公开(公告)号：US20200318488A1

公开(公告)日：2020-10-08

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：US10563520B2

公开(公告)日：2020-02-18

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

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：US20170268089A1

公开(公告)日：2017-09-21

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 ,  F01D5/02 ,  F04D29/32

CPC classification number: C22F1/10 ,  B23P15/006 ,  C21D1/42 ,  C21D11/00 ,  F01D5/02 ,  F01D5/063 ,  F01D5/28 ,  F01D5/286 ,  F01D5/34 ,  F04D29/023 ,  F04D29/321 ,  F04D29/322 ,  F05D2220/32 ,  F05D2230/211 ,  F05D2230/40 ,  F05D2230/41 ,  F05D2230/42 ,  F05D2300/17 ,  F05D2300/175 ,  F05D2300/606

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.