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：US20180156054A1

公开(公告)日：2018-06-07

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

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：US20210003023A1

公开(公告)日：2021-01-07

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

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：US10683763B2

公开(公告)日：2020-06-16

申请号：US15285347

申请日：2016-10-04

Applicant: HONEYWELL INTERNATIONAL INC.

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

IPC: F01D5/18 ,  F01D5/08

Abstract: A turbine blade with an integral flow meter is provided. The turbine blade includes a trailing edge and a leading edge opposite the trailing edge. The turbine blade includes at least one cooling passage defined internally within the turbine blade, and the at least one cooling passage is in fluid communication with a source of cooling fluid via an inlet to receive a cooling fluid. The turbine blade also includes at least one flow meter formed within the turbine blade at the inlet that supplies the cooling fluid to the at least one cooling passage.

公开(公告)号：US20180094527A1

公开(公告)日：2018-04-05

申请号：US15285347

申请日：2016-10-04

Applicant: HONEYWELL INTERNATIONAL INC.

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

IPC: F01D5/18

Abstract: A turbine blade with an integral flow meter is provided. The turbine blade includes a trailing edge and a leading edge opposite the trailing edge. The turbine blade includes at least one cooling passage defined internally within the turbine blade, and the at least one cooling passage is in fluid communication with a source of cooling fluid via an inlet to receive a cooling fluid. The turbine blade also includes at least one flow meter formed within the turbine blade at the inlet that supplies the cooling fluid to the at least one cooling passage.

公开(公告)号：US20240417095A1

公开(公告)日：2024-12-19

申请号：US18532222

申请日：2023-12-07

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Alexandre Guerinot ,  Jude Miller ,  Nicholas Hemans

IPC: B64D35/025

Abstract: An electromechanically controlled aircraft power transmission system includes a first planetary gear set, a first gas turbine engine, a first electric machine, a second planetary gear set, a second gas turbine engine, a second electric machine, a propulsor shaft, and at least one propulsor. The first gas turbine engine is coupled to the first planetary gear set. The first electric machine is coupled to the first planetary gear set and is configured vary the gear ratio of the first planetary gear set. The second gas turbine engine is coupled to the second planetary gear set. The second electric machine is coupled to the second planetary gear set and is configured to vary the gear ratio of the second planetary gear set. The propulsor shaft is coupled to the first and second planetary gear sets and the at least one propulsor is coupled to the propulsor shaft.

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：US12179933B1

公开(公告)日：2024-12-31

申请号：US18532222

申请日：2023-12-07

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Alexandre Guerinot ,  Jude Miller ,  Nicholas Hemans

IPC: B64D35/02 ,  B64D35/025

Abstract: An electromechanically controlled aircraft power transmission system includes a first planetary gear set, a first gas turbine engine, a first electric machine, a second planetary gear set, a second gas turbine engine, a second electric machine, a propulsor shaft, and at least one propulsor. The first gas turbine engine is coupled to the first planetary gear set. The first electric machine is coupled to the first planetary gear set and is configured vary the gear ratio of the first planetary gear set. The second gas turbine engine is coupled to the second planetary gear set. The second electric machine is coupled to the second planetary gear set and is configured to vary the gear ratio of the second planetary gear set. The propulsor shaft is coupled to the first and second planetary gear sets and the at least one propulsor is coupled to the propulsor shaft.

公开(公告)号：US10851660B2

公开(公告)日：2020-12-01

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 ,  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.