公开(公告)号：US20140190171A1

公开(公告)日：2014-07-10

申请号：US13738619

申请日：2013-01-10

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Ian Critchley ,  Stony Kujala ,  Eduardo Guerra

IPC: F23R3/00

CPC classification number: F23R3/002 ,  F23R3/005 ,  F23R3/045 ,  F23R3/06 ,  F23R2900/00012 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

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 and has a longitudinal axis that defines axial, radial and circumferential directions. The first liner is a first dual walled liner having a first hot wall facing the combustion chamber and a first cold wall that forms a first liner cavity with the first hot wall. The combustor further includes a primary air admission hole defined in the first hot wall and a first fixed liner seal between the first hot wall and the first cold wall proximate to the primary air admission hole.

Abstract translation: 用于涡轮发动机的燃烧器包括第一衬套和形成具有第一衬套的燃烧室的第二衬套。 燃烧室被配置为容纳用于在其中燃烧的空气 - 燃料混合物，并且具有限定轴向，径向和圆周方向的纵向轴线。 第一衬垫是具有面向燃烧室的第一热壁的第一双壁衬套和与第一热壁形成第一衬里腔的第一冷壁。 燃烧器还包括限定在第一热壁中的一次进气孔和在第一热壁和靠近一次进气孔的第一冷壁之间的第一固定衬套密封。

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.

公开(公告)号：US09631814B1

公开(公告)日：2017-04-25

申请号：US14161941

申请日：2014-01-23

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Michael T. Todd Barton ,  Samir Rida ,  Ian Critchley

IPC: F23R3/10 ,  F23R3/28

CPC classification number: F23R3/10 ,  F01D5/142 ,  F01D9/041 ,  F02C3/08 ,  F02C3/14 ,  F02C7/222 ,  F04D29/444 ,  F05D2250/52 ,  F23R3/28 ,  F23R3/50 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/675

Abstract: An engine assembly includes a compressor section configured to supply compressed air and a combustion section coupled to the compressor section. The compressor section includes a diffuser with diffuser vanes to condition the compressed air, and the diffuser vanes have a vane count of a first value. The combustion section includes a combustion chamber to receive the compressed air and fuel injection assemblies configured to introduce fuel into the combustion chamber. The fuel injection assemblies have a fuel injection assembly count of a second value, and the first value is a whole number multiple of the second value.