公开(公告)号：US20110219779A1

公开(公告)日：2011-09-15

申请号：US12721774

申请日：2010-03-11

申请人： Ian Critchley ,  Frank Joseph Zupanc

发明人： Ian Critchley ,  Frank Joseph Zupanc

IPC分类号： F02C9/00 ,  F02C7/22 ,  F02C3/14

CPC分类号： F02C3/14 ,  F02C7/228 ,  F23R3/286 ,  F23R3/343 ,  F23R3/54

摘要： A combustion system for a gas turbine engine is provided. The system includes a forward liner; an aft liner; a combustion chamber formed by the forward liner and the aft liner, the combustion chamber defining a lean combustion zone and a pilot combustion zone; a premixing zone coupled to the combustion chamber; a pilot fuel injector coupled to the combustion chamber and configured to deliver a first flow of fuel to the pilot combustion zone; and a slinger unit configured to deliver a second flow of fuel to the premixing zone such that the second flow of fuel is mixed with air in the premixing zone and directed into the lean combustion zone of the combustion chamber.

摘要翻译： 提供了一种燃气轮机的燃烧系统。 该系统包括一个前向衬垫; 尾衬; 所述燃烧室由所述前部衬套和所述后部衬套形成，所述燃烧室限定稀燃燃烧区域和先导燃烧区域; 耦合到所述燃烧室的预混合区; 联接到所述燃烧室并被配置为将第一燃料流输送到所述先导燃烧区的引燃燃料喷射器; 以及抛油环单元，其构造成将第二燃料流输送到预混合区域，使得第二燃料流与预混合区域中的空气混合并引导到燃烧室的稀燃燃烧区域。

公开(公告)号：US20050097896A1

公开(公告)日：2005-05-12

申请号：US10705580

申请日：2003-11-10

申请人： Ian Critchley ,  Barry Kingery ,  Cristopher Frost ,  David Walhood ,  Robert Sumegi

发明人： Ian Critchley ,  Barry Kingery ,  Cristopher Frost ,  David Walhood ,  Robert Sumegi

IPC分类号： F02C6/00 ,  F02C7/268

CPC分类号： F02C6/00 ,  F05D2220/50 ,  Y02T50/671

摘要： A gas turbine engine integrates the functions of an auxiliary power unit (APU) with one or more functions of an ECS, and that is capable of operating in both an unfired mode and a fired mode. The gas turbine engine includes a combustor system that is configured to allow the gas turbine to quickly transition from the unfired mode to the fired mode, by bypassing a portion of the air flowing to the combustor system around the combustor.

摘要翻译： 燃气涡轮发动机将辅助动力单元（APU）的功能与ECS的一个或多个功能集成，并且能够在未燃烧模式和燃烧模式下操作。 燃气涡轮发动机包括燃烧器系统，其被构造成允许燃气涡轮机通过绕流动到燃烧器系统周围的燃烧器的一部分空气而从未燃烧模式快速转变到燃烧模式。

公开(公告)号：US20070234725A1

公开(公告)日：2007-10-11

申请号：US11393580

申请日：2006-03-29

申请人： Ian Critchley ,  James Hadder

发明人： Ian Critchley ,  James Hadder

IPC分类号： F02C7/22

CPC分类号： F23R3/38 ,  F23R3/52 ,  F23R2900/00005

摘要： A rotary fuel slinger and a turbine engine including the rotary fuel source is provided. The rotary fuel slinger includes a coupler shaft coupled to a turbine shaft of the turbine engine and is configured to rotate therewith. The slinger further includes a slinger disc coupled to the coupler shaft and configured to rotate therewith. The slinger disc includes a vertical shoulder extending substantially perpendicular to the coupler shaft and a slinger disc rim extending substantially perpendicularly from the vertical shoulder. The slinger disc rim is configured to define a cup-shaped section and a counterbalance mass, wherein the cup-shaped section is counterbalanced by the counterbalance mass. The rotary fuel slinger is adapted to receive a rotational drive force and to receive a flow of fuel from a fuel source and configured, upon receipt of the rotational drive force, to centrifuge the received fuel into a combustion chamber of the turbine engine.

摘要翻译： 提供旋转燃料抛油环和包括旋转燃料源的涡轮发动机。 旋转燃料抛油环包括联接到涡轮发动机的涡轮轴的联轴器，并且构造成与其一起旋转。 抛油环还包括联接到联接轴并且被配置为随其旋转的抛油盘。 抛油盘包括基本上垂直于联接轴延伸的垂直肩部和从垂直肩部基本上垂直延伸的抛油环盘缘。 抛油环盘缘被配置为限定杯形部分和平衡块，其中杯形部分由平衡块抵消。 旋转燃料抛油环适于接受旋转驱动力并且接收来自燃料源的燃料流并且在接收到旋转驱动力时构造成将接收到的燃料离心到涡轮发动机的燃烧室中。

公开(公告)号：US20050241316A1

公开(公告)日：2005-11-03

申请号：US10835169

申请日：2004-04-28

申请人： Ly Nguyen ,  Stony Kujala ,  David Walhood ,  Ian Critchley ,  Gregory Woodcock ,  Jurgen Schumacher

发明人： Ly Nguyen ,  Stony Kujala ,  David Walhood ,  Ian Critchley ,  Gregory Woodcock ,  Jurgen Schumacher

IPC分类号： F02C3/14 ,  F23R3/10

CPC分类号： F23R3/10 ,  F23R2900/03041 ,  Y02T50/675

摘要： A dome for a combustion chamber may have a plurality of effusion holes therein to provide efficient cooling while preventing carbon formation on the dome and chamber walls of the combustion chamber. Conventional dome cooling designs, using dome louvers, for example, may become corroded and/or may allow for ingestion of carbon particles that may build up and eventually separate from the dome. Furthermore, the dome cooling design of the present invention allows for the use of a lower profile dome as compared with conventional domes, thereby maximizing liner volume in the constrained combustion envelope while reducing combustor case weight. Additionally, the dome effusion cooling design of the present invention requires the use of less thermal barrier coating, as compared to conventional designs, in order to minimize thermal variation within the dome and between the dome and the combustor wall. A method for uniformly cooling a dome of a combustion chamber of an engine is also disclosed.

摘要翻译： 用于燃烧室的圆顶可以在其中具有多个渗出孔以提供有效的冷却，同时防止燃烧室的圆顶和室壁上的碳形成。 例如，使用圆顶百叶窗的常规圆顶冷却设计可能被腐蚀和/或可能允许摄取可能积聚并最终与圆顶分离的碳颗粒。 此外，本发明的圆顶冷却设计允许与常规圆顶相比使用下部轮廓圆顶，由此在减小燃烧器壳体重量的同时最大化受限燃烧包层中的衬管体积。 此外，与传统设计相比，本发明的圆顶渗出冷却设计需要使用较少的热障涂层，以便最小化圆顶内部和圆顶与燃烧室壁之间的热变化。 还公开了一种用于均匀冷却发动机的燃烧室的圆顶的方法。

公开(公告)号：US20050204744A1

公开(公告)日：2005-09-22

申请号：US10803428

申请日：2004-03-17

申请人： Jurgen Schumacher ,  Ian Critchley ,  David Walhood

发明人： Jurgen Schumacher ,  Ian Critchley ,  David Walhood

IPC分类号： F23R3/04 ,  F23R3/06 ,  F23R3/52

CPC分类号： F23R3/06 ,  F23R3/52 ,  Y02T50/675

摘要： A variable penetration dilution jet array for a single can and scroll assembly includes a plurality of differentially sized dilution openings around the circumference of the combustor can. The alternating smaller and larger openings provide for circumferential and radial mixing uniformity with the smaller openings giving shallow penetration and the larger openings enabling deep core penetration. The larger openings provide dilution air to the hot gas flow core without the need for an increase in combustor pressure drop. The smaller openings provide a film cooling flow to the downstream scroll, reducing dedicated scroll cooling requirements.

摘要翻译： 用于单个罐和涡旋组件的可变渗透稀释喷射阵列包括围绕燃烧器罐的圆周的多个差异尺寸的稀释开口。 交替的较小和较大的开口提供周向和径向混合均匀性，较小的开口提供浅穿透，并且较大的开口使得能够深入岩心穿透。 较大的开口为热气流芯提供稀释空气，而不需要增加燃烧室压降。 较小的开口提供到下游涡卷的薄膜冷却流，从而减少专用的涡旋冷却要求。

公开(公告)号：US20060213200A1

公开(公告)日：2006-09-28

申请号：US11090000

申请日：2005-03-25

申请人： Ian Critchley ,  Bruce Anson ,  Matthew Caspermeyer ,  Mike Scott

发明人： Ian Critchley ,  Bruce Anson ,  Matthew Caspermeyer ,  Mike Scott

IPC分类号： F02C9/26

CPC分类号： F02C9/26

摘要： The present invention provides an adaptive combustion controller and method for a turbine engine. The adaptive combustion controller and method modulates the fuel flow to the turbine engine combustor to reduce combustion instabilities. In particular, the adaptive combustion controller includes a fuel flow phase controller and a fuel flow magnitude controller. The adaptive combustion controller receives sensor data from the turbine engine. In response to the sensor data the fuel flow phase controller adjusts the phase of the modulated fuel flow to reduce instabilities in the combustor. Likewise, in response to the sensor data the fuel flow magnitude controller adjusts the magnitude of the modulated fuel flow to further reduce the instabilities in the combustor. By modulating the fuel flow to the combustor, and adaptively adjusting the phase and magnitude of the modulated fuel flow, the adaptive combustion controller is able to effectively reduce combustion instabilities.

摘要翻译： 本发明提供了一种用于涡轮发动机的自适应燃烧控制器和方法。 自适应燃烧控制器和方法调节到涡轮发动机燃烧器的燃料流量以减少燃烧不稳定性。 特别地，自适应燃烧控制器包括燃料流相位控制器和燃料流量幅值控制器。 自适应燃烧控制器从涡轮发动机接收传感器数据。 响应于传感器数据，燃料流相位控制器调节调制燃料流的相位以减少燃烧器中的不稳定性。 类似地，响应于传感器数据，燃料流量幅度控制器调节调制燃料流量的大小以进一步降低燃烧器中的不稳定性。 通过调节到燃烧器的燃料流量，并且自适应地调整调节燃料流量的相位和幅度，自适应燃烧控制器能够有效地减少燃烧不稳定性。