公开(公告)号：US06729141B2

公开(公告)日：2004-05-04

申请号：US10190285

申请日：2002-07-03

申请人： Joe Britt Ingram

发明人： Joe Britt Ingram

IPC分类号： F23R304

CPC分类号： F23R3/50 ,  F23C2900/03001 ,  F23R3/045

摘要： Air tubes are circumferentially spaced around the outer liner of an annular combustor for a microturbine engine in proximity to and downstream of a dam extending into the combustion chamber for reducing the emission of NOX. The air tubes are dimensioned so that the length to passage diameter is such that a swirling motion of the air injected into the combustion zone is normal to the center line of the annular combustor.

公开(公告)号：US5687572A

公开(公告)日：1997-11-18

申请号：US970420

申请日：1992-11-02

申请人： Jeffrey P. Schrantz ,  David R. Squire

发明人： Jeffrey P. Schrantz ,  David R. Squire

IPC分类号： F23R3/00 ,  F23R3/04 ,  F23R3/06

CPC分类号： F23R3/045 ,  F23R3/007 ,  F23R3/06 ,  F05B2260/201 ,  F23R2900/03041 ,  F23R2900/03044

摘要： A combustor for a gas turbine engine having a porous outer metallic shell and a thin-walled, nonporous ceramic liner whose backside is impingement cooled, with only primary and secondary openings in the ceramic liner for delivering pressurized primary air and dilution air to the combustion zone.

摘要翻译： 一种用于燃气涡轮发动机的燃烧器，其具有多孔外部金属壳体和薄壁无孔陶瓷衬套，其背面被冲击冷却，仅在陶瓷衬套中具有用于将加压的一次空气和稀释空气输送到燃烧区域的初级和次级开口 。

公开(公告)号：US5317864A

公开(公告)日：1994-06-07

申请号：US954971

申请日：1992-09-30

申请人： Linn C. Shorb ,  Michael W. Sledd ,  Jack R. Shekleton

发明人： Linn C. Shorb ,  Michael W. Sledd ,  Jack R. Shekleton

IPC分类号： F23R3/04 ,  F23R3/28 ,  F23R3/50 ,  F23R3/32 ,  F02C7/22

CPC分类号： F23R3/50 ,  F23R3/045 ,  F23R3/28 ,  F05B2220/50 ,  F05B2250/322 ,  Y02T50/675

摘要： Difficulties in downsizing annular combustors (20) due to orienting fuel injectors with respect to oxidant blast tubes are avoided in a construction for a combustor (20) including radially spaced annular walls (22, 24) and an interconnecting radial wall (26) defining an annular combustion chamber (32). A plurality of circumferentially spaced tubes (28, 30) extend through the radially outermost annular wall (24) and are directed generally tangentially into the combustion space (32). A plurality of fuel injectors (42) are provided for directing fuel radially inwardly into the space (32) and are circumferentially spaced about the combustion space (32) and located between the tubes (28).

摘要翻译： 在包括径向隔开的环形壁（22,24）和相互连接的径向壁（26）的燃烧器（20）的结构中避免了因相对于氧化剂鼓风管定向燃料喷射器来减小环形燃烧器（20）的难度， 环形燃烧室（32）。 多个周向间隔开的管（28,30）延伸穿过径向最外面的环形壁（24），并且大致切向地指向燃烧空间（32）。 设置多个燃料喷射器（42），用于将燃料径向向内引导到空间（32）中，并且围绕燃烧空间（32）周向间隔开并且位于管（28）之间。

公开(公告)号：US5277021A

公开(公告)日：1994-01-11

申请号：US698994

申请日：1991-05-13

申请人： Jack R. Shekleton

发明人： Jack R. Shekleton

IPC分类号： F02C3/05 ,  F02C7/18 ,  F23R3/00 ,  F23R3/04 ,  F23R3/28 ,  F23R3/06

CPC分类号： F23R3/002 ,  F23R3/045 ,  F23R3/28 ,  F05B2220/50 ,  F05B2260/202 ,  Y02T50/675

摘要： In order to facilitate enhanced starting of gas turbines at very high altitudes where the cost must be low and the design must be simple, a turbine engine (10) is disclosed. It includes a turbine wheel (12) coupled to a compressor (14) for driven movement, a nozzle (16) for directing gases of combustion at the turbine wheel 12), and an annular combustor (18) defining an annular combustion space upstream of the turbine wheel (12) in fluid communication with both the compressor (14) and the nozzle (16). The combustor (18) receives fuel from a source and air from the compressor (14) and combusts them in the combustion space to generate the gases of combustion. The combustor (18) is defined by an annular outer wall (20), an annular inner wall (22), and a radial wall (24) extending therebetween opposite the nozzle (16). The turbine engine (10) also includes at least one air blast fuel injector (26) disposed in the annular outer wall (20) of the combustor (18) for injecting atomized fuel generally tangentially of the outer wall (20) outwardly of a flame zone (28) within the combustion space. In order to achieve the objectives of the present invention, and to do so in a manner which does not require sophisticated fuel injector or combustor designs, the turbine engine (10) utilizes air film strips (36, 38, 40) and/or holes (20b, 22b, 24b) for cooling the combustor (18) with an air film on an inwardly facing surface of one or more of the walls (20, 22, 24) defining the combustor (18) while at the same time avoiding the filming of air onto the outer wall (20) radially outwardly of and generally axially coextensive with the flame zone (28).

摘要翻译： 为了便于在非常高的高度的燃气轮机的增加启动，其中成本必须低，并且设计必须简单，公开了一种涡轮发动机（10）。 其包括联接到用于驱动运动的压缩机（14）的涡轮机叶轮（12），用于引导涡轮机叶轮12处的燃烧气体的喷嘴（16））和环形燃烧器（18），其限定环形燃烧空间 涡轮机叶轮（12）与压缩机（14）和喷嘴（16）流体连通。 燃烧器（18）从源头和来自压缩机（14）的空气接收燃料并将其燃烧在燃烧空间中以产生燃烧气体。 燃烧器（18）由环形外壁（20），环形内壁（22）和在喷嘴（16）之间延伸的径向壁（24）限定。 涡轮发动机（10）还包括设置在燃烧器（18）的环形外壁（20）中的至少一个鼓风燃料喷射器（26），用于从火焰向外大致切向地将外壁（20）切向喷射雾化燃料 区域（28）。 为了实现本发明的目的，并且以不需要复杂的燃料喷射器或燃烧器设计的方式来实现，涡轮发动机（10）利用空气膜条（36,38,40）和/或孔 （20b，22b，24b），用于在限定燃烧器（18）的一个或多个壁（20,22,24）的面向内的表面上用空气膜冷却燃烧器（18），同时避免 将空气在与火焰区域（28）径向向外并大致轴向共延伸的外壁（20）上成膜。

公开(公告)号：US5235805A

公开(公告)日：1993-08-17

申请号：US851167

申请日：1992-03-12

申请人： Gerard Y. G. Barbier ,  Xavier M. H. Bardey ,  Michel A. A. Desaulty ,  Serge M. Meunier

发明人： Gerard Y. G. Barbier ,  Xavier M. H. Bardey ,  Michel A. A. Desaulty ,  Serge M. Meunier

IPC分类号： F23R3/04 ,  F23R3/26

CPC分类号： F23R3/045 ,  F23R3/26

摘要： An oxidizer intake flow control system is disclosed for a gas turbine engine combustion chamber. The chamber has an oxidizer intake assembly which extends through the wall of the chamber such that an inlet aperture of the oxidizer intake and an exhaust aperture of the oxidizer intake are located on opposite sides of the wall defining the combustion chamber. An oxidizer intake sleeve defines a central passage through which oxidizer may pass into the combustion chamber. The intake passage extends along a central axis and the intake assembly is attached to the wall of the combustion chamber such that it is rotatable about this central axis. The inlet aperture and/or the exhaust aperture is located in a plane extending non-perpendicularly to the central axis. The combustion chamber may have several oxidizer intake assemblies extending through the combustion chamber walls. The intake assemblies may be interconnected such that they may be simultaneously rotated with respect to the combustion chamber wall.

摘要翻译： 公开了一种用于燃气涡轮发动机燃烧室的氧化剂进气流量控制系统。 腔室具有氧化剂进入组件，其延伸穿过腔室的壁，使得氧化剂吸入口的入口孔和氧化剂吸入口的排气口位于限定燃烧室的壁的相对侧上。 氧化剂进气套限定了中心通道，氧化剂可通过该中心通道进入燃烧室。 进气通道沿中心轴线延伸，并且进气组件附接到燃烧室的壁，使得其可围绕该中心轴线旋转。 入口孔和/或排气孔位于非垂直于中心轴延伸的平面中。 燃烧室可以具有延伸穿过燃烧室壁的几个氧化剂进料组件。 进气组件可以互连，使得它们可以相对于燃烧室壁同时旋转。

公开(公告)号：US5187937A

公开(公告)日：1993-02-23

申请号：US659353

申请日：1991-02-19

申请人： Stanley J. Stevens ,  Jonathan F. Carrotte

发明人： Stanley J. Stevens ,  Jonathan F. Carrotte

IPC分类号： F23R3/04 ,  F23R3/06

CPC分类号： F23R3/06 ,  F23R3/045 ,  Y02T50/675

摘要： A gas turbine engine combustor, eg of annular combustor configuration, has air inlets, typically in the dilution zone, which incorporate vortex generators operative to trip the inlet jet flow causing stabilizing vortex flow at the lateral edges of the jet. The vortex generators can comprise an inwardly directed abrupt change of section between forward and rearward parts of the air inlets. The rearward section of the air inlets can have a configuration operative to reinforce the jet stabilizing effect of the vortex flow. The combustor exhibits improved uniformity of jet and crossflow mixing.

公开(公告)号：US5140808A

公开(公告)日：1992-08-25

申请号：US686038

申请日：1991-04-16

申请人： Jack R. Shekleton ,  Melvin K. Lafferty

发明人： Jack R. Shekleton ,  Melvin K. Lafferty

IPC分类号： F23R3/04 ,  F23R3/06 ,  F23R3/32 ,  F23R3/54

CPC分类号： F23R3/54 ,  F23R3/045 ,  F23R3/06 ,  F23R3/32

摘要： A gas turbine engine 10 having a rotor 12 with turbine blades 14 and a nozzle 16 adjacent the turbine blades 14 for directing hot gases of combustion at the turbine blades 14. The engine 10 also includes an annular combustor 18 about the rotor 12 and an annular combustor housing 30 substantially surrounding the combustor 18 in generally concentric spaced relation. A fuel injection system is operatively associated with the combustor 18 for injecting fuel into a combustion space 28 to be combusted with air from a compressor 34. The fuel injection system may include a plurality of circumferentially spaced fuel injectors 68 disposed in an outer wall 20 of the combustor 18 together with a generally oval shaped manifold 70 in fluid communication with a primary fuel source and the fuel injectors 68. A turbine shrould 36 is provided to extend radially outward from the rotor to the outer wall of the combustor on the side of the nozzle 16 opposite the combustion space 28. The turbine shroud 36 is cooled by a film of air which passes through a plurality of circumferentially spaced orifices 40/20 in the outer wall 20 of the combuston 18. The engine 10 also includes an abutment member 38, 60 and a spacing member 66 between the combustor 18 and the housing 30. With this arrangement, the combustor 18 and the housing 30 can be maintained in generally concentric preslected axial relation.

摘要翻译： 具有转子12的燃气涡轮发动机10具有涡轮机叶片14和与涡轮机叶片14相邻的喷嘴16，用于在涡轮叶片14处引导燃烧的热气体。发动机10还包括围绕转子12的环形燃烧器18和环形 燃烧器壳体30基本上围绕燃烧器18以大致同心间隔的关系。 燃料喷射系统与燃烧器18可操作地相关联，用于将燃料喷射到燃烧空间28中以与来自压缩机34的空气燃烧。燃料喷射系统可以包括多个周向间隔开的燃料喷射器68，其布置在外壁20中 燃烧器18与通常为椭圆形的歧管70一起与主燃料源和燃料喷射器68流体连通。涡轮机重力36被设置成从转子径向向外延伸到燃烧器的侧壁上 喷嘴16与燃烧空间28相对。涡轮机罩36由通过在燃烧器18的外壁20中的多个周向间隔开的孔40/20的空气膜冷却。发动机10还包括抵接构件38 ，60和在燃烧器18和壳体30之间的间隔构件66.通过这种布置，燃烧器18和壳体30可以保持大致同心 假定的轴向关系。

公开(公告)号：US5113647A

公开(公告)日：1992-05-19

申请号：US455588

申请日：1989-12-22

申请人： Jack R. Shekleton

发明人： Jack R. Shekleton

IPC分类号： F23R3/04 ,  F23R3/28 ,  F23R3/54

CPC分类号： F23R3/045 ,  F23R3/28 ,  F23R3/54 ,  Y02T50/675

摘要： The expense of fabricating an annular combustor (10) for a gas turbine is minimized by providing a combustor housing (12) including an axially extending sleeve (14) and an annular liner (18) disposed within the housing (12) and about the sleeve (14). The annular liner (18) has concentric inner and outer axially elongated walls (20, 22) spaced from the sleeve (14) and the housing (12), respectively, and also has a radially extending wall (24) spaced from the housing (12) and interconnecting the inner and outer walls (20, 22) at one end to define a combustion chamber (26). The liner (18) to spaced from the housing (12) the sleeve (14) to define a compressed air flow path (28) extending from a radially outer compressed air inlet (30) to a radially inner compressed air outlet (32) in communication with the combustion chamber (26) axially remote from the radially extending wall (24). The annular combustor (26) is provided with a plurality of fuel injectors (36, 40) for injecting a liquid fuel to be burned into the liner (18) in a generally tangential direction adjacent the radially extending wall (24) to impact liquid fuel directly onto an inner surface (22a) of the outer wall (22) adjacent to the radially extending wall (24). The annular combustor (26) also includes a plurality of open ended elongated tubes (34) in the outer wall (22) intermediate the compressed air inlet (30) and the radially extending wall (24) to direct air for combustion into the combustion chamber (26). With this arrangement, a mixture of fuel and air may be ignited within the combustion chamber (26) and the resulting hot gases of combustion utilized to drive the gas turbine.

摘要翻译： 制造用于燃气轮机的环形燃烧器（10）的费用通过提供包括轴向延伸的套筒（14）和设置在壳体（12）内的环形衬套（18）的燃烧器壳体（12）和围绕套筒 （14）。 环形衬套（18）具有与套筒（14）和壳体（12）分开的同心的内部和外部轴向细长的壁（20,22），并且还具有与壳体间隔开的径向延伸的壁（24） 12）并且在一端连接所述内壁和外壁（20,22），以限定燃烧室（26）。 衬套（18）与壳体（12）间隔开套筒（14）以限定从径向外部压缩空气入口（30）延伸到径向内部压缩空气出口（32）的压缩空气流动通道（28） 与燃烧室（26）的轴向远离径向延伸的壁（24）连通。 环形燃烧器（26）设置有多个燃料喷射器（36,40），用于沿与径向延伸的壁（24）相邻的大致切向的方向将待燃烧的液体燃料喷射到衬套（18）中，以冲击液体燃料 直接位于邻近径向延伸壁（24）的外壁（22）的内表面（22a）上。 环形燃烧器（26）还包括在压缩空气入口（30）和径向延伸壁（24）之间的外壁（22）中的多个开口的细长管（34），以引导空气燃烧进入燃烧室 （26）。 利用这种布置，可以在燃烧室（26）内点燃燃料和空气的混合物，并产生用于驱动燃气轮机的所产生的热燃烧气体。

公开(公告)号：US4805397A

公开(公告)日：1989-02-21

申请号：US56884

申请日：1987-06-03

申请人： Gerard Y. G. Barbier ,  Gerard J. P. B. Laboure ,  Michel A. A. Desaulty ,  Francois Duchene ,  Pascal M. Truvillot

发明人： Gerard Y. G. Barbier ,  Gerard J. P. B. Laboure ,  Michel A. A. Desaulty ,  Francois Duchene ,  Pascal M. Truvillot

IPC分类号： F23R3/00 ,  F23R3/04 ,  F02C7/20 ,  F02C1/00

CPC分类号： F23R3/045 ,  F23R3/002 ,  F05B2260/201 ,  F05B2260/202

摘要： A combustion chamber for a turbojet engine is disclosed which utilizes double walled construction. Hot walls are attached to adjacent cold walls solely by an orifice member which defines an orifice to supply primary of dilution air to the combustion chamber. The attachment allows relative radial movement of the hot walls with respect to the cold walls so as to accommodate the thermal expansion and contraction of the hot walls. The sleeves forming the walls also cooperate so as to provide an internal cooling film on the interior surface of the hot walls. Convection cooling may also be utilized between the walls to prevent structural damage due to high temperatures.

摘要翻译： 公开了一种用于涡轮喷气发动机的燃烧室，其采用双壁结构。 热壁仅通过孔口构件附接到相邻的冷壁，孔口构件限定了向燃烧室供应初级稀释空气的孔口。 附件允许热壁相对于冷壁的相对径向运动，以适应热壁的热膨胀和收缩。 形成壁的套筒也配合，以在热壁的内表面上提供内部冷却膜。 也可以在壁之间使用对流冷却，以防止由于高温引起的结构损坏。

公开(公告)号：US4151713A

公开(公告)日：1979-05-01

申请号：US777807

申请日：1977-03-15

申请人： Joseph J. Faitani ,  William E. Woodburn, Jr.

发明人： Joseph J. Faitani ,  William E. Woodburn, Jr.

IPC分类号： F23C7/02 ,  F23R3/04 ,  F23R3/06 ,  F23R3/50 ,  F02C7/18

CPC分类号： F23R3/50 ,  F23R3/045 ,  F23R3/06 ,  Y02T50/675

摘要： This invention relates to means for minimizing the smoke emitted from the exhaust of a gas turbine engine by judiciously adding air to the primary burning zone of a combustor at discrete locations. This invention contemplates retrofitting existing burners by substituting the improvement for existing can burner components to obviate the necessity of replacing the entire combustor.

摘要翻译： 本发明涉及通过在离散的位置明智地向燃烧器的主要燃烧区域添加空气来最小化从燃气涡轮发动机的排气排放的烟雾的装置。 本发明考虑通过替代现有罐式燃烧器部件的改进来消除现有燃烧器的改造，从而避免了更换整个燃烧器的必要性。