the tube body and configured to discharge airflow for impingement against one of the turbine nozzle vanes, a first flow-turning feature located in the tube body, and an inlet formed in the tube body and configured receive cooling airflow in a substantially radial direction. The first flow-turning feature is shaped and positioned to turn the airflow received through the inlet in a substantially axial direction, which is perpendicular to the radial direction, prior to discharge through the impingement outlet.

公开(公告)号：US20140356188A1

公开(公告)日：2014-12-04

申请号：US13871655

申请日：2013-04-26

Applicant: HONEYWELL INTERNATIONAL, INC.

Inventor： Vighneswara Rao Kollati ,  Balamurugan Srinivasan ,  Jong Liu ,  Daniel C. Crites ,  Luis Tapia ,  Malak Fouad Malak ,  Rajiv Rana

IPC: F01D5/18 ,  B23P15/02

CPC classification number: F01D5/186 ,  B23P15/02 ,  F05D2230/10 ,  F05D2240/303 ,  F05D2240/305 ,  F05D2240/306 ,  Y02T50/676 ,  Y10T29/49341

Abstract: Turbine blade airfoils, film cooling systems thereof, and methods for forming improved film cooled components are provided. The turbine blade airfoil has an external wall surface and comprises leading and trailing edges, pressure and suction sidewalls both extending between the leading and the trailing edges, an internal cavity, one or more isolation trenches in the external wall surface, a plurality of film cooling holes arranged in cooling rows, and a plurality of span-wise surface connectors interconnecting the outlets of the film cooling holes in the same cooling row to form a plurality of rows of interconnected film cooling holes. Each film cooling hole has an inlet connected to the internal cavity and an outlet opening onto the external wall surface. The span-wise surface connectors in at least one selected row of interconnected film cooling holes are disposed in the one or more isolation trenches.

Abstract translation: 提供了涡轮叶片翼型件，其薄膜冷却系统以及用于形成改进的薄膜冷却部件的方法。 涡轮叶片翼型件具有外壁表面并且包括前缘和后缘，压力和吸力侧壁均在前缘和后缘之间延伸，内腔，外壁表面中的一个或多个隔离沟槽，多个膜冷却 布置在冷却排中的孔，以及将相同冷却排中的膜冷却孔的出口互连的多个跨距表面连接器，以形成多排相互连接的膜冷却孔。 每个薄膜冷却孔具有连接到内部空腔的入口和外壁表面上的出口。 在至少一个所选择的互连薄膜冷却孔排中的跨度表面连接器设置在所述一个或多个隔离沟槽中。

公开(公告)号：US11448093B2

公开(公告)日：2022-09-20

申请号：US17180035

申请日：2021-02-19

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Steven Whitaker ,  Daniel C. Crites ,  Mark C. Morris ,  Ardeshir Riahi

IPC: F01D25/12 ,  F01D9/04

Abstract: A turbine vane includes an airfoil that extends from an inner diameter to an outer diameter, and from a leading edge to a trailing edge. The turbine vane includes an inner platform coupled to the airfoil at the inner diameter. The turbine vane includes a cooling system defined in the airfoil including a first conduit in proximity to the leading edge to cool the leading edge and a second conduit to cool the trailing edge. The first conduit has an inlet at the outer diameter to receive a cooling fluid and an outlet portion that is defined at least partially through the inner platform. The first conduit includes a plurality of cooling features that extend between a first surface and a second surface of the first conduit, and the first surface of the first conduit is opposite the leading edge.

公开(公告)号：US11199099B2

公开(公告)日：2021-12-14

申请号：US16826953

申请日：2020-03-23

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Daniel C. Crites ,  Michael Kahrs ,  Brandan Wakefield ,  Ardeshir Riahi

IPC: F01D5/18

Abstract: An airfoil for a rotor blade in a gas turbine engine includes a first side wall and a second side wall joined to the first side wall at a leading edge and a trailing edge. The airfoil further includes a tip cap extending between the first and second side walls such that the tip cap and at least portions of the first and second side walls form a blade tip and an internal cooling system. The internal cooling system includes a leading edge cooling circuit, a central cooling circuit, and a trailing edge cooling circuit. Each of the internal passages within the leading edge cooling circuit, the central cooling circuit, and the trailing edge cooling circuit is bounded in the radial outward direction with a surface that has at least one escape hole or that is positively angled in the radial outward direction relative to a chordwise axis.

公开(公告)号：US11015472B2

公开(公告)日：2021-05-25

申请号：US17014547

申请日：2020-09-08

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Steve Halfmann ,  Daniel C. Crites ,  Michael Kahrs ,  Ardeshir Riahi ,  Jude Miller

IPC: F01D11/00 ,  F01D5/08 ,  F01D5/30 ,  F01D5/12 ,  F01D5/22

Abstract: A turbine engine includes a turbine wheel including a rotor disk and turbine blades connected to the rotor disk through blade mounts. The blade mounts and the rotor disk have fore and aft surfaces. The blade mount includes a blade attachment surface connecting the fore and aft surfaces with the turbine blade extending from the blade attachment surface. A gap is defined between and separating adjacent blade mounts and extends into the rotor disk. The gap includes a pocket having a fore opening and a rotor relief hole. The turbine wheel further includes a plug disposed in a rotor relief opening and a pocket seal disposed in the pocket. The turbine engine further includes a fore seal plate having an edge abutting the blade mounts about a circumference of the turbine wheel and a finger extending toward and contacting the plug to maintain the plug in the rotor relief opening.

公开(公告)号：US10989067B2

公开(公告)日：2021-04-27

申请号：US16035173

申请日：2018-07-13

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Steven Whitaker ,  Daniel C. Crites ,  Mark C. Morris ,  Ardeshir Riahi

IPC: F01D25/12 ,  F01D9/04

Abstract: A turbine vane includes an airfoil that extends from an inner diameter to an outer diameter, and from a leading edge to a trailing edge. The turbine vane includes an inner platform coupled to the airfoil at the inner diameter. The turbine vane includes a cooling system defined in the airfoil including a first conduit in proximity to the leading edge to cool the leading edge and a second conduit to cool the trailing edge. The first conduit has an inlet at the outer diameter to receive a cooling fluid and an outlet portion that is defined at least partially through the inner platform. The first conduit includes a plurality of cooling features that extend between a first surface and a second surface of the first conduit, and the first surface of the first conduit is opposite the leading edge.

公开(公告)号：US10954801B2

公开(公告)日：2021-03-23

申请号：US16546055

申请日：2019-08-20

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Benjamin Dosland Kamrath ,  Jason Smoke ,  Daniel C. Crites

IPC: F01D5/18

Abstract: A cooling circuit to receive a cooling fluid includes at least one shaped cooling pin disposed in the cooling circuit. The at least one shaped cooling pin has a first end and a second end extending along an axis. The first end has a first curved surface defined by a minor diameter and the second end has a second curved surface defined by a major diameter. The first curved surface is to be upstream in the cooling fluid and the minor diameter is less than the major diameter.

公开(公告)号：US20200378277A1

公开(公告)日：2020-12-03

申请号：US16998523

申请日：2020-08-20

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Daniel C. Crites ,  Mark C. Morris ,  Steven Whitaker ,  David Waldman

IPC: F01D25/32 ,  F01D5/18 ,  F01D5/20

Abstract: A turbine blade includes an airfoil that has a tip region that extends from the leading edge toward the trailing edge, and the tip region is bounded by a wall that extends at an angle. The leading edge has a leading edge cooling circuit that is defined from the platform to a tip flag channel, and the leading edge cooling circuit is in fluid communication with the tip flag channel. The pressure side includes at least one tip dust hole defined through the wall proximate the pressure side, and the at least one tip dust hole has an inlet and an outlet. The airfoil has at least one rib defined on the wall that extends at a second angle to direct the particles and a portion of the cooling fluid into the inlet.

公开(公告)号：US10751843B2

公开(公告)日：2020-08-25

申请号：US15639061

申请日：2017-06-30

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Michael Kahrs ,  Daniel C. Crites ,  Jude Miller ,  Steve Halfmann ,  Jason Smoke ,  Ardeshir Riahi ,  David K. Jan

IPC: B23P15/00 ,  F01D5/02 ,  F01D5/30 ,  F01D5/08

Abstract: Turbine wheels, turbine engines, and methods of fabricating the turbine wheels are provided. An exemplary method includes fabricating a turbine wheel that includes a rotor disk and a plurality of turbine blades operatively connected to the rotor disk through a blade mount. The method includes locating a cooling passage within a blade mount preliminary configuration and a cooling inlet on a surface of the blade mount preliminary configuration. A rotor disk bonding surface geometry and a blade mount bonding surface geometry are designed based upon a stress analysis of the turbine wheel and locations of the cooling passage and cooling inlet. A rotor disk production configuration and a blade mount production configuration are generated based upon the preliminary configurations. A blade mount and a rotor disk are formed based upon the production configurations. A blade ring including a plurality of blade mounts is formed and bonded to the rotor disk.