公开(公告)号：US20120036863A1

公开(公告)日：2012-02-16

申请号：US12856107

申请日：2010-08-13

Applicant: Joseph Kirzhner ,  Predrag Popovic ,  Roy Marshall Washam

Inventor： Joseph Kirzhner ,  Predrag Popovic ,  Roy Marshall Washam

IPC: F02C7/22 ,  F02C9/00

CPC classification number: F02C7/22 ,  F02C9/34 ,  F02C9/40

Abstract: In operating a gas turbine, there can be a difference between the desired heating value of the fuel and the actual needs of the fuel for sustainable combustion during various stages of the turbine operation. In one aspect, combustible lean limit operation of the gas turbine free of lean blow out is enabled by adjusting fuel-air-ratio of the fuel and fuel-air mixture properties, based on the operation requirements of the turbine and flammability of the fuel components.

Abstract translation: 在操作燃气轮机时，在涡轮机运行的各个阶段期间燃料的期望的热值与用于可持续燃烧的燃料的实际需要之间可能存在差异。 在一个方面，通过基于涡轮机的操作要求和燃料组分的可燃性调节燃料和燃料 - 空气混合物性质的燃料空气比，能够实现无烟气的燃气轮机的可燃稀薄限制操作 。

公开(公告)号：US20120102967A1

公开(公告)日：2012-05-03

申请号：US12926121

申请日：2010-10-27

Applicant: Joseph Kirzhner ,  Predrag Popovic

Inventor： Joseph Kirzhner ,  Predrag Popovic

IPC: F02C9/00

CPC classification number: F23N5/242 ,  F23N2021/10 ,  F23N2021/12 ,  F23N2023/04 ,  F23N2023/08 ,  F23N2041/20 ,  F23R3/36 ,  F23R2900/00002 ,  Y02T50/677 ,  Y02T50/678

Abstract: A method and system for preventing or reducing the risk of combustion instabilities in a gas turbine includes utilizing a turbine controller computer processor to compare predetermined and stored stable combustion characteristics, including rate of change of the characteristics, with actual operating combustion characteristics. If the actual operating combustion characteristics are divergent from stable combustion characteristics then the controller modifies one or more gas turbine operating parameters which most rapidly stabilize the operation of the gas turbine.

Abstract translation: 用于防止或降低燃气轮机中燃烧不稳定性风险的方法和系统包括利用涡轮机控制器计算机处理器将包括特性变化率的预定和存储的稳定燃烧特性与实际操作燃烧特性进行比较。 如果实际的操作燃烧特性与稳定的燃烧特性不同，则控制器改变一个或多个最迅速地稳定燃气轮机的运行的燃气轮机操作参数。

公开(公告)号：US20120102914A1

公开(公告)日：2012-05-03

申请号：US12938415

申请日：2010-11-03

Applicant: Joseph Kirzhner ,  Matthieu Paul Frederic Vierling ,  Nicolas Pourron ,  Denis Michel Martin ,  Predrag Popovic

Inventor： Joseph Kirzhner ,  Matthieu Paul Frederic Vierling ,  Nicolas Pourron ,  Denis Michel Martin ,  Predrag Popovic

IPC: F02C9/00 ,  G01M15/14

CPC classification number: F02C9/48 ,  F01D17/08 ,  F02C9/40 ,  F05D2260/80 ,  F05D2270/0831 ,  F05D2270/309

Abstract: Certain embodiments of the invention may include systems and methods for compensating fuel composition variations in a gas turbine. According to an example embodiment of the invention, a method is provided for compensating for fuel composition variations in a turbine. The method can include: monitoring at least one fuel parameter associated with a turbine combustor; monitoring one or more combustion dynamics characteristics associated with the turbine combustor; monitoring one or more performance and emissions characteristics associated with the turbine; estimating fuel composition based at least in part on the at least one fuel parameter, the one or more combustion dynamics characteristics, and the one or more performance and emissions characteristics, and adjusting at least one fuel parameter based at least in part on the estimated fuel composition.

Abstract translation: 本发明的某些实施例可以包括用于补偿燃气轮机中的燃料组成变化的系统和方法。 根据本发明的示例性实施例，提供了一种用于补偿涡轮机中的燃料组成变化的方法。 该方法可以包括：监测与涡轮机燃烧器相关联的至少一个燃料参数; 监测与所述涡轮机燃烧器相关联的一个或多个燃烧动态特性; 监测与涡轮相关联的一个或多个性能和排放特性; 至少部分地基于所述至少一个燃料参数，所述一个或多个燃烧动态特性以及所述一个或多个性能和排放特征来估计燃料组成，并且至少部分地基于所估计的燃料来调整至少一个燃料参数 组成。

公开(公告)号：US09500369B2

公开(公告)日：2016-11-22

申请号：US13449695

申请日：2012-04-18

Applicant: Predrag Popovic ,  Gilbert Otto Kraemer ,  William Thomas Ross ,  Vladimir Belvaev

Inventor： Predrag Popovic ,  Gilbert Otto Kraemer ,  William Thomas Ross ,  Vladimir Belvaev

IPC: F23R3/14 ,  F23R3/28 ,  F02C7/264 ,  F02C7/266 ,  F23C7/00

CPC classification number: F23R3/14 ,  F02C7/264 ,  F02C7/266 ,  F23C7/004 ,  F23R3/28 ,  F23R3/286

Abstract: A fuel nozzle and a method for operating a combustor are disclosed. The method includes flowing a fuel and an oxidizer through a fuel nozzle, the fuel nozzle comprising an inner tube, an intermediate tube, and an outer tube each configured for flowing one of the fuel or the oxidizer therethrough. At least one of the inner tube, the intermediate tube, or the outer tube includes a plurality of swirler vanes. The method further includes imparting a swirl to the fuel and the oxidizer in the fuel nozzle, and exhausting the fuel and the oxidizer from the fuel nozzle into a combustion zone.

Abstract translation: 公开了燃料喷嘴和操作燃烧器的方法。 该方法包括使燃料和氧化剂流过燃料喷嘴，燃料喷嘴包括内管，中间管和外管，每个都配置成使燃料或氧化剂之一流过其中。 内管，中间管或外管中的至少一个包括多个旋流叶片。 该方法还包括向燃料喷嘴中的燃料和氧化剂施加漩涡，并将燃料和氧化剂从燃料喷嘴排出到燃烧区中。

公开(公告)号：US20150135723A1

公开(公告)日：2015-05-21

申请号：US14358134

申请日：2012-02-21

Applicant: Vladimir Vasilyevich Belyaev ,  Gilber Otto Kraemer ,  Predrag Popovic

Inventor： Vladimir Vasilyevich Belyaev ,  Gilber Otto Kraemer ,  Predrag Popovic

IPC: F02C7/22 ,  F23R3/28 ,  F02C7/04

CPC classification number: F02C7/22 ,  F02C7/04 ,  F23R3/14 ,  F23R3/28

Abstract: A combustor nozzle includes a fuel passage that extends generally axially in the nozzle and a surface that extends radially across at least a portion of the fuel passage. A projection in the surface extends generally axially down-stream from the surface, and an indention in the surface radially surrounds the projection. An oxidant supply is in fluid communication with an oxidant passage, and the oxidant passage is radially displaced from the fuel passage and terminates at an oxidant outlet. A method of supplying a fuel to a combustor includes flowing fuel through a projection in a surface, wherein the projection extends generally axially downstream from the surface, and flowing fuel through an indention in the surface, wherein the indention radially surrounds the projection. The method further includes flowing an oxidant through an oxidant outlet that circumferentially surrounds the indention in the surface.

Abstract translation: 燃烧器喷嘴包括在喷嘴中大致轴向延伸的燃料通道和径向延伸穿过燃料通道的至少一部分的表面。 表面上的突起从表面大致轴向向下延伸，并且表面中的凹陷径向包围突起。 氧化剂供应源与氧化剂通道流体连通，并且氧化剂通道从燃料通道径向移位并终止于氧化剂出口。 向燃烧器供应燃料的方法包括使燃料流过表面中的突起，其中突出部大体轴向地从表面向下延伸，并且使燃料通过表面中的压痕流动，其中凹口径向包围突起。 该方法还包括使氧化剂流过氧化剂出口，其周向地围绕表面中的凹陷。

公开(公告)号：US20130263605A1

公开(公告)日：2013-10-10

申请号：US13438851

申请日：2012-04-04

Applicant: Abinash Baruah ,  Gilbert Otto Kraemer ,  Predrag Popovic ,  Arvind Venugopal Menon

Inventor： Abinash Baruah ,  Gilbert Otto Kraemer ,  Predrag Popovic ,  Arvind Venugopal Menon

IPC: F23R3/28

CPC classification number: F23R3/12 ,  F23R3/28

Abstract: The present application thus provides a fuel nozzle for use with one or more flows of fuel and a flow of air in a combustor. The fuel nozzle may include one or more gas fuel passages for the one or more of flows of fuel, a swirler with one or more air chambers therein surrounding the gas fuel passages, and a collar with one or more curtain slots surrounding the swirler. The flow of air is divided between a swirler flow through the air chambers and a curtain flow through the curtain slots.

Abstract translation: 因此，本申请提供了一种用于一个或多个燃料流和燃烧器中的空气流的燃料喷嘴。 燃料喷嘴可以包括用于一个或多个燃料流的一个或多个气体燃料通道，其中围绕气体燃料通道的一个或多个气室的旋流器以及围绕旋流器的一个或多个窗帘槽的套环。 空气流在通过空气室的旋流器流动和通过帘槽之间的帘子流中分开。

公开(公告)号：US20130074504A1

公开(公告)日：2013-03-28

申请号：US13240165

申请日：2011-09-22

Applicant: Abinash Baruah ,  Anand Prafulchandra Desai ,  Thangaraj Dhanasekaran ,  Predrag Popovic

Inventor： Abinash Baruah ,  Anand Prafulchandra Desai ,  Thangaraj Dhanasekaran ,  Predrag Popovic

IPC: F02C9/28 ,  F23R3/28

CPC classification number: F23R3/28 ,  F23L7/00 ,  F23L2900/07002 ,  F23L2900/07003 ,  F23L2900/07009 ,  F23N5/003 ,  Y02T50/677

Abstract: A system including a controller. The controller may receive a signal indicative of an emissions level of a turbine. The controller may also generate at least one control signal. This control signal may control a split of diluent between a first and a second mixing chamber, whereby the first and the second mixing chambers are located in a fuel nozzle in the turbine.

Abstract translation: 包括控制器的系统。 控制器可以接收指示涡轮机的排放水平的信号。 控制器还可以产生至少一个控制信号。 该控制信号可以控制在第一和第二混合室之间的稀释剂的分离，由此第一和第二混合室位于涡轮机中的燃料喷嘴中。

公开(公告)号：US08365534B2

公开(公告)日：2013-02-05

申请号：US13048564

申请日：2011-03-15

Applicant: Predrag Popovic ,  Abinash Baruah ,  Gilbert Otto Kraemer ,  William Thomas Ross

Inventor： Predrag Popovic ,  Abinash Baruah ,  Gilbert Otto Kraemer ,  William Thomas Ross

IPC: F02C7/22 ,  F23R3/28 ,  F23D14/22

CPC classification number: F23R3/28 ,  F23C2900/07022 ,  F23D14/22 ,  F23L7/00 ,  F23R3/10 ,  F23R3/283 ,  F23R3/343 ,  F23R3/346 ,  F23R3/46

Abstract: A combustor includes an end cover having a nozzle. The nozzle has a front end face and a central axis. The nozzle includes a plurality of fuel passages and a plurality of oxidizer passages. The fuel passages are configured for fuel exiting the fuel passage. The fuel passages are positioned to direct fuel in a first direction, where the first direction is angled inwardly towards the center axis. The oxidizer passages are configured for having oxidizer exit the oxidizer passages. The oxidizer passages are positioned to direct oxidizer in a second direction, where the second direction is angled outwardly away from the center axis. The plurality of fuel passages and the plurality of oxidizer passages are positioned in relation to one another such that fuel is in a cross-flow arrangement with oxidizer to create a burning zone in the combustor.

Abstract translation: 燃烧器包括具有喷嘴的端盖。 喷嘴具有前端面和中心轴线。 喷嘴包括多个燃料通道和多个氧化剂通道。 燃料通道构造成用于离开燃料通道的燃料。 燃料通道被定位成在第一方向上引导燃料，其中第一方向向内朝向中心轴线倾斜。 氧化剂通道构造成使氧化剂离开氧化剂通道。 氧化剂通道定位成在第二方向上引导氧化剂，其中第二方向与中心轴向外成一定角度。 多个燃料通道和多个氧化剂通道相对于彼此定位，使得燃料与氧化剂成交叉流动布置以在燃烧器中产生燃烧区域。

公开(公告)号：US08522554B2

公开(公告)日：2013-09-03

申请号：US12652244

申请日：2010-01-05

Applicant: John Intile ,  Predrag Popovic ,  Lucas John Stoia

Inventor： John Intile ,  Predrag Popovic ,  Lucas John Stoia

IPC: F02C1/00 ,  F02G3/00

CPC classification number: F23R3/283 ,  F23D2209/30 ,  F23D2214/00

Abstract: A secondary fuel nozzle for a turbine includes a passive purge air passageway which provides purge air to the secondary nozzle at all times that the nozzle is in operation. The passive purge air passageway draws in air from a location adjacent an upstream end of the nozzle. Because of a pressure differential between air located at the downstream end of the nozzle and air located at the upstream end of the nozzle, purge air will run through the passive purge air passageway at all times the nozzle is in operation. There is no need for a supply of compressed purge air.

Abstract translation: 用于涡轮机的次级燃料喷嘴包括被动吹扫空气通道，其在喷嘴正在运行的任何时候向次喷嘴提供吹扫空气。 被动吹扫空气通道从与喷嘴上游端相邻的位置吸入空气。 由于位于喷嘴下游端的空气和位于喷嘴上游端的空气之间的压差，净化空气将始终贯穿被动吹扫空气通道，喷头始终处于运行状态。 不需要供应压缩的吹扫空气。

公开(公告)号：US20120266604A1

公开(公告)日：2012-10-25

申请号：US13449695

申请日：2012-04-18

Applicant: Predrag Popovic ,  Gilbert Otto Kraemer ,  William Thomas Ross ,  Vladimir Belvaev

Inventor： Predrag Popovic ,  Gilbert Otto Kraemer ,  William Thomas Ross ,  Vladimir Belvaev

IPC: F02C7/22 ,  F23D14/48 ,  F02C7/264

CPC classification number: F23R3/14 ,  F02C7/264 ,  F02C7/266 ,  F23C7/004 ,  F23R3/28 ,  F23R3/286

Abstract: A fuel nozzle and a method for operating a combustor are disclosed. The method includes flowing a fuel and an oxidizer through a fuel nozzle, the fuel nozzle comprising an inner tube, an intermediate tube, and an outer tube each configured for flowing one of the fuel or the oxidizer therethrough. At least one of the inner tube, the intermediate tube, or the outer tube includes a plurality of swirler vanes. The method further includes imparting a swirl to the fuel and the oxidizer in the fuel nozzle, and exhausting the fuel and the oxidizer from the fuel nozzle into a combustion zone.

Abstract translation: 公开了燃料喷嘴和操作燃烧器的方法。 该方法包括使燃料和氧化剂流过燃料喷嘴，燃料喷嘴包括内管，中间管和外管，每个都配置成使燃料或氧化剂之一流过其中。 内管，中间管或外管中的至少一个包括多个旋流叶片。 该方法还包括向燃料喷嘴中的燃料和氧化剂施加漩涡，并将燃料和氧化剂从燃料喷嘴排出到燃烧区中。