公开(公告)号：EP2075507A3

公开(公告)日：2017-05-03

申请号：EP08165970.8

申请日：2008-10-07

Applicant: General Electric Company

Inventor： Lohmueller, Steven Joseph

IPC: F23R3/04 ,  F23R3/28 ,  F23R3/26

CPC classification number: F23R3/04 ,  F23R3/26 ,  F23R3/283 ,  Y02T50/675

Abstract: A combustor (37) for a gas turbine engine (21) is provided. The combustor includes a housing (33) at least in part defining an internal combustion chamber (47) of the combustor, a combustor component held in communication with the combustion chamber, and a ferrule (37) generally coupled to the housing and being moveable relative thereto between a first position and a second position, the ferrule having a primary opening (51) through which the combustor component extends for support of the combustor component by the ferrule such that the combustor component is moveable conjointly with the ferrule relative to the housing, the ferrule further having a plurality of purge gas openings (55,57,59) formed therein separate from and in transversely spaced relationship with the primary opening to allow purge gas to flow through the ferrule into the combustion chamber, the purge gas openings being located in the ferrule such that in the first position of the ferrule the purge gas openings comprise at least one blocked purge gas opening that is blocked against the flow of purge gas therethrough into the combustion chamber and at least one unblocked purge gas opening through which purge gas is permitted to flow into the combustion chamber, and in the second position of the ferrule at least one of the blocked purge gas openings of the first ferrule position is unblocked to permit the flow of purge gas therethrough into the combustion chamber.

Abstract translation: 一种用于燃气涡轮发动机（21）的燃烧器（37）被提供。 该燃烧器包括在燃烧器中，在与燃烧室连通保持的燃烧器部件的内部燃烧室（47）的部分限定至少一个壳体（33），和一个套箍（37）基因的反弹联接到所述壳体和能够移动的相对 到其上的第一位置和第二位置之间，具有由所述套圈的主开口（51），通过该支持燃烧器组件的燃烧器组件延伸检查套圈做的燃烧器部件是共同地与相对于所述壳体的套圈可移动的， 套圈进一步具有形成在其中从和与主开口横向间隔关系分开以允许吹扫气体通过所述套圈流入燃烧室吹扫气体开口的多个（55,57,59），所述吹扫气体开口位于 在套圈搜索在所述套圈的所述第一位置没有吹扫气体开口包括至少一种封端的净化气体开口没有被阻挡agai NST吹扫气体的流动有通过进入燃烧室和至少一个未封闭的吹扫气体开口，通过该吹扫气体被允许流入燃烧室，和在套圈的第二位置的封端吹扫气体开口中的至少一个 第一套管位置是畅通通过那里，以允许净化气体流入燃烧室。

公开(公告)号：EP1793097B1

公开(公告)日：2009-04-22

申请号：EP06255019.9

申请日：2006-09-28

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Lohmueller, Steven Joseph ,  Czachor, Robert Paul

IPC: F01D25/28 ,  F02C3/14 ,  F23R3/60

CPC classification number: F01D25/28 ,  F05D2230/642 ,  F05D2240/35 ,  F23R3/60

公开(公告)号：EP1186832A2

公开(公告)日：2002-03-13

申请号：EP01307493.5

申请日：2001-09-04

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Hura, Harjit Singh ,  Cooper, James Neil ,  Mongia, Hukam Chand ,  Sabla, Paul Edward ,  Duncan, Beverly Stephenson ,  Lohmueller, Steven Joseph

IPC: F23R3/34

CPC classification number: F23R3/346 ,  F23C2201/20 ,  F23C2201/401

Abstract: A two-stage fuel nozzle assembly (56) for a gas turbine engine. The primary combustion region (120) is centrally positioned and includes a fuel injector (122) that is surrounded by one or more swirl chambers (132, 160) to provide a fuel air mixture that is ignited to define a first stage combustion zone. A secondary combustion region is provided by an annular housing (168) that surrounds the primary combustion region (120) and it includes a secondary fuel injector (126) having a radially-outwardly-directed opening (172) and surrounded by an annular ring (128) that includes openings (194) for providing a swirl chamber for the secondary combustion region (124). Cooling air is directed angularly between the primary and secondary combustion zones to delay intermixing and thereby allow more complete combustion of the respective zones prior to their coalescing further downstream. The primary combustion region (120) is activated during idle and low engine power conditions, and both the primary (120) and secondary (124) combustion regions are activated during high engine power conditions.

公开(公告)号：EP1186832B1

公开(公告)日：2008-09-17

申请号：EP01307493.5

申请日：2001-09-04

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Hura, Harjit Singh ,  Cooper, James Neil ,  Mongia, Hukam Chand ,  Sabla, Paul Edward ,  Duncan, Beverly Stephenson ,  Lohmueller, Steven Joseph

IPC: F23R3/34

CPC classification number: F23R3/346 ,  F23C2201/20 ,  F23C2201/401

公开(公告)号：EP1793097A1

公开(公告)日：2007-06-06

申请号：EP06255019.9

申请日：2006-09-28

Applicant: General Electric Company

Inventor： Lohmueller, Steven Joseph ,  Czachor, Robert Paul

IPC: F01D25/28 ,  F02C3/14 ,  F23R3/60

CPC classification number: F01D25/28 ,  F05D2230/642 ,  F05D2240/35 ,  F23R3/60

Abstract: A method for assembling a gas turbine engine (13) includes coupling an axisymmetric structure within the gas turbine engine, wherein the axisymmetric structure includes at least one mounting bushing (3) extending from a radially outer surface of the axisymmetric structure, and inserting a pin (110) having a crowned surface at least partially into the mounting bushing such that the pin provides both axial and tangential support to the axisymmetric structure, and securing the pin to the gas turbine engine utilizing a retaining assembly (140).

Abstract translation: 一种用于组装燃气涡轮发动机（13）的方法，包括在燃气涡轮发动机内连接轴对称结构，其中所述轴对称结构包括从所述轴对称结构的径向外表面延伸的至少一个安装衬套（3） （110）具有至少部分地到所述安装衬套中的凸面，使得所述销向所述轴对称结构提供轴向和切向支撑，并且使用保持组件（140）将所述销固定到所述燃气涡轮发动机。

公开(公告)号：EP1445539B1

公开(公告)日：2014-12-17

申请号：EP04250446.4

申请日：2004-01-28

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Mancini, Alfred Albert ,  Lohmueller, Steven Joseph

IPC: F23R3/34 ,  F23K5/18

CPC classification number: F23K5/18 ,  F23D2209/30 ,  F23R3/343

公开(公告)号：EP2075507A2

公开(公告)日：2009-07-01

申请号：EP08165970.8

申请日：2008-10-07

Applicant: General Electric Company

Inventor： Lohmueller, Steven Joseph

IPC: F23R3/04 ,  F23R3/26 ,  F23R3/28

CPC classification number: F23R3/04 ,  F23R3/26 ,  F23R3/283 ,  Y02T50/675

Abstract: A combustor (37) for a gas turbine engine (21) is provided. The combustor includes a housing (33) at least in part defining an internal combustion chamber (47) of the combustor, a combustor component held in communication with the combustion chamber, and a ferrule (37) generally coupled to the housing and being moveable relative thereto between a first position and a second position, the ferrule having a primary opening (51) through which the combustor component extends for support of the combustor component by the ferrule such that the combustor component is moveable conjointly with the ferrule relative to the housing, the ferrule further having a plurality of purge gas openings (55,57,59) formed therein separate from and in transversely spaced relationship with the primary opening to allow purge gas to flow through the ferrule into the combustion chamber, the purge gas openings being located in the ferrule such that in the first position of the ferrule the purge gas openings comprise at least one blocked purge gas opening that is blocked against the flow of purge gas therethrough into the combustion chamber and at least one unblocked purge gas opening through which purge gas is permitted to flow into the combustion chamber, and in the second position of the ferrule at least one of the blocked purge gas openings of the first ferrule position is unblocked to permit the flow of purge gas therethrough into the combustion chamber.

公开(公告)号：EP1445539A1

公开(公告)日：2004-08-11

申请号：EP04250446.4

申请日：2004-01-28

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Mancini, Alfred Albert ,  Lohmueller, Steven Joseph

IPC: F23R3/34 ,  F23K5/18

CPC classification number: F23K5/18 ,  F23D2209/30 ,  F23R3/343

Abstract: A fuel injector (10) includes an annular main fuel nozzle received within an annular nozzle housing, a main nozzle fuel circuit having at least one annular leg, and a pilot nozzle fuel circuit. Spray orifices (106) of the leg extend through the fuel nozzle and spray wells (220) through the housing are aligned with the orifices (106). The nozzle is designed to generate sufficient static pressure differentials between at least two different ones of the spray wells (220) to purge the main nozzle fuel circuit (102). Spray well portions (222) may be asymmetrically flared out with respect to a spray well centerline (224) in different local streamwise directions (225). Some of the spray well portions (222) may be asymmetrically flared out in a local upstream direction (226) and others in a local downstream direction (228). The local streamwise direction (225) may have an axial component (236) parallel to a nozzle axis about which the annular nozzle housing is circumscribed and a circumferential component (234) around the nozzle housing.

Abstract translation: 燃料喷射器（10）包括容纳在环形喷嘴壳体内的环形主燃料喷嘴，具有至少一个环形腿部的主喷嘴燃料回路和引燃喷嘴燃料回路。 腿的喷孔（106）延伸穿过燃料喷嘴，并且通过壳体的喷射井（220）与孔口（106）对齐。 喷嘴被设计成在至少两个不同喷雾井（220）之间产生足够的静压差，以清除主喷嘴燃料回路（102）。 在不同的局部流动方向（225）上，相对于喷雾井中心线（224），喷射井部分（222）可以不对称地展开。 一些喷井部分（222）可以在局部上游方向（226）不对称地向外扩张，而在局部下游方向（228）可以是不对称的。 局部流动方向（225）可以具有平行于喷嘴轴线的轴向分量（236），环形喷嘴壳体周围围绕喷嘴轴线和围绕喷嘴壳体的周向部件（234）。

公开(公告)号：EP1186832A3

公开(公告)日：2002-04-24

申请号：EP01307493.5

申请日：2001-09-04

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Hura, Harjit Singh ,  Cooper, James Neil ,  Mongia, Hukam Chand ,  Sabla, Paul Edward ,  Duncan, Beverly Stephenson ,  Lohmueller, Steven Joseph

IPC: F23R3/34

CPC classification number: F23R3/346 ,  F23C2201/20 ,  F23C2201/401

Abstract: A two-stage fuel nozzle assembly (56) for a gas turbine engine. The primary combustion region (120) is centrally positioned and includes a fuel injector (122) that is surrounded by one or more swirl chambers (132, 160) to provide a fuel air mixture that is ignited to define a first stage combustion zone. A secondary combustion region is provided by an annular housing (168) that surrounds the primary combustion region (120) and it includes a secondary fuel injector (126) having a radially-outwardly-directed opening (172) and surrounded by an annular ring (128) that includes openings (194) for providing a swirl chamber for the secondary combustion region (124). Cooling air is directed angularly between the primary and secondary combustion zones to delay intermixing and thereby allow more complete combustion of the respective zones prior to their coalescing further downstream. The primary combustion region (120) is activated during idle and low engine power conditions, and both the primary (120) and secondary (124) combustion regions are activated during high engine power conditions.

Abstract translation: 一种用于燃气涡轮发动机的两级燃料喷嘴组件（56）。 主燃烧区域（120）位于中央，并且包括被一个或多个涡流室（132,160）包围的燃料喷射器（122），以提供被点燃以限定第一阶段燃烧区域的燃料空气混合物。 二次燃烧区域由围绕主燃烧区域（120）的环形壳体（168）提供，并且其包括具有径向向外指向的开口（172）并且被环形圈（120）包围的次级燃料喷射器（126） 128），其包括用于为所述第二燃烧区域（124）提供涡流室的开口（194）。 冷却空气在初级燃烧区和次级燃烧区之间有角度地引导，以延迟混合，从而允许相应区在更下游的聚结之前更完全地燃烧。 在怠速和低发动机功率状态期间主燃烧区域（120）被激活，并且在高发动机功率状态期间主燃烧区域（120）和次燃烧区域（124）都被激活。