公开(公告)号：US20130298560A1

公开(公告)日：2013-11-14

申请号：US13466184

申请日：2012-05-08

Applicant: Patrick Benedict Melton ,  John Charles Intile ,  Lucas John Stoia

Inventor： Patrick Benedict Melton ,  John Charles Intile ,  Lucas John Stoia

IPC: F23R3/34 ,  F23R3/42 ,  F23R3/54 ,  F02C7/18

CPC classification number: F23R3/346 ,  F23R2900/03341

Abstract: A system for supplying a working fluid to a combustor includes a fuel nozzle, a combustion chamber downstream from the fuel nozzle, and a flow sleeve that circumferentially surrounds the combustion chamber. A plurality of fuel injectors are circumferentially arranged around the flow sleeve to provide fluid communication through the flow sleeve to the combustion chamber. A distribution manifold circumferentially surrounds the plurality of fuel injectors, and a fluid passage through the flow sleeve and into the distribution manifold provides fluid communication through the flow sleeve to the plurality of fuel injectors.

Abstract translation: 用于向燃烧器供应工作流体的系统包括燃料喷嘴，燃料喷嘴下游的燃烧室和周向围绕燃烧室的流动套筒。 多个燃料喷射器周向地布置在流动套筒周围，以提供通过流动套筒到燃烧室的流体连通。 分配歧管周向地围绕多个燃料喷射器，并且通过流动套管并进入分配歧管的流体通道提供通过流动套筒到多个燃料喷射器的流体连通。

公开(公告)号：US08402763B2

公开(公告)日：2013-03-26

申请号：US12605591

申请日：2009-10-26

Applicant: Jason Mulherin ,  John Charles Intile

Inventor： Jason Mulherin ,  John Charles Intile

IPC: F02C1/00 ,  F02G3/00 ,  F23R3/26

CPC classification number: F23R3/28 ,  F23R3/04

Abstract: A combustor for a gas turbine includes a plurality of nozzles provided in an array; a baffle plate configured to provide a desired air flow distribution to the array of nozzles; and a casing comprising a plurality of holes in an outer surface. The casing extends from a headend of the combustor to the baffle plate. A method of distributing an air flow in a combustor of a gas turbine includes providing an air flow to the outer surface of the casing; directing the air flow around the baffle plate; and distributing the air flow through the baffle plate to the array of nozzles.

Abstract translation: 燃气轮机的燃烧器包括设置成阵列的多个喷嘴; 挡板，被配置为向所述喷嘴阵列提供期望的气流分布; 以及在外表面中包括多个孔的壳体。 壳体从燃烧室的前端延伸到挡板。 在燃气轮机的燃烧器中分配空气流的方法包括向壳体的外表面提供空气流; 将气流引导到挡板周围; 并将空气流通过挡板分配到喷嘴阵列。

公开(公告)号：US08365532B2

公开(公告)日：2013-02-05

申请号：US12570678

申请日：2009-09-30

Applicant: Baifang Zuo ,  Willy Steve Ziminsky ,  Thomas Edward Johnson ,  John Charles Intile ,  Benjamin Paul Lacy

Inventor： Baifang Zuo ,  Willy Steve Ziminsky ,  Thomas Edward Johnson ,  John Charles Intile ,  Benjamin Paul Lacy

IPC: F02C1/00

CPC classification number: F23D14/62 ,  F23C2900/07001 ,  F23D2900/14004 ,  F23D2900/14701 ,  F23R3/14 ,  F23R3/286

Abstract: A nozzle includes an inlet, an outlet, and an axial centerline. A shroud surrounding the axial centerline extends from the inlet to the outlet and defines a circumference. The circumference proximate the inlet is greater than the circumference at a first point downstream of the inlet, and the circumference at the first point downstream of the inlet is less than the circumference at a second point downstream of the first point. A method for supplying a fuel through a nozzle directs a first airflow along a first path and a second airflow along a second path separate from the first path. The method further includes injecting the fuel into at least one of the first path or the second path and accelerating at least one of the first airflow or the second airflow.

Abstract translation: 喷嘴包括入口，出口和轴向中心线。 围绕轴向中心线的护罩从入口延伸到出口并限定圆周。 入口周围的圆周大于入口下游第一点处的圆周，入口下游第一点处的圆周小于第一点下游第二点处的圆周。 用于通过喷嘴供应燃料的方法沿着第一路径引导第一气流和沿着与第一路径分离的第二路径的第二气流。 该方法还包括将燃料喷射到第一路径或第二路径中的至少一个中并且加速第一气流或第二气流中的至少一个。

公开(公告)号：US08818684B2

公开(公告)日：2014-08-26

申请号：US12761029

申请日：2010-04-15

Applicant: Justin V. John ,  Nirm Velumylum Nirmalan ,  John Charles Intile ,  Scott William Szepek ,  Daniel Joseph Peczka ,  Bradley Steven Carey

Inventor： Justin V. John ,  Nirm Velumylum Nirmalan ,  John Charles Intile ,  Scott William Szepek ,  Daniel Joseph Peczka ,  Bradley Steven Carey

IPC: G06F19/00

CPC classification number: F01D21/00 ,  F02C9/00 ,  F05D2260/80

Abstract: Certain embodiments of the invention may include systems, methods, and apparatus for detecting failure in gas turbine hardware. According to an example embodiment of the invention, a method for detecting a failure in a gas turbine is provided. The method can include monitoring a parameter associated with the turbine, wherein the monitored parameter comprises at least one turbine bucket temperature, detecting an event associated with operation of the turbine, wherein the event is based at least in part on the monitored parameter, and initiating shutdown of the turbine upon detection of the event wherein the monitored parameter is above a predetermined value for at least a predetermined time duration.

Abstract translation: 本发明的某些实施例可以包括用于检测燃气轮机硬件故障的系统，方法和装置。 根据本发明的示例性实施例，提供了一种用于检测燃气轮机故障的方法。 该方法可以包括监测与涡轮相关联的参数，其中所监测的参数包括至少一个涡轮机桶温度，检测与涡轮机的运行相关联的事件，其中该事件至少部分地基于所监测的参数，并且启动 在检测到所监视的参数高于预定值至少预定持续时间的事件的情况下关闭涡轮机。

公开(公告)号：US20110257864A1

公开(公告)日：2011-10-20

申请号：US12761029

申请日：2010-04-15

Applicant: Justin V. John ,  Nirm Velumylum Nirmalan ,  John Charles Intile ,  Scott William Szepek ,  Daniel Joseph Peczka ,  Bradley Steven Carey

Inventor： Justin V. John ,  Nirm Velumylum Nirmalan ,  John Charles Intile ,  Scott William Szepek ,  Daniel Joseph Peczka ,  Bradley Steven Carey

IPC: F02C9/00

CPC classification number: F01D21/00 ,  F02C9/00 ,  F05D2260/80

Abstract: Certain embodiments of the invention may include systems, methods, and apparatus for detecting failure in gas turbine hardware. According to an example embodiment of the invention, a method for detecting a failure in a gas turbine is provided. The method can include monitoring a parameter associated with the turbine, wherein the monitored parameter comprises at least one turbine bucket temperature, detecting an event associated with operation of the turbine, wherein the event is based at least in part on the monitored parameter, and initiating shutdown of the turbine upon detection of the event wherein the monitored parameter is above a predetermined value for at least a predetermined time duration.

Abstract translation: 本发明的某些实施例可以包括用于检测燃气轮机硬件故障的系统，方法和装置。 根据本发明的示例性实施例，提供了一种用于检测燃气轮机故障的方法。 该方法可以包括监测与涡轮相关联的参数，其中所监测的参数包括至少一个涡轮机桶温度，检测与涡轮机的运行相关联的事件，其中该事件至少部分地基于所监测的参数，并且启动 在检测到所监视的参数高于预定值至少预定持续时间的事件的情况下关闭涡轮机。

公开(公告)号：US20110072824A1

公开(公告)日：2011-03-31

申请号：US12570678

申请日：2009-09-30

Applicant: BAIFANG ZUO ,  WILLY STEVE ZIMINSKY ,  THOMAS EDWARD JOHNSON ,  JOHN CHARLES INTILE ,  BENJAMIN PAUL LACY

Inventor： BAIFANG ZUO ,  WILLY STEVE ZIMINSKY ,  THOMAS EDWARD JOHNSON ,  JOHN CHARLES INTILE ,  BENJAMIN PAUL LACY

IPC: F02C7/22

CPC classification number: F23D14/62 ,  F23C2900/07001 ,  F23D2900/14004 ,  F23D2900/14701 ,  F23R3/14 ,  F23R3/286

Abstract: A nozzle includes an inlet, an outlet, and an axial centerline. A shroud surrounding the axial centerline extends from the inlet to the outlet and defines a circumference. The circumference proximate the inlet is greater than the circumference at a first point downstream of the inlet, and the circumference at the first point downstream of the inlet is less than the circumference at a second point downstream of the first point. A method for supplying a fuel through a nozzle directs a first airflow along a first path and a second airflow along a second path separate from the first path. The method further includes injecting the fuel into at least one of the first path or the second path and accelerating at least one of the first airflow or the second airflow.

Abstract translation: 喷嘴包括入口，出口和轴向中心线。 围绕轴向中心线的护罩从入口延伸到出口并限定圆周。 入口周围的圆周大于入口下游第一点处的圆周，入口下游第一点处的圆周小于第一点下游第二点处的圆周。 用于通过喷嘴供应燃料的方法沿着第一路径引导第一气流和沿着与第一路径分离的第二路径的第二气流。 该方法还包括将燃料喷射到第一路径或第二路径中的至少一个中并且加速第一气流或第二气流中的至少一个。

公开(公告)号：US07010921B2

公开(公告)日：2006-03-14

申请号：US10709886

申请日：2004-06-01

Applicant: John Charles Intile ,  James A. West ,  William Byrne

Inventor： John Charles Intile ,  James A. West ,  William Byrne

IPC: F02C1/00 ,  F02G3/00

CPC classification number: F23R3/002 ,  F23R3/06 ,  F23R2900/03042 ,  F23R2900/03044

Abstract: A method and apparatus for cooling a combustor liner and transitions piece of a gas turbine include a combustor liner with a plurality of circular ring turbulators arranged in an array axially along a length defining a length of the combustor liner and located on an outer surface thereof; a first flow sleeve surrounding the combustor liner with a first flow annulus therebetween including a plurality of axial channels (C) extending over a portion of an aft end portion of the liner parallel to each other, the cross-sectional area of each channel either constant or varying along the length of the channel, the first flow sleeve having a plurality of rows of cooling holes formed about a circumference of the first flow sleeve for directing cooling air from the compressor discharge into the first flow annulus; a transition piece connected to the combustor liner and adapted to carry hot combustion gases to a stage of the turbine; a second flow sleeve surrounding the transition piece a second plurality of rows of cooling apertures for directing cooling air into a second flow annulus between the second flow sleeve and the transition piece; wherein the first plurality of cooling holes and second plurality of cooling apertures are each configured with an effective area to distribute less than 50% of compressor discharge air to the first flow sleeve and mix with cooling air from the second flow annulus.

Abstract translation: 用于冷却燃烧器衬套和燃气轮机的过渡件的方法和设备包括具有多个圆环形湍流器的燃烧器衬套，所述多个环形湍流器沿着限定燃烧器衬套的长度并位于其外表面上的长度轴向排列; 环绕燃烧器衬套的第一流动套筒包括在衬套的后端部分的一部分上彼此平行延伸的多个轴向通道（C），每个通道的横截面面积是恒定的 或沿着所述通道的长度变化，所述第一流动套筒具有围绕所述第一流动套筒的圆周形成的多排冷却孔，用于将来自所述压缩机排出口的冷却空气引导到所述第一流动环空中; 连接到所述燃烧器衬套并适于将热燃烧气体运送到所述涡轮机的级的过渡件; 围绕所述过渡件的第二流动套筒，用于将冷却空气引导到所述第二流动套筒和所述过渡件之间的第二流动环空中的第二多排冷却孔; 其中所述第一多个冷却孔和第二多个冷却孔分别配置有有效区域以将小于50％的压缩机排出空气分配到所述第一流动套筒并与来自所述第二流动环的冷却空气混合。

公开(公告)号：US08677753B2

公开(公告)日：2014-03-25

申请号：US13466184

申请日：2012-05-08

Applicant: Patrick Benedict Melton ,  John Charles Intile ,  Lucas John Stoia

Inventor： Patrick Benedict Melton ,  John Charles Intile ,  Lucas John Stoia

IPC: F02C1/00

CPC classification number: F23R3/346 ,  F23R2900/03341

Abstract: A system for supplying a working fluid to a combustor includes a fuel nozzle, a combustion chamber downstream from the fuel nozzle, and a flow sleeve that circumferentially surrounds the combustion chamber. A plurality of fuel injectors are circumferentially arranged around the flow sleeve to provide fluid communication through the flow sleeve to the combustion chamber. A distribution manifold circumferentially surrounds the plurality of fuel injectors, and a fluid passage through the flow sleeve and into the distribution manifold provides fluid communication through the flow sleeve to the plurality of fuel injectors.

Abstract translation: 用于向燃烧器供应工作流体的系统包括燃料喷嘴，燃料喷嘴下游的燃烧室和周向围绕燃烧室的流动套筒。 多个燃料喷射器周向地布置在流动套筒周围，以提供通过流动套筒到燃烧室的流体连通。 分配歧管周向地围绕多个燃料喷射器，并且通过流动套管并进入分配歧管的流体通道提供通过流动套筒到多个燃料喷射器的流体连通。

公开(公告)号：US20130160456A1

公开(公告)日：2013-06-27

申请号：US13334879

申请日：2011-12-22

Applicant: Daniel David Snook ,  John Charles Intile

Inventor： Daniel David Snook ,  John Charles Intile

IPC: F02C7/00

CPC classification number: F02C1/06 ,  F02C3/34 ,  Y02E20/16

Abstract: A system for controlling oxygen emissions from a gas turbine includes a combustor, a plenum downstream from the combustor, and a turbine downstream from the plenum that produces an exhaust. A compressor downstream from the turbine receives the exhaust and produces a compressed exhaust. A compressed exhaust plenum downstream from the compressor provides fluid communication to the combustor and the plenum. A method for controlling oxygen emissions from a gas turbine includes flowing an exhaust from a turbine and increasing the pressure of the exhaust to produce a compressed exhaust. The method further includes flowing a first portion of the compressed exhaust to an inlet of a combustor and flowing a second portion of the compressed exhaust to a plenum between the turbine and the combustor.

Abstract translation: 用于控制来自燃气涡轮机的氧气排放的系统包括燃烧器，来自燃烧器下游的增压室以及产生排气的气室下游的涡轮机。 涡轮机下游的压缩机接收排气并产生压缩排气。 压缩机下游的压缩排气室提供与燃烧器和增压室的流体连通。 用于控制来自燃气轮机的氧气排放的方法包括使来自涡轮机的排气流动并且增加排气的压力以产生压缩排气。 该方法还包括将压缩排气的第一部分流动到燃烧器的入口并将压缩排气的第二部分流动到涡轮和燃烧器之间的集气室。

公开(公告)号：US08024964B2

公开(公告)日：2011-09-27

申请号：US12569507

申请日：2009-09-29

Applicant: Timothy Andrew Healy ,  John Charles Intile ,  Joseph Vincent Citeno ,  Garth Curtis Frederick

Inventor： Timothy Andrew Healy ,  John Charles Intile ,  Joseph Vincent Citeno ,  Garth Curtis Frederick

IPC: G01M15/14

CPC classification number: F02C9/40 ,  F02C7/22 ,  F05D2270/303 ,  F05D2270/708 ,  F23N5/003 ,  F23N5/022 ,  F23N2021/10 ,  F23N2041/20 ,  G01N33/225

Abstract: Disclosed is a method and system for determining composition of a fuel entering a combustor. The method includes determining a temperature of the fuel entering the combustor, calculating a first estimated total fuel flow utilizing fuel properties and fuel nozzle effective area (Ae), and calculating a second estimated total fuel flow utilizing an aero-thermal cycle model analysis. The first estimated total fuel flow is compared to the second estimated total fuel flow and a lower heating value of the fuel is determined from a difference between the first estimated total fuel flow and the second estimated total fuel flow. A method and system for controlling a gas turbine includes calculating effects of the fuel composition on performance of the gas turbine and comparing one or more performance parameters to one or more parameter limits. One or more machine controls of the gas turbine are changed based on the results of the comparison.

Abstract translation: 公开了一种用于确定进入燃烧器的燃料的组成的方法和系统。 该方法包括确定进入燃烧器的燃料的温度，利用燃料特性和燃料喷嘴有效面积（Ae）计算第一估计的总燃料流量，以及利用航空 - 热循环模型分析计算第二估计的总燃料流量。 将第一估计总燃料流量与第二估计总燃料流量进行比较，并且根据第一估计总燃料流量与第二估计总燃料流量之间的差确定燃料的较低热值。 用于控制燃气轮机的方法和系统包括计算燃料组成对燃气轮机性能的影响，并将一个或多个性能参数与一个或多个参数限制进行比较。 基于比较的结果，改变燃气轮机的一个或多个机器控制。