公开(公告)号：US20230271150A1

公开(公告)日：2023-08-31

申请号：US17931441

申请日：2022-09-12

Applicant: Honeywell International Inc.

Inventor： Stephen Yates ,  Amanda Childers ,  Mehrad Mehr ,  Jeffrey Spencer ,  Jason Smoke ,  Abigail Parsons

IPC: B01J6/00 ,  C01B3/24

CPC classification number: B01J6/008 ,  C01B3/24 ,  C01B2203/0272 ,  C01B2203/1241

Abstract: A thermal process system includes a retort assembly, a heating assembly, and a vessel housing. The retort assembly includes a retort chamber and is configured to substantially form a containment boundary to contain one or more gases in the retort chamber during a thermal process. The heating assembly includes one or more heating elements and is configured to heat the retort chamber. The vessel housing is positioned around the retort chamber and the one or more heating elements and configured to form a pressure boundary to maintain a pressure within the retort chamber and reduce a pressure across the retort chamber.

公开(公告)号：US20210041104A1

公开(公告)日：2021-02-11

申请号：US17028559

申请日：2020-09-22

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Nagaraja S. Rudrapatna ,  Ian Critchley ,  Jeffrey Spencer ,  Philip Smalley

IPC: F23R3/06

Abstract: A liner for a combustor includes a first wall and a second wall extending around at least a portion of the first wall to form a liner cavity with the first wall. The first wall defines a first wall orifice and the second wall defines a second wall orifice. The liner further includes a first insert mounted on the second wall within the second wall orifice and extending through the first wall orifice. The first insert is configured to direct a first air jet through the second wall and the first wall. The first insert is formed by a tubular body portion extending through the first wall orifice and the second wall orifice, and a shoulder extending around the body portion that abuts the first side of the second wall. The shoulder has a first diameter and the first wall orifice has a second diameter, greater than the first diameter.

公开(公告)号：US11326781B2

公开(公告)日：2022-05-10

申请号：US17028559

申请日：2020-09-22

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Nagaraja S. Rudrapatna ,  Ian Critchley ,  Jeffrey Spencer ,  Philip Smalley

IPC: F23R3/06 ,  F23R3/00 ,  F23R3/50

Abstract: A liner for a combustor includes a first wall and a second wall extending around at least a portion of the first wall to form a liner cavity with the first wall. The first wall defines a first wall orifice and the second wall defines a second wall orifice. The liner further includes a first insert mounted on the second wall within the second wall orifice and extending through the first wall orifice. The first insert is configured to direct a first air jet through the second wall and the first wall. The first insert is formed by a tubular body portion extending through the first wall orifice and the second wall orifice, and a shoulder extending around the body portion that abuts the first side of the second wall. The shoulder has a first diameter and the first wall orifice has a second diameter, greater than the first diameter.

公开(公告)号：US11022308B2

公开(公告)日：2021-06-01

申请号：US15993986

申请日：2018-05-31

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Nagaraja S. Rudrapatna ,  Ian Critchley ,  Jeffrey Spencer ,  Philip Smalley

IPC: F23R3/06 ,  F23R3/00 ,  F23R3/50

Abstract: A combustor for a turbine engine includes a first liner and a second liner forming a combustion chamber with the first liner. The combustion chamber is configured to receive an air-fuel mixture for combustion therein. The first liner is a first double wall liner with a first wall forming a portion of the combustion chamber and a second wall extending around at least a portion of the first wall to form a liner cavity with the first wall. The first wall defines a first wall orifice and the second wall defines a second wall orifice. The combustor further includes a first insert mounted on the second wall within the second wall orifice and extending through the first wall orifice. The first insert is configured to direct a first air jet through the second wall, through the first wall, and into the combustion chamber.