公开(公告)号：US10662792B2

公开(公告)日：2020-05-26

申请号：US15113116

申请日：2015-01-29

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Meggan Harris ,  Alexander W. Williams ,  Sheree R. Swenson-Dodge

IPC: F01D9/06 ,  F01D9/04 ,  F01D25/00 ,  F01D25/12

Abstract: A cooling arrangement for a turbine engine includes a cooling source and first and second structures. A ceramic-based composite cooling tube fluidly provides a fluid connection between the first and second structures. The cooling tube is configured to transfer a cooling fluid from the cooling source to the second structure.

公开(公告)号：US10598382B2

公开(公告)日：2020-03-24

申请号：US14935076

申请日：2015-11-06

Applicant: United Technologies Corporation

Inventor： John S. Tu ,  James B. Hoke ,  Monica Pacheco-Tougas ,  Alexander W. Williams

IPC: F23R3/16 ,  F23R3/00 ,  F23R3/06 ,  F23M5/08 ,  B64D27/10 ,  F02C7/18

Abstract: A liner associated with an engine of an aircraft is described. The liner includes a panel and an array of projections configured to enhance a cooling of the panel and distributed on at least part of a first side of the panel that corresponds to a cold side of the panel.

公开(公告)号：US10101031B2

公开(公告)日：2018-10-16

申请号：US14911205

申请日：2014-06-30

Applicant: United Technologies Corporation

Inventor： Alexander W. Williams ,  Seth A. Max ,  Christopher B. Lyons

IPC: F23R3/60 ,  F23R3/12 ,  F23R3/14 ,  F23R3/28

Abstract: A swirler for a combustor of a gas turbine engine includes a swirler outer body with a male snap component and/or female snap component of a snap-fit interface defined around a swirler central longitudinal axis. A bulkhead assembly for a combustor of a gas turbine engine includes a swirler mounted to a bulkhead support shell through a snap-fit interface.

公开(公告)号：US10060631B2

公开(公告)日：2018-08-28

申请号：US14911158

申请日：2014-08-29

Applicant: United Technologies Corporation

Inventor： Christopher B. Lyons ,  Alexander W. Williams ,  Alexander Broulidakis

IPC: F23R3/00 ,  F23R3/60 ,  F02C3/14 ,  F01D25/16 ,  F01D25/24 ,  F01D9/04 ,  F02C7/20 ,  F23R3/04 ,  F04D29/54

CPC classification number: F23R3/60 ,  F01D9/041 ,  F01D25/162 ,  F01D25/24 ,  F01D25/243 ,  F02C3/14 ,  F02C7/20 ,  F04D29/54 ,  F04D29/542 ,  F23R3/04 ,  Y02T50/671 ,  Y02T50/675

Abstract: A hybrid diffuser case for a gas turbine engine includes an outer diffuser case wall that extends downstream from an annular outer pre-diffuser case shroud. An inner diffuser case wall extends downstream from an annular inner pre-diffuser case shroud. A multiple of struts extend between the annular outer pre-diffuser case shroud and the annular inner pre-diffuser case shroud.

公开(公告)号：US20160341054A1

公开(公告)日：2016-11-24

申请号：US15113116

申请日：2015-01-29

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Meggan Harris ,  Alexander W. Williams ,  Sheree R. Swenson-Dodge

IPC: F01D9/06 ,  F01D25/00 ,  F01D9/04 ,  F01D25/12

Abstract: A cooling arrangement for a turbine engine includes a cooling source and first and second structures. A ceramic-based composite cooling tube fluidly provides a fluid connection between the first and second structures. The cooling tube is configured to transfer a cooling fluid from the cooling source to the second structure.

Abstract translation: 涡轮发动机的冷却装置包括冷却源和第一和第二结构。 基于陶瓷的复合冷却管在第一和第二结构之间流体地提供流体连接。 冷却管构造成将冷却流体从冷却源传递到第二结构。

公开(公告)号：US20160195275A1

公开(公告)日：2016-07-07

申请号：US14911158

申请日：2014-08-29

Applicant: United Technologies Corporation

Inventor： Christopher B. Lyons ,  Alexander W. Williams ,  Alexander Broulidakis

IPC: F23R3/60 ,  F01D25/24 ,  F02C3/14

CPC classification number: F23R3/60 ,  F01D9/041 ,  F01D25/162 ,  F01D25/24 ,  F01D25/243 ,  F02C3/14 ,  F02C7/20 ,  F04D29/54 ,  F04D29/542 ,  F23R3/04 ,  Y02T50/671 ,  Y02T50/675

Abstract: A hybrid diffuser case for a gas turbine engine includes an outer diffuser case wall that extends downstream from an annular outer pre-diffuser case shroud. An inner diffuser case wall extends downstream from an annular inner pre-diffuser case shroud. A multiple of struts extend between the annular outer pre-diffuser case shroud and the annular inner pre-diffuser case shroud.

Abstract translation: 用于燃气涡轮发动机的混合式扩散器壳体包括从环形外部预扩散器壳体护罩的下游延伸的外部扩散器壳体壁。 内部扩散器壳壁从环形内部预扩散器壳体护罩的下游延伸。 多个支柱在环形外部预扩散器壳体护罩和环形内部预扩散器壳体护罩之间延伸。

公开(公告)号：US20140173896A1

公开(公告)日：2014-06-26

申请号：US13723542

申请日：2012-12-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Brian S. Tryon ,  Kevin Joseph Low ,  James P. Bangerter ,  Russell A. Beers ,  Alexander W. Williams

IPC: B05C13/02

CPC classification number: B05B13/0285 ,  B05C13/02 ,  B22D19/00 ,  C23C4/12 ,  Y10T29/49234

Abstract: A method for coating a turbine engine component comprises the steps of: providing a turbine engine component having at least one sacrificial attachment on a first side; grasping the turbine engine component via the at least one sacrificial attachment to position a first surface of the turbine engine component relative to a source of coating material; and applying a coating to said first side.

Abstract translation: 用于涂覆涡轮发动机部件的方法包括以下步骤：提供在第一侧上具有至少一个牺牲附件的涡轮发动机部件; 通过所述至少一个牺牲附件来抓住所述涡轮发动机部件，以相对于涂料源定位所述涡轮发动机部件的第一表面; 以及向所述第一侧施加涂层。