公开(公告)号：US20160169512A1

公开(公告)日：2016-06-16

申请号：US14939619

申请日：2015-11-12

Applicant: United Technologies Corporation

Inventor： John S. Tu ,  Steven W. Burd

IPC: F23M5/08 ,  F23R3/06 ,  F23R3/00

Abstract: A wall assembly that may be for a combustor of a gas turbine engine includes a liner having a hot face that defines a combustion chamber, an opposite cold face, and a plurality of effusion holes. A shell of the assembly is spaced outward from the cold face and includes a plurality of impingement holes each having a centerline orientated substantially normal to the cold face. A plurality of cooling member arrays of the liner each include a first plurality of members that may be pins projecting outward from the cold face to conduct heat out of the liner. Each array is spaced between adjacent effusion holes and is symmetrically orientated about the respective centerline.

Abstract translation: 可用于燃气涡轮发动机的燃烧器的壁组件包括具有限定燃烧室，相对冷面和多个渗出孔的热面的衬套。 组件的壳体与冷面相隔一定距离，并且包括多个冲击孔，每个冲击孔具有基本垂直于冷面的中心线。 衬套的多个冷却构件阵列各自包括第一多个构件，其可以是从冷面向外突出的销，以将热量传导出衬套。 每个阵列在相邻的渗出孔之间隔开并且围绕相应的中心线对称定向。

公开(公告)号：US20140165585A1

公开(公告)日：2014-06-19

申请号：US13717232

申请日：2012-12-17

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Steven W. Burd

IPC: F02C7/22

CPC classification number: F23R3/28 ,  F05D2260/14 ,  F23R3/10 ,  F23R3/12 ,  F23R3/14 ,  F23R3/286 ,  Y02T50/675

Abstract: In accordance with one aspect of the disclosure, a swirler is disclosed. The swirler may include an outer shroud and inner shroud. The inner shroud may be positioned radially inside the outer shroud. At least one of the outer shroud and inner shroud may have a major diameter which is larger than a minor diameter such that the shrouds define an oblong shape. The swirler may further include a plurality of vanes which may be positioned between the inner and outer shrouds.

Abstract translation: 根据本公开的一个方面，公开了一种旋流器。 旋流器可以包括外护罩和内护罩。 内护罩可以位于外护罩的径向内侧。 外护罩和内护罩中的至少一个可以具有大于小直径的大直径，使得护罩限定长方形。 旋流器还可以包括可以位于内护罩和外护罩之间的多个叶片。

公开(公告)号：US20140165578A1

公开(公告)日：2014-06-19

申请号：US13717203

申请日：2012-12-17

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Steven W. Burd

IPC: F02G3/00

CPC classification number: F02G3/00 ,  F23R3/14 ,  F23R3/28 ,  F23R3/286 ,  Y02T50/675 ,  Y10T137/2087

Abstract: In accordance with one aspect of the disclosure, a swirler is disclosed. The swirler may include an outer shroud and inner shroud. The inner shroud may be positioned radially inside the outer shroud. At least one of the outer shroud and inner shroud may have a major diameter greater than that of a minor diameter such that the shrouds define an ovate shape. The swirler may further include a plurality of vanes which may be positioned between the inner and outer shrouds.

Abstract translation: 根据本公开的一个方面，公开了一种旋流器。 旋流器可以包括外护罩和内护罩。 内护罩可以位于外护罩的径向内侧。 外护罩和内护罩中的至少一个可以具有大于小直径的大直径，使得护罩限定卵形。 旋流器还可以包括可以位于内护罩和外护罩之间的多个叶片。

公开(公告)号：US20140147271A1

公开(公告)日：2014-05-29

申请号：US13688340

申请日：2012-11-29

Applicant: United Technologies Corporation

Inventor： Steven W. Burd

IPC: F01D11/00

CPC classification number: F01D11/02 ,  F01D11/005 ,  F05D2220/32 ,  F05D2240/55 ,  F05D2300/432 ,  F16J15/447 ,  F16J15/54 ,  Y02T50/672

Abstract: A gas turbine engine has a pair of components having a high-pressure chamber on one side, and a low pressure chamber on an opposed side. A three-sided seal has one side in sealing contact with each of said components. A third side is associated with a third component. At least one non-metallic wear surface is positioned between one of the three sides of the seal and its respective component.

Abstract translation: 一种燃气涡轮发动机具有一对在一侧具有高压室的部件和在相对侧的低压室。 三面密封件具有与每个所述部件密封接触的一侧。 第三侧与第三组件相关联。 至少一个非金属磨损表面位于密封件的三个侧面之一和其相应的部件之间。

公开(公告)号：US10132498B2

公开(公告)日：2018-11-20

申请号：US14601037

申请日：2015-01-20

Applicant: United Technologies Corporation

Inventor： Steven W. Burd

IPC: F23R3/04 ,  F23R3/00 ,  F23R3/06 ,  F23R3/50

Abstract: Aspects of the disclosure are directed to a liner associated with a combustor of an aircraft engine, comprising: a thermal barrier coating, and a base metal, wherein the thermal barrier coating comprises a contoured surface on a flowpath side proximate to an exit of a hole formed by the thermal barrier coating and the base metal.

公开(公告)号：US20180231251A1

公开(公告)日：2018-08-16

申请号：US15432098

申请日：2017-02-14

Applicant: United Technologies Corporation

Inventor： Steven W. Burd

IPC: F23R3/00

Abstract: A combustor for a gas turbine engine including a combustor liner support shell with a furrow formed therein; a forward liner panel mounted to the support shell via a multiple of studs, the forward liner panel including a forward liner panel rail the extends into the furrow; and an aft liner panel mounted to the support shell via a multiple of studs downstream of the forward liner panel, the aft liner panel including an aft liner panel rail that extends into the furrow.

公开(公告)号：US10030583B2

公开(公告)日：2018-07-24

申请号：US14759774

申请日：2013-11-06

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Steven W. Burd

IPC: F02C7/266 ,  F23R3/00 ,  F23C99/00

Abstract: An ignition system for a combustor of a gas turbine engine is disclosed. The ignition system may include an igniter operatively associated with the combustor, and an electrode operatively associated with the combustor and spaced from the igniter, wherein an electrical potential is created between the igniter and the electrode to produce an electric arc therebetween.

公开(公告)号：US20160312741A1

公开(公告)日：2016-10-27

申请号：US15105117

申请日：2014-12-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Steven W. Burd

IPC: F02K3/075 ,  F01D25/02 ,  F04D29/52 ,  F04D29/54 ,  F02C3/04 ,  F02K3/06

CPC classification number: F02K3/075 ,  F01D25/02 ,  F02C3/04 ,  F02C7/047 ,  F02C7/057 ,  F02K3/06 ,  F04D29/522 ,  F04D29/541 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2270/17

Abstract: The present disclosure relates generally to a system for fan nacelle inlet flow control in a gas turbine engine, the nacelle comprising a nacelle inlet cowl including an inlet lip disposed at a leading edge of the nacelle inlet cowl, an inner surface extending aft from the inlet lip, and an outer surface extending aft from the inlet lip and positioned radially outward of the inner surface; and at least one flow control passage extending through the nacelle inlet cowl, each of the at least one flow control passage including a flow control passage inlet, disposed on the inlet lip, and a flow control passage outlet; wherein air may flow into the flow control passage inlet, through the flow control passage, and exits the flow control passage outlet.

Abstract translation: 本公开总体上涉及一种用于燃气涡轮发动机中的风扇机舱入口流量控制的系统，所述机舱包括机舱入口罩，其包括设置在所述机舱进气罩的前缘处的入口唇缘，从所述入口向后延伸的内表面 唇缘和从入口唇缘向后延伸并且位于内表面的径向外侧的外表面; 以及延伸穿过所述机舱进气罩的至少一个流量控制通道，所述至少一个流量控制通道中的每一个包括设置在所述入口唇缘上的流量控制通道入口和流量控制通道出口; 其中空气可以通过流量控制通道流入流量控制通道入口，并且离开流量控制通道出口。

公开(公告)号：US20160131364A1

公开(公告)日：2016-05-12

申请号：US14935146

申请日：2015-11-06

Applicant: United Technologies Corporation

Inventor： Steven W. Burd

IPC: F23R3/06 ,  F23R3/00 ,  B23P15/00

Abstract: Aspects of the disclosure are directed to a method for forming a cooling circuit in at least one of a combustor panel or liner wall of an aircraft engine. The method includes producing a substrate with the cooling circuit formed in the substrate, where the cooling circuit is located in proximity to an aperture associated with the at least one of a panel or liner wall.

Abstract translation: 本公开的方面涉及在飞机发动机的燃烧器板或衬套壁中的至少一个中形成冷却回路的方法。 该方法包括：在衬底中形成有冷却回路的衬底，其中冷却回路位于与面板或衬套壁中的至少一个相关联的孔附近。

公开(公告)号：US20160069567A1

公开(公告)日：2016-03-10

申请号：US14849017

申请日：2015-09-09

Applicant: United Technologies Corporation

Inventor： Steven W. Burd

IPC: F23R3/00

Abstract: A single-walled combustor includes a multi-layered wall having a first face defining a cooling plenum and an opposite second face. A thermal barrier coating of the wall may be secured to the second face and defines at least in-part a combustion chamber. A plurality of cooling circuits each extend through the base layer and the thermal barrier coating for flowing cooling air from the plenum and into the combustion chamber. Each circuit includes a first surface recessed from the second face and spaced from the thermal barrier coating with a channel defined in-part by the first surface and covered by the thermal barrier coating. A hole in the thermal barrier coating is in fluid communication between the channel and the combustion chamber. A method of manufacturing the circuit includes fabricating the base layer with the aperture and hole; then placing an insert into the channel prior to application of the coating over the base layer and insert. The insert is then removed and the film cooling hole is formed through the coating.

Abstract translation: 单壁燃烧器包括具有限定冷却气室和相对的第二面的第一面的多层壁。 壁的隔热涂层可以固定到第二面并且至少部分地限定燃烧室。 多个冷却回路各自延伸穿过基层和热障涂层，用于使冷却空气从气室流入燃烧室。 每个电路包括从第二面凹陷并且与隔热涂层间隔开的第一表面，其具有由第一表面部分限定并被热障涂层覆盖的通道。 热障涂层中的孔在通道和燃烧室之间流体连通。 一种制造该电路的方法包括：制备具有孔和孔的基层; 然后在将涂层涂覆在基层上并插入之前将插入物放入通道中。 然后移除插入物，并通过涂层形成膜冷却孔。