公开(公告)号：US20050268615A1

公开(公告)日：2005-12-08

申请号：US10907866

申请日：2005-04-19

Applicant: Ronald Bunker ,  Jeremy Bailey ,  Stanley Widener ,  Thomas Johnson ,  John Intile

Inventor： Ronald Bunker ,  Jeremy Bailey ,  Stanley Widener ,  Thomas Johnson ,  John Intile

IPC: F23R3/06 ,  F02C7/12 ,  F02C7/18 ,  F23R3/00 ,  F23R3/30 ,  F23R3/42

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 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, 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: 一种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湍流器的燃烧器衬套，该多个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; 围绕所述燃烧器衬套的第一流动套筒，其间具有第一流动环空，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，用于将冷却空气从所述压缩机排出口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：US20050268613A1

公开(公告)日：2005-12-08

申请号：US10709886

申请日：2004-06-03

Applicant: John Intile ,  James West ,  William Byrne

Inventor： John Intile ,  James West ,  William Byrne

IPC: F23R3/06 ,  F02C7/12 ,  F02C7/18 ,  F23R3/00 ,  F23R3/30 ,  F23R3/42

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：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：US20110162373A1

公开(公告)日：2011-07-07

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: F02C7/22

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：US20060010874A1

公开(公告)日：2006-01-19

申请号：US10891966

申请日：2004-07-15

Applicant: John Intile ,  Thomas Farrell

Inventor： John Intile ,  Thomas Farrell

IPC: F02C7/12

CPC classification number: F23R3/002 ,  F23R3/04 ,  F23R2900/03042 ,  F23R2900/03043

Abstract: A liner (18) installed in a transition region (16) between a combustion section (12) of a gas turbine engine (10) and an air discharge section (14) of the turbine. The liner has an air inlet (26) for admitting air into the liner, and an air outlet (28) by which air is discharged from the liner. Flow of air through the liner acts to cool air flowing through the transition region of the turbine between the combustion and air discharge sections thereof, so to lower the temperature from between 2800-3000° F. to around 1400-1550° F. The liner has at least one channel (C1, C2) formed in it for flow of air through the liner. The height of this channel uniformly decreases along the length of the channel from the liner's air inlet to its air outlet. This liner construction reduces the thermal strain occurring at the aft end of the liner, prolonging the useful life of the liner, while reducing the amount of air needed to flow through the liner to affect a desired level of cooling in the transition region.

Abstract translation: 安装在燃气涡轮发动机（10）的燃烧部（12）与涡轮机的排气部（14）之间的过渡区域（16）中的衬套（18）。 衬里具有用于将空气引入衬套的空气入口（26）和用于从衬套排出空气的空气出口（28）。 通过衬套的空气流动用于冷却流过涡轮机的过渡区域的空气在其燃烧和空气排放部分之间流动，从而将温度从2800-3000°F降低到约1400-1550°F。衬垫 在其中形成有至少一个通道（C 1，C 2），用于使空气流过衬套。 该通道的高度沿着通道从衬套的空气入口到其出风口的长度均匀地减小。 该衬套结构减少了在衬套的后端发生的热应变，延长了衬套的使用寿命，同时减少了流过衬套所需的空气量以影响过渡区域中所需的冷却水平。