专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US6101806A Tri-mode combustion system 有权
标题翻译：三模燃烧系统
公开(公告)号：US6101806A
公开(公告)日：2000-08-15
申请号：US143588
申请日：1998-08-31
申请人： Daih-Yeou Chen , Cristopher Frost , Hans Heydrich , Ronald B. Pardington
发明人： Daih-Yeou Chen , Cristopher Frost , Hans Heydrich , Ronald B. Pardington
IPC分类号： F02C3/13 , F02C6/16 , F02C7/268
CPC分类号： F02C6/16 , F02C3/13 , F05D2220/50 , Y02E60/15
摘要： A turbine engine is disclosed that is capable of operating in an emergency power mode, an air breathing auxiliary power mode and a bypass bleed environmental control mode. In a preferred embodiment of the invention, the engine comprises in working fluid flow order a compressor for compressing air, a combustion chamber and a power turbine for extracting mechanical work from heated and/or compressed air. The compressor and turbine are separately coupled by a shaft which is also coupled to a generator for supplying electrical power and a cooling turbine for supplying cooled air to the aircraft cabin and avionics. The combustion chamber has an upstream combustor inlet and a downstream combustor inlet, each of which may admit compressed air either to be mixed with fuel for combustion, or to pass directly to the combustor outlet which is operatively attached to the power turbine section inlet. During emergency/starting operation, the combustion chamber and turbine section receive compressed air from a stored air accumulator through a stored air inlet. During normal air breathing operation, the combustion chamber and turbine section receive compressed air from a compressor through an air breathing inlet. During bypass bleed operation, the combustion chamber and turbine section receive compressed air from the aircraft main engine through a bypass bleed air inlet. The tri-mode operation is made possible by a unique two-way bypass ring having a plurality of axial passages communicating the stored air inlet and air breathing inlet with the upstream combustor inlet and a plurality of radial passages communicating the bypass bleed inlet with the downstream combustor inlet. A valving system selectively admits compressed air into the combustor and turbine section from the stored air inlet, air breathing inlet or bypass bleed inlet depending on the mode of operation.
摘要翻译：公开了一种涡轮发动机，其能够在紧急动力模式，空气呼吸辅助动力模式和旁路出血环境控制模式下操作。在本发明的优选实施例中，发动机包括工作流体流动的压缩空气压缩机，燃烧室和动力涡轮机，用于从加热和/或压缩空气中提取机械作业。压缩机和涡轮机分别由轴连接，轴也耦合到用于提供电力的发电机和用于向飞机机舱和航空电子设备供应冷却空气的冷却涡轮机。燃烧室具有上游燃烧器入口和下游燃烧器入口，每个入口可以允许压缩空气与燃料混合以便燃烧，或者直接通到可操作地连接到动力涡轮机部分入口的燃烧室出口。在紧急/启动操作期间，燃烧室和涡轮部分通过储存的空气入口从储存的空气储存器接收压缩空气。在正常的呼吸呼吸操作期间，燃烧室和涡轮部分通过空气吸入口从压缩机接收压缩空气。在旁路泄放操作期间，燃烧室和涡轮部分通过旁路放气入口接收来自飞机主机的压缩空气。通过具有多个轴向通道的独特的双向旁路环来实现三模式操作，所述多个轴向通道将存储的空气入口和空气呼吸入口与上游燃烧器入口连通，以及多个径向通道将旁路出气口与下游燃烧器入口。阀门系统根据操作模式，从储存的空气入口，空气呼吸入口或旁路渗流入口选择性地将压缩空气进入燃烧器和涡轮机部分。

2. 发明申请

US20060037326A1 Dual ignition system for a gas turbine engine 有权
公开(公告)号：US20060037326A1
公开(公告)日：2006-02-23
申请号：US10922471
申请日：2004-08-20
申请人： Michael Mehrer , Daih-Yeou Chen
发明人： Michael Mehrer , Daih-Yeou Chen
IPC分类号： F02C7/264
CPC分类号： F02P15/08 , F02C7/264 , F02P15/003 , F23N2027/02 , F23N2041/20
摘要： A dual channel ignition circuit (Channel A and a Channel B). In a start sequence in which a successful ignition event occurs, an exciter controller first energizes only a primary ignition channel (Channel A). Once the exciter controller recognizes a success light-off, the alternate channel (Channel B) will also then be excited as the gas turbine engine is accelerated to a self-sustaining speed. The exciter controller will then switch the primary alternative designation of the channels for the next start attempt. In a start sequence in which an unsuccessful ignition event occurs, the exciter controller sets a fail-to-start on the primary ignition channel on a failure to start A/B counter such that a failed ignition channel is diagnosed without dedicated electronic diagnostic circuits while still attempting to excite both circuits to enhance the dependability of a successful engine light-off.

3. 发明授权

US06955053B1 Pyrospin combuster 有权
标题翻译：焦油燃烧器
公开(公告)号：US06955053B1
公开(公告)日：2005-10-18
申请号：US10186640
申请日：2002-07-01
申请人： Daih-Yeou Chen , Chris Hayden , Dietmar Trees , Paul Piconi , Tony Reichmann , Jack Vitale
发明人： Daih-Yeou Chen , Chris Hayden , Dietmar Trees , Paul Piconi , Tony Reichmann , Jack Vitale
IPC分类号： F23R3/06 , F23R3/50 , F23R3/54 , F23R3/58
CPC分类号： F23R3/54 , F23R3/06 , F23R3/50 , F23R3/58 , F23R2900/03041
摘要： An annular combustor that has angled effusion holes through at least one surface of the combustor liner with the angle of the effusion holes oriented to cause the flow of air through the holes to facilitate swirling of the fuel and air within the combustor. The effusion holes thereby facilitate efficient cooling of the combustor liner combined with superior fuel/air mixing within the combustor.
摘要翻译：一种环形燃烧器，其具有穿过燃烧器衬套的至少一个表面的成角度的溢流孔，其中排出孔的角度被定向成使空气流过孔，以促进燃烧器内的燃料和空气的旋转。渗出孔因此有助于燃烧器衬套的有效冷却与燃烧器内的优良燃料/空气混合相结合。

4. 发明申请

US20090199563A1 Scalable pyrospin combustor 审中-公开
标题翻译：可扩展的火焰燃烧器
公开(公告)号：US20090199563A1
公开(公告)日：2009-08-13
申请号：US12069107
申请日：2008-02-07
申请人： Daih-Yeou Chen
发明人： Daih-Yeou Chen
IPC分类号： F23R3/20 , F02C7/22 , F02C7/12
CPC分类号： F23R3/52 , F02C7/222 , F23R3/06 , F23R2900/03041 , Y02T50/67 , Y02T50/675
摘要： An axial-flow pyrospin combustor comprises inner and outer combustor liners and a plurality of pyrospin effusion holes. The inner liner is coaxially mounted inside the outer liner, about a central combustor axis. The pyrospin effusion holes are formed in at least one of the outer combustor liner and the inner combustor liner. Each of the pyrospin effusion holes has a down angle and a back angle, which control a global swirl flow about the central axis, and promote film cooling without detachment.
摘要翻译：轴流式火焰喷射燃烧器包括内部和外部燃烧器衬套和多个焦油喷射孔。内衬层围绕中心燃烧器轴线同轴地安装在外衬里内。火焰喷射孔形成在外燃烧器衬套和内燃烧器衬套中的至少一个中。每个焦油喷射孔具有向下的角度和后角，其控制围绕中心轴线的全局旋转流动，并且促进薄膜冷却而不脱离。

5. 发明授权

US07509812B2 Dual ignition system for a gas turbine engine 有权
标题翻译：燃气涡轮发动机的双重点火系统
公开(公告)号：US07509812B2
公开(公告)日：2009-03-31
申请号：US10922471
申请日：2004-08-20
申请人： Michael E. Mehrer , Daih-Yeou Chen
发明人： Michael E. Mehrer , Daih-Yeou Chen
IPC分类号： F02C7/22
CPC分类号： F02P15/08 , F02C7/264 , F02P15/003 , F23N2027/02 , F23N2041/20
摘要： A dual channel ignition circuit (Channel A and a Channel B). In a start sequence in which a successful ignition event occurs, an exciter controller first energizes only a primary ignition channel (Channel A). Once the exciter controller recognizes a success light-off, the alternate channel (Channel B) will also then be excited as the gas turbine engine is accelerated to a self-sustaining speed. The exciter controller will then switch the primary alternative designation of the channels for the next start attempt. In a start sequence in which an unsuccessful ignition event occurs, the exciter controller sets a fail-to-start on the primary ignition channel on a failure to start A/B counter such that a failed ignition channel is diagnosed without dedicated electronic diagnostic circuits while still attempting to excite both circuits to enhance the dependability of a successful engine light-off.
摘要翻译：双通道点火电路（通道A和通道B）。在其中发生成功的点火事件的启动顺序中，励磁机控制器首先仅激励初级点火通道（通道A）。一旦励磁机控制器识别到成功点亮，则随着燃气涡轮发动机加速到自持速度，备用通道（通道B）也将被激励。然后，激励器控制器将切换下一次启动尝试的通道的主要替代指定。在发生不成功的点火事件的启动顺序中，激励器控制器在启动A / B计数器的故障时在初级点火通道上设置故障启动，使得在没有专用电子诊断电路的情况下诊断故障点火通道，而仍然试图激励两个电路，以增强成功引擎熄灭的可靠性。

6. 发明授权

US07559696B2 Active thrust management system 有权
标题翻译：主动推力管理系统
公开(公告)号：US07559696B2
公开(公告)日：2009-07-14
申请号：US10929803
申请日：2004-08-30
申请人： Carlos Oncina , Michael E. Mehrer , Bing Tong , Pete Suttie , Daih-Yeou Chen , William Dornfield
发明人： Carlos Oncina , Michael E. Mehrer , Bing Tong , Pete Suttie , Daih-Yeou Chen , William Dornfield
IPC分类号： F16C32/06
CPC分类号： F01D3/04 , F16C39/04
摘要： An active thrust management system varies pressure responsive to changes in rotor assembly thrust to maintain a desired position. The system includes a bearing supporting rotation of a rotor assembly within a pressurizing chamber. The rotor assembly is supported on a cushion of air generated between the bearing and the rotor assembly. Pressure within a cavity adjacent the rotor assembly opposes a thrust force to maintain a desired position of the rotor assembly. Modulating airflow into the pressurizing chamber adjacent the rotor assembly compensates for changes in the thrust generated by the rotor assembly to maintain the desired rotor assembly position.
摘要翻译：主动推力管理系统根据转子组件推力的变化来改变压力以保持期望的位置。该系统包括支撑转子组件在加压室内的旋转的轴承。转子组件支撑在轴承和转子组件之间产生的空气衬垫上。与转子组件相邻的空腔内的压力抵抗推力以保持转子组件的期望位置。调节与转子组件相邻的加压室中的气流补偿由转子组件产生的推力的变化，以维持所需的转子组件位置。

7. 发明授权

US07302801B2 Lean-staged pyrospin combustor 有权
标题翻译：精馏级焦油燃烧器
公开(公告)号：US07302801B2
公开(公告)日：2007-12-04
申请号：US10827573
申请日：2004-04-19
申请人： Daih-Yeou Chen
发明人： Daih-Yeou Chen
IPC分类号： F23R3/34
CPC分类号： F23R3/54 , F23D2900/00014 , F23R3/34
摘要： A combustor assembly includes a combustor chamber having a primary and intermediate zone that provides for reduced flame temperatures. The combustor assembly includes first and second pluralities of injectors. The first plurality of injectors introduces fuel to a primary zone. A second plurality of injectors introduces fuel to an intermediate zone. During operation between initial start up and before the introduction of engine load, fuel is introduced into the primary zone only by the first plurality of injectors. Once engine load is applied to the engine, fuel is introduced into the intermediate zone by the second plurality of injectors. Introduction of additional volume of fuel allows the fuel-air ratio to remain constant regardless of engine operating conditions. The constant fuel-air ratio is maintained at a desired rate to lower flame temperatures and reduce nitrous oxide emissions.
摘要翻译：燃烧器组件包括具有主要和中间区域的燃烧器室，其提供降低的火焰温度。燃烧器组件包括第一和第二多个喷射器。第一组多个喷射器将燃料引入主区域。第二组多个喷射器将燃料引入中间区域。在初始启动之前和引入发动机负载之前的操作期间，燃料仅由第一多个喷射器引入主区域。一旦发动机负载被施加到发动机，燃料通过第二多个喷射器被引入中间区域。引入附加体积的燃料允许燃料 - 空气比保持恒定，不管发动机的运行条件如何。恒定的燃料空气比保持在期望的速率以降低火焰温度并减少一氧化二氮排放。

8. 发明授权

US07095601B2 High energy primary spark ignition system for a gas turbine engine 有权
标题翻译：用于燃气涡轮发动机的高能一次火花点火系统
公开(公告)号：US07095601B2
公开(公告)日：2006-08-22
申请号：US10922699
申请日：2004-08-20
申请人： Michael E. Mehrer , Daih-Yeou Chen , Joseph James
发明人： Michael E. Mehrer , Daih-Yeou Chen , Joseph James
IPC分类号： G08B21/00
CPC分类号： F02C7/266
摘要： An exciter circuit for a gas turbine engine delivers a first single high-energy spark followed by subsequent sparks of relatively lower energy to ensures start reliability by specifically clearing ice build-up at the ignition plugs.
摘要翻译：用于燃气涡轮发动机的激励器电路提供第一单个高能量火花，随后是相对较低能量的随后火花，以通过特别地清除点火塞上的积冰来确保启动可靠性。

9. 发明申请

US20050229604A1 Lean-staged pyrospin combustor 有权
标题翻译：精馏级焦油燃烧器
公开(公告)号：US20050229604A1
公开(公告)日：2005-10-20
申请号：US10827573
申请日：2004-04-19
申请人： Daih-Yeou Chen
发明人： Daih-Yeou Chen
IPC分类号： F23R3/34 , F23R3/54
CPC分类号： F23R3/54 , F23D2900/00014 , F23R3/34
摘要： A combustor assembly includes a combustor chamber having a primary and intermediate zone that provides for reduced flame temperatures. The combustor assembly includes first and second pluralities of injectors. The first plurality of injectors introduces fuel to a primary zone. A second plurality of injectors introduces fuel to an intermediate zone. During operation between initial start up and before the introduction of engine load, fuel is introduced into the primary zone only by the first plurality of injectors. Once engine load is applied to the engine, fuel is introduced into the intermediate zone by the second plurality of injectors. Introduction of additional volume of fuel allows the fuel-air ratio to remain constant regardless of engine operating conditions. The constant fuel-air ratio is maintained at a desired rate to lower flame temperatures and reduce nitrous oxide emissions.
摘要翻译：燃烧器组件包括具有主要和中间区域的燃烧器室，其提供降低的火焰温度。燃烧器组件包括第一和第二多个喷射器。第一组多个喷射器将燃料引入主区域。第二组多个喷射器将燃料引入中间区域。在初始启动之前和引入发动机负载之前的操作期间，燃料仅由第一多个喷射器引入主区域。一旦发动机负载被施加到发动机，燃料通过第二多个喷射器被引入中间区域。引入附加体积的燃料允许燃料 - 空气比保持恒定，不管发动机的运行条件如何。恒定的燃料空气比保持在期望的速率以降低火焰温度并减少一氧化二氮排放。

10. 发明申请

US20110072823A1 GAS TURBINE ENGINE FUEL INJECTOR 审中-公开
标题翻译：燃气涡轮发动机燃油喷射器
公开(公告)号：US20110072823A1
公开(公告)日：2011-03-31
申请号：US12570103
申请日：2009-09-30
申请人： Daih-Yeou Chen , Xiaolan Hu
发明人： Daih-Yeou Chen , Xiaolan Hu
IPC分类号： F02C7/22
CPC分类号： F02C7/222 , F23R3/28 , F23R3/50
摘要： An example gas turbine engine fuel injector nozzle assembly includes a nozzle tip secured relative to a combustion area within a gas turbine engine. The nozzle establishes a plurality of first apertures that are configured to communicate a fuel to the combustion area. The nozzle establishes at least one second aperture that is configured to communicate a fluid to the combustion area. The fluid is different than the fuel. An example method of providing fuel to a combustion area within a gas turbine engine includes communicating a fuel through a first aperture in a nozzle tip to a combustion area in a gas turbine engine. The nozzle tip establishes an axis. The method also includes influencing fuel moving from the nozzle tip using a fluid directed through a second aperture in the nozzle tip. The fluid is different than the fuel. A portion of the second aperture is radially closer to the axis than the first aperture.
摘要翻译：示例性燃气涡轮发动机燃料喷射器喷嘴组件包括相对于燃气涡轮发动机内的燃烧区域固定的喷嘴尖端。喷嘴建立多个第一孔，其构造成将燃料传送到燃烧区。喷嘴建立至少一个第二孔，其构造成将流体传送到燃烧区。流体与燃料不同。向燃气涡轮发动机内的燃烧区域提供燃料的示例性方法包括将燃料通过喷嘴尖端中的第一孔连通到燃气涡轮发动机的燃烧区域。喷嘴尖端建立一个轴。该方法还包括影响使用引导通过喷嘴尖端中的第二孔的流体从喷嘴尖端移动的燃料。流体与燃料不同。第二孔的一部分比第一孔径向更靠近轴线。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式