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：US20200003059A1

公开(公告)日：2020-01-02

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：US10385433B2

公开(公告)日：2019-08-20

申请号：US15071630

申请日：2016-03-16

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Christopher David Gatto ,  Jude Miller ,  Benjamin Dosland Kamrath ,  Don Mittendorf ,  Jason Smoke ,  Mark C. Morris

IPC: C22F1/10 ,  C21D1/34 ,  F01D5/02 ,  F01D5/28 ,  F04D29/32 ,  C21D1/00 ,  F04D29/02 ,  B23P15/00 ,  F01D5/06 ,  F01D5/34

Abstract: Methods for processing bonded dual alloy rotors are provided. In one embodiment, the method includes obtaining a bonded dual alloy rotor including rotor blades bonded to a hub disk. The rotor blades and hub disk are composed of different alloys. A minimum processing temperature (TDISK_PROCESS_MIN) for the hub disk and a maximum critical temperature for the rotor blades (TBLADE_MAX) is established such that TBLADE_MAX is less than TDISK_PROCESS_MIN. A differential heat treatment process is then performed during which the hub disk is heated to processing temperatures equal to or greater than TDISK_PROCESS_MIN, while at least a volumetric majority of each of the rotor blades is maintained at temperatures below TBLADE_MAX. Such a targeted differential heat treatment process enables desired metallurgical properties (e.g., precipitate hardening) to be created within the hub disk, while preserving the high temperature properties of the rotor blades and any blade coating present thereon.

公开(公告)号：US10669617B2

公开(公告)日：2020-06-02

申请号：US16529724

申请日：2019-08-01

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Christopher David Gatto ,  Jude Miller ,  Benjamin Dosland Kamrath ,  Don Mittendorf ,  Jason Smoke ,  Mark C. Morris

IPC: C22F1/10 ,  F01D5/28 ,  C21D1/34 ,  F01D5/02 ,  F04D29/02 ,  F01D5/06 ,  B23P15/00 ,  F04D29/32

Abstract: Methods for processing bonded dual alloy rotors are provided. In one embodiment, the method includes obtaining a bonded dual alloy rotor including rotor blades bonded to a hub disk. The rotor blades and hub disk are composed of different alloys. A minimum processing temperature (TDISK_PROCESS_MIN) for the hub disk and a maximum critical temperature for the rotor blades (TBLADE_MAX) is established such that TBLADE_MAX is less than TDIsK_PROCESS_MIN. A differential heat treatment process is then performed during which the hub disk is heated to processing temperatures equal to or greater than TDISK_PROCESS_MIN, while at least a volumetric majority of each of the rotor blades is maintained at temperatures below TBLADE_MAX. Such a targeted differential heat treatment process enables desired metallurgical properties (e.g., precipitate hardening) to be created within the hub disk, while preserving the high temperature properties of the rotor blades and any blade coating present thereon.

公开(公告)号：US20200140983A1

公开(公告)日：2020-05-07

申请号：US16529724

申请日：2019-08-01

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Christopher David Gatto ,  Jude Miller ,  Benjamin Dosland Kamrath ,  Don Mittendorf ,  Jason Smoke ,  Mark C. Morris

IPC: C22F1/10 ,  B23P15/00 ,  C21D1/00 ,  F01D5/06 ,  F01D5/28 ,  F04D29/02 ,  F04D29/32 ,  C21D1/42 ,  C21D11/00 ,  F01D5/02

Abstract: Methods for processing bonded dual alloy rotors are provided. In one embodiment, the method includes obtaining a bonded dual alloy rotor including rotor blades bonded to a hub disk. The rotor blades and hub disk are composed of different alloys. A minimum processing temperature (TDISK_PROCESS_MIN) for the hub disk and a maximum critical temperature for the rotor blades (TBLADE_MAX) is established such that TBLADE_MAX is less than TDISK_PROCESS_MIN. A differential heat treatment process is then performed during which the hub disk is heated to processing temperatures equal to or greater than TDISK_PROCESS_MIN, while at least a volumetric majority of each of the rotor blades is maintained at temperatures below TBLADE_MAX. Such a targeted differential heat treatment process enables desired metallurgical properties (e.g., precipitate hardening) to be created within the hub disk, while preserving the high temperature properties of the rotor blades and any blade coating present thereon.

公开(公告)号：US11230929B2

公开(公告)日：2022-01-25

申请号：US16674527

申请日：2019-11-05

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Steven Whitaker ,  Daniel Crites ,  Vighneswara Kollati ,  Mark Morris ,  Benjamin Dosland Kamrath

IPC: F01D5/18 ,  F01D9/04

Abstract: A turbine component includes a hot wall, a cold wall spaced apart from the hot wall and a conduit defined between the hot wall and the cold wall. A cooling system is defined in the conduit. The cooling system includes a plurality of cooling pins, each including a first end having a first cross-sectional area and a second end having a second cross-sectional area. Each cooling pin includes a body extending between the first end and the second end, with a pin leading edge defined along the body from the first end to the second end. The pin leading edge is defined by a first diameter and a pin trailing edge is defined by a second diameter. At least one first cooling pin has the first end coupled to the hot wall and the second end coupled to the cold wall with a fillet.

公开(公告)号：US11156116B2

公开(公告)日：2021-10-26

申请号：US16378030

申请日：2019-04-08

Applicant: HONEYWELL INTERNATIONAL INC.

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

IPC: F01D9/04 ,  F01D11/00

Abstract: A turbine nozzle for a gas turbine engine includes a plurality of nozzle segments that are configured to be assembled into a full ring such that each one of the plurality of nozzle segments is adjacent to another one of the plurality of nozzle segments. Each one of the plurality of nozzle segments includes an endwall segment and a nozzle vane. The turbine nozzle includes a feather seal interface defined by endwall segments of adjacent ones of the plurality of nozzle segments. The feather seal interface is defined along an area of reduced pressure drop through a pressure field defined between adjacent nozzle vanes of the plurality of nozzle segments to reduce leakage through the plurality of nozzle segments. The turbine nozzle includes a feather seal received within the feather seal interface that cooperates with the feather seal interface to reduce leakage through the plurality of nozzle segments.

公开(公告)号：US20210131289A1

公开(公告)日：2021-05-06

申请号：US16674527

申请日：2019-11-05

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Steven Whitaker ,  Daniel Crites ,  Vighneswara Kollati ,  Mark Morris ,  Benjamin Dosland Kamrath

IPC: F01D5/18 ,  F01D9/04

Abstract: A turbine component includes a hot wall, a cold wall spaced apart from the hot wall and a conduit defined between the hot wall and the cold wall. A cooling system is defined in the conduit. The cooling system includes a plurality of cooling pins, each including a first end having a first cross-sectional area and a second end having a second cross-sectional area. Each cooling pin includes a body extending between the first end and the second end, with a pin leading edge defined along the body from the first end to the second end. The pin leading edge is defined by a first diameter and a pin trailing edge is defined by a second diameter. At least one first cooling pin has the first end coupled to the hot wall and the second end coupled to the cold wall with a fillet.

公开(公告)号：US20180283182A1

公开(公告)日：2018-10-04

申请号：US15475597

申请日：2017-03-31

Applicant: HONEYWELL INTERNATIONAL INC.

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

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F01D5/18 ,  F05D2220/323 ,  F05D2240/30 ,  F05D2250/18 ,  F05D2250/60 ,  F05D2260/20 ,  F05D2260/2212 ,  F05D2260/22141 ,  F05D2260/607 ,  Y02T50/676

Abstract: A turbine component with shaped cooling pins is provided. The turbine component includes at least one cooling circuit defined within the turbine component, the at least one cooling circuit in fluid communication with a source of a cooling fluid. The turbine component includes at least one shaped cooling pin disposed in the at least one 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 upstream in the cooling fluid and the minor diameter is less than the major diameter.

公开(公告)号：US20210372289A1

公开(公告)日：2021-12-02

申请号：US17444754

申请日：2021-08-10

Applicant: HONEYWELL INTERNATIONAL INC.

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

IPC: F01D9/04 ,  F01D11/00

Abstract: A turbine nozzle for a gas turbine engine includes a plurality of nozzle segments that are configured to be assembled into a full ring such that each one of the plurality of nozzle segments is adjacent to another one of the plurality of nozzle segments. Each one of the plurality of nozzle segments includes an endwall segment and a nozzle vane. The turbine nozzle includes a feather seal interface defined by endwall segments of adjacent ones of the plurality of nozzle segments. The feather seal interface is defined along an area of reduced pressure drop through a pressure field defined between adjacent nozzle vanes of the plurality of nozzle segments to reduce leakage through the plurality of nozzle segments. The turbine nozzle includes a feather seal received within the feather seal interface that cooperates with the feather seal interface to reduce leakage through the plurality of nozzle segments.