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公开(公告)号：US10551065B2
公开(公告)日：2020-02-04
申请号：US15165003
申请日：2016-05-26
Applicant: United Technologies Corporation
Inventor： Jonathan Jeffery Eastwood , Joey Wong , Robert M. Sonntag , Albert K. Cheung , Timothy S. Snyder
Abstract: A gas turbine engine includes a fan, a compressor section, a combustor, a fan drive gear system, and a turbine section coupled to drive the fan through the gear system. The combustor includes an annular outer shell and an annular inner shell that define an annular combustion chamber. There is a bulkhead in the annular combustion chamber, and an annular heat shield is mounted on the bulkhead. The annular heat shield includes a segment that has a forward face and an aft face, a circumferential outer side and a circumferential inner side, a central orifice between the forward face and the aft face, a lip projecting from the forward face around the central orifice, a rail projecting from the forward face, and a plurality of through-holes between the rail and the lip. The rail contacts the bulkhead to define a cavity bounded by the rail, the lip, and the bulkhead.
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公开(公告)号：US09562690B2
公开(公告)日：2017-02-07
申请号：US14456685
申请日：2014-08-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Albert K. Cheung
Abstract: An air swirler, a fuel and air admission assembly, and a staged combustor are disclosed. The staged combustor may be equipped with the fuel and air admission assemblies incorporating the air swirlers for use in gas turbine engines, such as for example gas turbine engines powering aircraft having supersonic cruise capability.
Abstract translation: 公开了一种空气旋流器，燃料和空气进入组件和分级燃烧器。 分级燃烧器可以配备有燃料和空气进入组件，其包括用于燃气涡轮发动机的空气旋流器，例如为具有超音速巡航能力的飞行器供电的燃气涡轮发动机。
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公开(公告)号：US20160273773A1
公开(公告)日：2016-09-22
申请号：US15165003
申请日：2016-05-26
Applicant: United Technologies Corporation
Inventor： Jonathan Jeffery Eastwood , Joey Wong , Robert M. Sonntag , Albert K. Cheung , Timothy S. Snyder
Abstract: A gas turbine engine includes a fan, a compressor section, a combustor, a fan drive gear system, and a turbine section coupled to drive the fan through the gear system. The combustor includes an annular outer shell and an annular inner shell that define an annular combustion chamber. There is a bulkhead in the annular combustion chamber, and an annular heat shield is mounted on the bulkhead. The annular heat shield includes a segment that has a forward face and an aft face, a circumferential outer side and a circumferential inner side, a central orifice between the forward face and the aft face, a lip projecting from the forward face around the central orifice, a rail projecting from the forward face, and a plurality of through-holes between the rail and the lip. The rail contacts the bulkhead to define a cavity bounded by the rail, the lip, and the bulkhead.
Abstract translation: 燃气涡轮发动机包括风扇，压缩机部分，燃烧器，风扇驱动齿轮系统和联接成通过齿轮系驱动风扇的涡轮部分。 燃烧器包括环形外壳和限定环形燃烧室的环形内壳。 在环形燃烧室中有一个隔壁，并在隔板上安装一个环形隔热罩。 环形隔热罩包括具有前表面和后表面，周向外侧和周向内侧的区段，前表面和后表面之间的中心孔，从中心孔周围的前表面突出的唇部 ，从前表面突出的轨道，以及轨道和唇缘之间的多个通孔。 轨道接触隔板以限定由轨道，唇缘和舱壁限定的空腔。
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公开(公告)号：US20160123596A1
公开(公告)日：2016-05-05
申请号：US14895784
申请日：2014-06-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： James B. Hoke , Randal G. McKinney , Albert K. Cheung
CPC classification number: F23R3/346 , F23R3/002 , F23R3/06 , F23R3/14 , F23R3/42 , F23R3/50 , Y02T50/675
Abstract: A combustor a gas turbine engine includes an axial fuel injection system in communication with a combustion chamber, the axial fuel injection system operable to supply between about 10%-35% of a combustion airflow. A radial fuel injection system communicates with the combustion chamber downstream of the axial fuel injection system, where the radial fuel injection system is operable to supply between about 30%-60% of the combustion airflow. A multiple of dilution holes are in communication with a combustion chamber downstream of said radial fuel injection system, where the multiple of dilution holes are operable to supply between about 5%-20% of the combustion airflow.
Abstract translation: 燃烧器是燃气涡轮发动机，其包括与燃烧室连通的轴向燃料喷射系统，所述轴向燃料喷射系统可操作以提供约10％-35％的燃烧气流。 径向燃料喷射系统与轴向燃料喷射系统下游的燃烧室连通，其中径向燃料喷射系统可操作以供应燃烧气流的约30％-60％。 多个稀释孔与所述径向燃料喷射系统下游的燃烧室连通，其中多个稀释孔可操作以供应约5％-20％的燃烧气流。
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公开(公告)号：US20210207807A1
公开(公告)日：2021-07-08
申请号：US16736340
申请日：2020-01-07
Applicant: United Technologies Corporation
Inventor： Fumitaka Ichihashi , Albert K. Cheung , Timothy S. Snyder
IPC: F23R3/00
Abstract: A combustor for a gas turbine engine includes a combustion chamber defined between an inner shell and an outer shell. The combustor further includes a bulkhead extending between the inner shell and the outer shell. The bulkhead includes a plurality of impingement cooling rings. Each impingement cooling ring of the plurality of impingement cooling rings includes a plurality of impingement cooling holes extending through the bulkhead. The combustor further includes a heat shield panel mounted to the bulkhead so as to define an impingement cooling chamber between the bulkhead and the heat shield panel. The heat shield panel further includes a radial portion between a perimeter and an opening, with respect to an opening center axis, which is free of penetrations. The plurality of impingement cooling holes of each of the plurality of impingement cooling rings are directed toward the radial portion of the heat shield panel.
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Patent Agency Ranking
公开(公告)号：US09797601B2
公开(公告)日：2017-10-24
申请号：US14601389
申请日：2015-01-21
Applicant: United Technologies Corporation
Inventor： Albert K. Cheung , James B. Hoke , Randal G. McKinney
CPC classification number: F23R3/286 , B01F3/04 , B01F15/0274 , F02C7/22 , F02M61/162 , F23D11/383 , F23R3/34
Abstract: A combustor is provided. The combustor may include an axial fuel injection system, and a radial fuel injection system aft of the axial fuel injection system. The axial fuel injection system includes a mixer having a bluff body at an exit port of the mixer, and a fuel injector disposed within the mixer. A fuel and air mixer is also provided and comprises an outer housing with an exit port and a bluff body. The bluff body extends across the exit port of the outer housing. A fuel injection system is also provided. The systems comprise a mixer having a bluff body at an exit port of the mixer and a fuel injector disposed within the mixer.
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公开(公告)号：US20170059161A1
公开(公告)日：2017-03-02
申请号：US14836117
申请日：2015-08-26
Applicant: United Technologies Corporation
Inventor： Albert K. Cheung , Christos Adamopoulos , Christopher B. Lyons
CPC classification number: F23R3/16 , F02C6/06 , F02C6/08 , F02C7/12 , F02C7/18 , F02C9/18 , F05D2220/32 , F05D2240/35 , F05D2260/20 , F23C9/08 , F23C2900/09001 , F23R3/002 , F23R3/02 , F23R3/04 , F23R3/42 , F23R3/425 , F23R3/44 , F23R3/46 , F23R3/48 , F23R3/50 , F23R3/52 , F23R3/54 , F23R3/56 , F23R3/58
Abstract: An air extraction port at a combustor of a gas turbine engine includes a port inlet at a combustor case of the combustor having an inlet area, a port outlet having a final area, and a fluid passage extending from the port inlet to the port outlet to convey an airflow, the port inlet sized and configured to extract the airflow from the combustor case at the same nominal upstream Mach number with a tolerance of +/−0.05.
Abstract translation: 燃气涡轮发动机的燃烧器处的空气抽出口包括在燃烧器壳体处的具有入口区域的端口入口，具有最终区域的端口出口和从端口入口延伸到端口出口的流体通道 传送气流，端口入口的尺寸和构造可以在相同标称上游马赫数处从燃烧器壳体提取气流，其公差为+/- 0.05。
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公开(公告)号：US20170045226A1
公开(公告)日：2017-02-16
申请号：US14826463
申请日：2015-08-14
Applicant: United Technologies Corporation
Inventor： Albert K. Cheung , Christos Adamopoulos
Abstract: A combustor liner for a gas turbine is provided. The combustor liner comprises a wall and a plurality of airflow injection holes in the wall arranged in a circumferentially-extending row, the plurality of airflow injection holes including a plurality of circular first airflow injection holes and at least one non-circular second airflow injection hole.
Abstract translation: 提供了一种用于燃气轮机的燃烧器衬套。 所述燃烧器衬套包括壁和沿所述壁布置成沿圆周方向延伸的排中的多个气流注入孔，所述多个气流注入孔包括多个圆形第一气流注入孔和至少一个非圆形第二气流注入孔 。
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公开(公告)号：US20160258627A1
公开(公告)日：2016-09-08
申请号：US14636689
申请日：2015-03-03
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Albert K. Cheung , Zhongtao Dai , James B. Hoke
Abstract: The present disclosure relates to gas turbine engines, and in particular to combustor swirlers and swirler configurations. In one embodiment, a swirler includes an inner passage for receiving a fuel injector and a plurality of outer passages concentrically arranged around the inner passage. The plurality of outer passages include an outer vane assembly including a plurality of vane elements arranged at a first angle and a first middle vane assembly include a plurality of vane elements arranged at a second angle, wherein the outer vane assembly is concentrically arranged around the first middle vane assembly, and wherein the outer vane assembly and first middle vane assembly are configured to produce a low net-swirl to control the penetration depth and improve premixing of a fuel air mixture for the fuel injector. According to another embodiment, the swirler includes a second middle vane assembly include a plurality of vane elements arranged at a third angle.
Abstract translation: 本公开涉及燃气涡轮发动机，特别涉及燃烧器旋流器和旋流器构造。 在一个实施例中，旋流器包括用于接收燃料喷射器的内部通道和围绕内部通道同心地布置的多个外部通道。 多个外部通道包括外部叶片组件，该外部叶片组件包括以第一角度布置的多个叶片元件，第一中间叶片组件包括以第二角度布置的多个叶片元件，其中外部叶片组件围绕第一角度同心地布置 中间叶片组件，并且其中外部叶片组件和第一中间叶片组件构造成产生低的网络涡流以控制穿透深度并改善用于燃料喷射器的燃料空气混合物的预混合。 根据另一个实施例，旋流器包括第二中间叶片组件，其包括以第三角度布置的多个叶片元件。
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公开(公告)号：US20160201688A1
公开(公告)日：2016-07-14
申请号：US14913922
申请日：2014-07-18
Applicant: United Technologies Corporation
Inventor： Christopher B. Lyons , Albert K. Cheung
Abstract: A diffuser for a gas turbine engine includes a diffuser housing that has a circumferential array of hollow struts that provide a cavity. The diffuser housing includes inlet and outlet apertures that are in fluid communication with the cavity. An opening on a trailing end of the struts is in fluid communication with the cavity. The diffuser housing is configured to introduce a fluid through the inlet aperture and receive a core flow through the opening. The fluid and core flow exit through the outlet aperture.
Abstract translation: 用于燃气涡轮发动机的扩散器包括具有提供空腔的中空支柱的圆周阵列的扩散器外壳。 扩散器壳体包括与空腔流体连通的入口和出口孔。 支柱尾端上的开口与空腔流体连通。 扩散器壳体构造成通过入口孔引入流体并且接收穿过开口的芯流。 流体和芯流通过出口孔流出。
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