公开(公告)号：US10655476B2

公开(公告)日：2020-05-19

申请号：US15841844

申请日：2017-12-14

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Steve Halfmann ,  Daniel C. Crites ,  Mark C. Morris ,  Ardeshir Riahi

IPC: F01D5/18

Abstract: An airfoil for a gas turbine engine includes a first side wall; a second side wall joined to the first side wall at a leading edge and a trailing edge; and an internal cooling system arranged within the first and second side walls configured to direct cooling air through and out of the airfoil. The internal cooling system has a first cooling circuit that includes an acceleration channel generally extending in a radial outward direction. A first section of the acceleration channel decreases in cross-sectional area along the radial outward direction such that the cooling air is accelerated through the first section of the acceleration channel. The first cooling circuit further includes a trailing edge chamber fluidly coupled to receive at least a portion of the cooling air from the acceleration channel and extending generally in a chordwise aft direction from the acceleration channel to the trailing edge.

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：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.

公开(公告)号：US09856739B2

公开(公告)日：2018-01-02

申请号：US14030647

申请日：2013-09-18

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Loris Bedrosyan ,  Ardeshir Riahi ,  Daniel C. Crites

IPC: F01D5/20 ,  F01D5/18 ,  F01D11/10

CPC classification number: F01D5/20 ,  F01D5/186 ,  F01D5/187 ,  F01D11/10 ,  F05D2240/307 ,  F05D2260/20 ,  Y02T50/673 ,  Y02T50/676

Abstract: A turbine rotor blade is provided with for a turbine section of an engine that includes a shroud surrounding the rotor blade. The rotor blade includes a platform and an airfoil extending from the platform into a mainstream gas path. The airfoil includes a pressure side wall, a suction side wall joined to the pressure side wall at a leading edge and a trailing edge, a tip cap extending between the suction side wall and the pressure side wall, a first squealer tip extension extending from the pressure side wall at a first angle relative to the pressure side wall, the first squealer tip extension defining a first cooling hole that converges between an inlet and an outlet; an internal cooling circuit configured to deliver cooling air to a gap between the pressure side squealer tip extension and the shroud via the first cooling hole.

公开(公告)号：US20150354461A1

公开(公告)日：2015-12-10

申请号：US14244219

申请日：2014-04-03

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： John Meier ,  Daniel C. Crites ,  Yogendra Yogi Sheoran ,  Mark C. Morris ,  Jeff Howe ,  Ardeshir Riahi

IPC: F02C7/30 ,  F02C7/052 ,  F02C3/04 ,  F02C7/18

CPC classification number: F02C7/30 ,  F01D5/081 ,  F01D9/065 ,  F01D25/32 ,  F02C3/04 ,  F02C7/052 ,  F02C7/18 ,  F04D29/441 ,  F05D2220/32 ,  F05D2260/232 ,  F05D2260/95 ,  Y02T50/673 ,  Y02T50/676

Abstract: A cooling arrangement is provided for a gas turbine engine with a turbine section. The cooling arrangement includes a first conduit to receive cooling air that includes particles; a separator system coupled to the first conduit to receive the cooling air and configured to remove at least a portion of the particles to result in relatively clean cooling air and scavenge air including the portion of the particles; and a second conduit coupled to the separator system and configured to direct the relatively clean cooling air to the turbine section.

Abstract translation: 为具有涡轮部分的燃气涡轮发动机提供冷却装置。 该冷却装置包括用于接收包括颗粒的冷却空气的第一管道; 分离器系统，其耦合到所述第一管道以接收所述冷却空气并且被配置为移除所述颗粒的至少一部分以导致相对干净的冷却空气并且清除包括所述颗粒的所述部分的空气; 以及耦合到分离器系统并被配置为将相对干净的冷却空气引导到涡轮机部分的第二导管。