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：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.

公开(公告)号：US10648354B2

公开(公告)日：2020-05-12

申请号：US15367735

申请日：2016-12-02

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: Turbine wheels, turbine engines, and methods of forming the turbine wheels are provided herein. In an embodiment, a turbine wheel includes a rotor disk and a plurality of turbine blades. Each turbine blade is operatively connected to the rotor disk through a blade mount, which is bonded to the rotor disk. The blade mount and the rotor disk have a fore surface on a higher pressure side thereof and an aft surface on a lower pressure side thereof. The blade mount includes a blade attachment surface that extends between and connects the fore surface and the aft surface. The turbine blade extends from the blade attachment surface. A gap is defined between adjacent blade mounts. The gap separates the blade mounts and extends into the rotor disk. The gap includes a pocket that has a fore opening in the fore surface. A pocket seal is disposed in the pocket.

公开(公告)号：US20200141258A1

公开(公告)日：2020-05-07

申请号：US16580951

申请日：2019-09-24

Applicant: HONEYWELL INTERNATIONAL INC.

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

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

Abstract: Turbine wheels, turbine engines, and methods of forming the turbine wheels are provided herein. In an embodiment, a turbine wheel includes a rotor disk and a plurality of turbine blades. Each turbine blade is operatively connected to the rotor disk through a blade mount, which is bonded to the rotor disk. The blade mount and the rotor disk have a fore surface on a higher pressure side thereof and an aft surface on a lower pressure side thereof. The blade mount includes a blade attachment surface that extends between and connects the fore surface and the aft surface. The turbine blade extends from the blade attachment surface. A gap is defined between adjacent blade mounts. The gap separates the blade mounts and extends into the rotor disk. The gap includes a pocket that has a fore opening in the fore surface. A pocket seal is disposed in the pocket.

公开(公告)号：US10260355B2

公开(公告)日：2019-04-16

申请号：US15062952

申请日：2016-03-07

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Jason Smoke ,  David K Jan ,  Amandine Miner ,  Deanna Pinar Chase ,  Michael Kahrs ,  Lorenzo Crosatti

IPC: F01D5/18 ,  F01D5/04 ,  F01D1/08 ,  F01D5/30

Abstract: A turbine blade and a radial turbine having at least one blade is provided. The turbine blade includes a trailing edge and a leading edge opposite the trailing edge. The turbine blade also includes a cooling passage defined internally within the turbine blade. The cooling passage is in fluid communication with a source of cooling fluid via a single inlet to receive a cooling fluid. The cooling passage diverges at a first point downstream from the single inlet into at least two branches that extend along the at least one blade from the first point to a second point near a tip of the leading edge and the cooling passage converges at the second point.

公开(公告)号：US20190001448A1

公开(公告)日：2019-01-03

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 ,  F01D5/30 ,  F01D5/02 ,  F01D5/08

CPC classification number: B23P15/006 ,  F01D5/02 ,  F01D5/025 ,  F01D5/08 ,  F01D5/085 ,  F01D5/3015 ,  F01D5/3061 ,  F05D2220/32 ,  F05D2230/232 ,  F05D2240/24 ,  F05D2240/81

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.