公开(公告)号：US20110252805A1

公开(公告)日：2011-10-20

申请号：US12762842

申请日：2010-04-19

Applicant: Jonathan Dwight BERRY ,  Kara Johnston EDWARDS ,  Heath Michael OSTEBEE

Inventor： Jonathan Dwight BERRY ,  Kara Johnston EDWARDS ,  Heath Michael OSTEBEE

IPC: F02C7/18

CPC classification number: F23R3/002 ,  F23R3/04

Abstract: A combustor assembly for a turbine includes a combustor and a combustor liner; a first flow sleeve surrounding the combustor liner forming a first substantially axially-extending flow annulus radially therebetween. The first flow sleeve has a first plurality of apertures formed about a circumference thereof for directing compressor discharge air as cooling air radially into said first flow annulus. A transition piece is connected to the combustor liner, the transition piece adapted to carry hot combustion gases to the turbine, and a second flow sleeve surrounds the transition piece forming a second substantially axially-extending flow annulus radially therebetween. The second flow sleeve has a second plurality of apertures for directing compressor discharge air as cooling air radially into the second flow annulus, the first substantially axially-extending flow annulus connecting with the second substantially axially-extending flow annulus. A resilient annular seal structure is disposed radially between an aft end portion of the combustor liner and a forward end portion of said transition piece, the resilient annular seal structure configured to form a first annular cavity radially between the forward end portion of the transition piece and the aft end portion of said combustor liner. At least one transfer tube radially extends from the second flow sleeve through the second flow annulus to the transition piece, and is arranged to supply compressor discharge cooling air radially from an area outside the first and second substantially axially extending flow annuli directly to the resilient annular seal structure and to the aft end of the combustor liner.

Abstract translation: 用于涡轮机的燃烧器组件包括燃烧器和燃烧器衬套; 围绕所述燃烧器衬套的第一流动套筒在其间径向形成第一基本上轴向延伸的流动环形空间。 第一流动套筒具有围绕其圆周形成的第一多个孔，用于将压缩机排放空气作为冷却空气径向地引导到所述第一流动环空中。 过渡件连接到燃烧器衬套，过渡件适于将热的燃烧气体运送到涡轮机，并且第二流动套管围绕过渡件，在其之间径向形成第二基本轴向延伸的流动环形空间。 第二流动套管具有第二多个孔，用于将冷却空气径向地引导到第二流动环空中的压缩机排放空气，第一大致轴向延伸的流动环与第二大致轴向延伸的流动环形空间连接。 弹性环形密封结构径向设置在燃烧器衬套的后端部和所述过渡件的前端部分之间，该弹性环形密封结构构造成在过渡件的前端部分和 所述燃烧器衬套的后端部分。 至少一个传送管从第二流动套管径向延伸穿过第二流动环到过渡件，并且被布置成将压缩机排出冷却空气从第一和第二大致轴向延伸的流动环的外部的区域径向地直接供应到弹性环 密封结构和燃烧器衬套的后端。

公开(公告)号：US20130032643A1

公开(公告)日：2013-02-07

申请号：US13195394

申请日：2011-08-01

Applicant: Jonathan Dwight BERRY ,  Heath Michael OSTEBEE

Inventor： Jonathan Dwight BERRY ,  Heath Michael OSTEBEE

IPC: F23R3/42 ,  F02C7/28

CPC classification number: F23R3/283 ,  F23R3/286 ,  F23R2900/00012

Abstract: A substantially wedge-shaped sector nozzle includes a nozzle body having inner and outer arcuate segments connected by diverging radial side plates and a nozzle plate at an aft end of the nozzle body formed with an array of fuel orifices. One of the diverging radial side plates supports a radially-oriented leaf seal assembly adapted to seal against a flat plate of an adjacent similarly-shaped sector nozzle.

Abstract translation: 基本上楔形的扇形喷嘴包括喷嘴体，其具有通过发散的径向侧板连接的内部和外部弓形段，以及在形成有燃料孔阵列的喷嘴体的后端处的喷嘴板。 发散的径向侧板中的一个支撑径向取向的叶片密封组件，其适于密封邻近的类似形状的扇形喷嘴的平板。

公开(公告)号：US20120167578A1

公开(公告)日：2012-07-05

申请号：US12984274

申请日：2011-01-04

Applicant: Jonathan Dwight BERRY ,  Michael HUGHES ,  Chunyang WU

Inventor： Jonathan Dwight BERRY ,  Michael HUGHES ,  Chunyang WU

IPC: F02C7/22 ,  F23R3/28 ,  F23R3/42

CPC classification number: F23R3/16 ,  F23D14/82 ,  F23R3/286 ,  F23R2900/03043

Abstract: A flame holding inhibitor includes a base portion and an upstanding support extending away from the base portion; at least one delta-wing-shaped flap on the upstanding support, each having a relatively pointed end and a relatively broad end.

Abstract translation: 火焰保持抑制剂包括基部和从基部延伸的直立支撑; 在直立支撑上的至少一个三角翼形翼片，每个具有相对尖的端部和相对宽的端部。

公开(公告)号：US20140053571A1

公开(公告)日：2014-02-27

申请号：US13593123

申请日：2012-08-23

Applicant: Christopher Paul KEENER ,  Jason Thurman STEWART ,  Thomas Edward JOHNSON ,  Jonathan Dwight BERRY

Inventor： Christopher Paul KEENER ,  Jason Thurman STEWART ,  Thomas Edward JOHNSON ,  Jonathan Dwight BERRY

IPC: F02C7/18

CPC classification number: F23R3/10 ,  F23R3/283 ,  F23R3/286 ,  F23R2900/00012 ,  F23R2900/03044

Abstract: A cooling circuit of a gas turbine passes an airflow through a combustor section that includes a plurality of mixing tubes for transporting a fuel/air mixture and a perforated plate including a plurality of impingement holes and a plurality of tube holes for accommodating the mixing tubes. The tube holes and the mixing tubes form a plurality of annulus areas between the perforated plate and the mixing tubes. The impingement holes and the annulus areas are configured to pass the airflow through the perforated plate. A flow management device modifies an effective size of the annulus areas to control a distribution of the airflow through the impingement holes and the annulus areas of the perforated plate to enhance cooling efficiency.

Abstract translation: 燃气轮机的冷却回路通过燃烧器部分，该燃烧器部分包括用于输送燃料/空气混合物的多个混合管和包括多个冲击孔的多孔板和用于容纳混合管的多个管孔。 管孔和混合管在多孔板和混合管之间形成多个环形区域。 冲击孔和环形区域被配置成使气流穿过多孔板。 流量管理装置修改环形区域的有效尺寸以控制通过穿孔板的冲击孔和环空区域的气流的分布，以提高冷却效率。

公开(公告)号：US20130025284A1

公开(公告)日：2013-01-31

申请号：US13194385

申请日：2011-07-29

Applicant: Chunyang WU ,  Derrick Walter SIMONS ,  Jonathan Dwight BERRY ,  Michael John HUGHES

Inventor： Chunyang WU ,  Derrick Walter SIMONS ,  Jonathan Dwight BERRY ,  Michael John HUGHES

IPC: F23R3/58

CPC classification number: F23R3/14 ,  F05B2260/96 ,  F23R3/286 ,  F23R3/34 ,  F23R2900/00014

Abstract: A premixing apparatus for a gas turbine system includes non-swirl elements around a periphery of a face of a premixing apparatus and a swirl assembly located substantially at a center of the face. The non-swirl elements premix a premixture prior to the premixture being delivered to a combustor of the gas turbine system. The swirl assembly disturbs a flow of fluid prior to the fluid being delivered to the combustor. The premixture includes fuel and oxidant, and the fluid disturbed by the swirl assembly includes the oxidant or the premixture.

Abstract translation: 用于燃气涡轮机系统的预混合装置包括围绕预混合装置的表面的周边的非旋转元件和基本上位于该表面中心的旋转组件。 非旋流元件在将预混合物输送到燃气轮机系统的燃烧器之前将混合物预混合。 涡流组件在流体被输送到燃烧器之前会扰乱流体流动。 预混合物包括燃料和氧化剂，并且由涡旋组件扰动的流体包括氧化剂或预混合物。