公开(公告)号：US20160319666A1

公开(公告)日：2016-11-03

申请号：US14701262

申请日：2015-04-30

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Eric Blumer ,  David K. Jan ,  Jason Smoke ,  Robbie Joseph Adams ,  Harry Lester Kington

IPC: F01D5/06 ,  F04D29/60 ,  F04D29/32 ,  F01D5/04 ,  F04D29/28

CPC classification number: F01D5/066 ,  B22F3/1055 ,  B22F3/15 ,  B22F5/009 ,  B22F2998/10 ,  B22F2999/00 ,  B23P15/006 ,  F01D5/04 ,  F01D5/3061 ,  F01D5/34 ,  F04D29/284 ,  F04D29/321 ,  F04D29/322 ,  F04D29/329 ,  F04D29/601 ,  F04D29/644 ,  F05D2220/32 ,  F05D2230/10 ,  F05D2230/23 ,  F05D2230/31 ,  Y02P10/295 ,  Y02T50/671 ,  B22F7/062 ,  B22F7/08 ,  B22F2207/01

Abstract: Bladed Gas Turbine Engine (GTE) rotors including deposited transition rings are provided, as are embodiments of methods for manufacturing bladed GTE rotors. In one embodiment, the method includes providing an outer blade ring having an inner circumferential surface defining a central opening, and depositing a deposited transition ring on the inner circumferential surface of the outer blade ring. The outer blade ring can be a full bladed ring or an annular grouping of individually-fabricated bladed pieces. After deposition of the transition ring, a hub disk is inserted into the central opening such that the transition ring extends around an outer circumferential surface of the hub disk. The transition ring is then bonded to the outer circumferential surface of the hub disk utilizing, for example, a hot isostatic pressing technique to join the transition ring and the outer blade ring thereto.

Abstract translation: 提供了包括沉积的过渡环的叶片燃气轮机发动机（GTE）转子，如用于制造叶片GTE转子的方法的实施例。 在一个实施例中，该方法包括提供具有限定中心开口的内周表面的外部叶片环，以及在外部叶片环的内圆周表面上沉积沉积的过渡环。 外刀片环可以是全刀片环或单独制造的刀片的环形组。 在沉积过渡环之后，毂盘插入中心开口中，使得过渡环围绕毂盘的外周表面延伸。 然后使用例如热等静压技术将过渡环接合到轮毂盘的外周面，以将过渡环和外刀环连接到其上。

公开(公告)号：US12091980B1

公开(公告)日：2024-09-17

申请号：US18538434

申请日：2023-12-13

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Jason Smoke ,  Courtney Murphy ,  Timothy Darling ,  William Weiss ,  Jeffrey Aitchison ,  Harry Kington

IPC: F01D11/18 ,  F01D25/24

CPC classification number: F01D11/18 ,  F01D25/246 ,  F05D2240/14 ,  F05D2260/38

Abstract: A system for coupling a shroud to a case associated with a gas turbine engine includes the case having a mounting pad, and the shroud having a surface that faces the case. The system includes a load spreader having a spreader surface in contact with the surface of the shroud and a locator pin coupled to the mounting pad and the load spreader to couple the shroud to the case. The system includes a load spreader retainer coupled to the load spreader. The load spreader retainer is to distribute a force to the load spreader. The system includes a biasing system coupled about the mounting pad that includes a spring arm configured to apply the force to the load spreader retainer to maintain the spreader surface of the load spreader in contact with the surface of the shroud.

公开(公告)号：US11506060B1

公开(公告)日：2022-11-22

申请号：US17305828

申请日：2021-07-15

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Paul Kurlak ,  Ardeshir Riahi ,  Benjamin D. Kamrath ,  Jason Smoke ,  John McClintic

IPC: F01D11/00 ,  F01D5/20 ,  F01D5/06 ,  F01D5/14

Abstract: A radial turbine rotor associated with an engine includes a disk, and a plurality of blades spaced apart about a perimeter of the disk. Each blade includes a forward end, an aft end and a root. The radial turbine rotor includes a plurality of sectors, with each sector coupled to the root of a respective blade of the plurality of blades. Each sector of the plurality of sectors defines a first surface configured to contact a working fluid and a second surface configured to be coupled to the disk, and each sector of the plurality of sectors defines at least one pocket between the first surface and the second surface proximate the forward end that extends toward the aft end. The radial turbine rotor includes a feather seal slot defined between adjacent sectors of the plurality of sectors proximate the first surface.

公开(公告)号：US20200182471A1

公开(公告)日：2020-06-11

申请号：US16736199

申请日：2020-01-07

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Jason Smoke ,  David K. Jan ,  Mark Matwey

IPC: F23R3/42 ,  F02C7/18 ,  F23R3/26 ,  F02C3/04 ,  F01D25/12 ,  F01D11/08 ,  F01D9/02 ,  F23R3/52

Abstract: A gas turbine engine includes a compressor section and a combustion section with a scroll, a scroll baffle, a combustor, and a combustor case. The scroll defines an interior scroll flow path. The scroll baffle surrounds the scroll to define a scroll cooling passage. The combustor case surrounds the combustor and the scroll baffle to define a collector space. Moreover, the engine includes a turbine section with a turbine rotor and a turbine rotor blade shroud that includes a shroud cooling passage. The compressor flow path is fluidly connected to the scroll for cooling the scroll. Also, the scroll cooling passage is fluidly connected to the shroud cooling passage for cooling the turbine rotor blade shroud. Furthermore, the shroud cooling passage is fluidly connected to the collector space. Flow from the collector space flows into the combustor, along the interior scroll flow path, toward the turbine rotor.

公开(公告)号：US10677084B2

公开(公告)日：2020-06-09

申请号：US15899756

申请日：2018-02-20

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Jason Smoke ,  Kent L. Kime ,  Blake Petersen ,  Luke Zurmehly

IPC: F01D11/08 ,  F01D25/12 ,  F01D9/04 ,  F01D11/00 ,  F01D25/24 ,  F01D11/12

Abstract: A shroud assembly for a gas turbine engine includes a plurality of shroud segments that are attached to a shroud support with an inter-segment joint defined between shroud segments. The shroud assembly also includes a cooling flow path cooperatively defined by the shroud support and the first shroud segment. The cooling flow path includes an internal cooling passage within the shroud segments. The cooling flow path includes an outlet chamber configured to receive flow from the internal cooling passage. The shroud assembly additionally includes a seal arrangement that extends across the inter-segment joint. The seal arrangement, the first shroud segment, and the second shroud segment cooperatively define a seal chamber that is enclosed.

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：US10399176B2

公开(公告)日：2019-09-03

申请号：US15648577

申请日：2017-07-13

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Amandine Miner ,  David K. Jan ,  Don Mittendorf ,  Jason Smoke

IPC: F01D5/30 ,  B23K1/00 ,  B23K20/02 ,  B23K31/02 ,  B23P15/00 ,  B23K20/14 ,  B23K20/22 ,  B23K20/26 ,  F01D5/34 ,  B23K101/00 ,  B23K20/00

Abstract: Dual alloy turbine rotors and methods for manufacturing the same are provided. The dual alloy turbine rotor comprises an assembled blade ring and a hub bonded to the assembled blade ring. The assembled blade ring comprises a first alloy selected from the group consisting of a single crystal alloy, a directionally solidified alloy, or an equi-axed alloy. The hub comprises a second alloy. The method comprises positioning a hub within a blade ring to define an interface between the hub and the blade ring. The interface is a non-contacting interface or a contacting interface. The interface is enclosed by a pair of diaphragms. The interface is vacuum sealed. The blade ring is bonded to the hub after the vacuum sealing step.

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：US20190022781A1

公开(公告)日：2019-01-24

申请号：US15811862

申请日：2017-11-14

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Bradley Reed Tucker ,  Ardeshir Riahi ,  Jason Smoke ,  Ed Zurmehly

IPC: B23K1/00 ,  F01D9/04 ,  B23P15/00 ,  B22D19/04 ,  B22D19/00

Abstract: Methods for manufacturing a turbine nozzle are provided. A plurality of nozzle segments is formed. Each nozzle segment comprises an endwall ring portion with at least one vane. The plurality of nozzle segments are connected to an annular endwall forming a segmented annular endwall concentric to the annular endwall with the at least one vane of each nozzle segment extending between the segmented annular endwall and the annular endwall.

公开(公告)号：US09938834B2

公开(公告)日：2018-04-10

申请号：US14701262

申请日：2015-04-30

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Eric Blumer ,  David K. Jan ,  Jason Smoke ,  Robbie Joseph Adams ,  Harry Lester Kington

IPC: F01D5/06 ,  B22F3/105 ,  B22F3/15 ,  B23P15/00 ,  F01D5/30 ,  F01D5/34 ,  F01D5/04 ,  F04D29/28 ,  F04D29/32 ,  F04D29/60 ,  F04D29/64

CPC classification number: F01D5/066 ,  B22F3/1055 ,  B22F3/15 ,  B22F5/009 ,  B22F2998/10 ,  B22F2999/00 ,  B23P15/006 ,  F01D5/04 ,  F01D5/3061 ,  F01D5/34 ,  F04D29/284 ,  F04D29/321 ,  F04D29/322 ,  F04D29/329 ,  F04D29/601 ,  F04D29/644 ,  F05D2220/32 ,  F05D2230/10 ,  F05D2230/23 ,  F05D2230/31 ,  Y02P10/295 ,  Y02T50/671 ,  B22F7/062 ,  B22F7/08 ,  B22F2207/01

Abstract: Bladed Gas Turbine Engine (GTE) rotors including deposited transition rings are provided, as are embodiments of methods for manufacturing bladed GTE rotors. In one embodiment, the method includes providing an outer blade ring having an inner circumferential surface defining a central opening, and depositing a deposited transition ring on the inner circumferential surface of the outer blade ring. The outer blade ring can be a full bladed ring or an annular grouping of individually-fabricated bladed pieces. After deposition of the transition ring, a hub disk is inserted into the central opening such that the transition ring extends around an outer circumferential surface of the hub disk. The transition ring is then bonded to the outer circumferential surface of the hub disk utilizing, for example, a hot isostatic pressing technique to join the transition ring and the outer blade ring thereto.