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公开(公告)号：US20070089424A1
公开(公告)日：2007-04-26
申请号：US11256786
申请日：2005-10-24
IPC分类号： F02C9/26
CPC分类号： F02C9/263 , F05D2270/112 , F05D2270/3032 , F23K5/005 , F23K5/06 , F23K2203/105 , F23N1/00 , F23N1/002 , F23N5/02 , F23N5/022 , F23N5/24 , F23N5/242
摘要： A gas turbine engine combustion system includes a plurality of fuel injectors circumferentially disposed around a combustor in a one to one fuel supply relationship with a plurality of fuel nozzle valves, and an electronic controller for controlling the fuel nozzle valves to eliminate and/or reduce hot streaking in response to sensed hot streak conditions. The fuel nozzle valves may be modulating valves. The electronic controller may be used to individually control the fuel nozzle valves. The hot streak conditions may be sensed with temperature sensors such as temperature sensors operably mounted in the combustor. A program in the electronic controller may be used for determining broken or malfunctioning sensors by calculating a combustor temperature and comparing it to measured temperatures from the sensors and comparing the measured fuel pressures in the individual fuel nozzle circuits with the simulated or calculated fuel pressures.
摘要翻译： 燃气涡轮发动机燃烧系统包括多个燃料喷射器，其周向地设置在与多个燃料喷嘴阀一对一燃料供给关系中的燃烧器周围;以及电子控制器，用于控制燃料喷嘴阀以消除和/或减少热量 响应于感测到的热条件条件。 燃料喷嘴阀可以是调节阀。 电子控制器可以用于单独地控制燃料喷嘴阀。 温度传感器可以感测热条纹条件，诸如可操作地安装在燃烧器中的温度传感器。 电子控制器中的程序可用于通过计算燃烧器温度并将其与来自传感器的测量温度进行比较并将各个燃料喷嘴回路中测量的燃料压力与模拟或计算的燃料压力进行比较来确定破坏或故障的传感器。
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公开(公告)号：US20070214795A1
公开(公告)日：2007-09-20
申请号：US11376507
申请日：2006-03-15
IPC分类号： F02C1/00
CPC分类号： F02K1/06 , F02C9/22 , F02C9/28 , F02K1/08 , F02K1/09 , F02K3/06 , F05D2270/112 , F05D2270/303 , F05D2270/3032
摘要： A method and system for maintaining a limiting gas temperature in a gas turbine engine working fluid flowpath by monitoring the gas temperature and adjusting one or more parameters when the gas temperature exceeds a predetermined or a calculated temperature limit during engine operation. The parameters include one or more of a group of engine parameters including high and low pressure turbine nozzle flow areas, fan and core flow areas, and a rotor speed. The one or more parameters are adjusted to lower the gas temperature to below the temperature limit during engine operation. The limiting gas temperature may be a turbine exhaust gas temperature such as a high pressure turbine exhaust gas temperature. The turbine nozzle flow areas may be adjusted with variable nozzle vanes and the fan and core exhaust nozzle flow areas with a translatable fan nozzle cowling and a translatable core nozzle plug, respectively.
摘要翻译： 一种用于通过监测气体温度并在发动机运行期间当气体温度超过预定或计算的温度极限时调节一个或多个参数来维持燃气涡轮发动机工作流体流路中的限制气体温度的方法和系统。 这些参数包括一组发动机参数中的一个或多个，包括高压和低压涡轮喷嘴流动区域，风扇和核心流动区域以及转子速度。 调节一个或多个参数以在发动机运行期间将气体温度降低到温度极限以下。 限制气体温度可以是涡轮机废气温度，例如高压汽轮机废气温度。 涡轮喷嘴流动面积可以分别用可变喷嘴叶片和风扇和核心排气喷嘴流动区域调节，其中分别具有可平移的风扇喷嘴罩和可平移的芯喷嘴塞。
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公开(公告)号：US20060053800A1
公开(公告)日：2006-03-16
申请号：US10941546
申请日：2004-09-15
IPC分类号： F02C7/12
CPC分类号： F02C7/18 , F02C5/00 , F05D2260/20 , F05D2260/96 , F23R3/005 , F23R3/04 , F23R7/00 , F23R2900/03044 , F23R2900/03281 , Y02T50/676
摘要： A gas turbine engine having a longitudinal centerline axis therethrough, including: a fan section at a forward end of the gas turbine engine including at least a first fan blade row connected to a first drive shaft; a booster compressor positioned downstream of and in at least partial flow communication with the fan section including a plurality of stages, each stage including a stationary compressor blade row and a rotating compressor blade row connected to a drive shaft and interdigitated with the stationary compressor blade row; a core system positioned downstream of the compressor, where the core system further includes an intermediate compressor positioned downstream of and in flow communication with the booster compressor, the intermediate compressor being connected to a second drive shaft, and a combustion system for producing pulses of gas having increased pressure and temperature from a fluid flow provided to an inlet thereof so as to produce a working fluid at an outlet; and, a low pressure turbine positioned downstream of and in flow communication with the core system, the low pressure turbine being utilized to power the first drive shaft. The core system may also include an intermediate turbine positioned downstream of the combustion system in flow communication with the working fluid, where the intermediate turbine is utilized to power the second drive shaft. A first source of compressed air having a predetermined pressure is provided to the combustion system inlet and a second source of compressed air having a pressure greater than the first source of compressed air is provided to cool the combustion system.
摘要翻译： 一种燃气涡轮发动机，其具有穿过其的纵向中心线轴线，包括：在所述燃气涡轮发动机的前端处的风扇部分，至少包括连接到第一驱动轴的第一风扇叶片排; 位于与包括多个级的风扇部分的下游并且至少部分流动连通的增压压缩机，每个级包括固定压缩机叶片排和连接到驱动轴的旋转压缩机叶片排，并与固定压缩机叶片排相互指向 ; 位于压缩机下游的核心系统，其中所述核心系统还包括位于所述增压压缩机下游并与所述增压压缩机流动连通的中间压缩机，所述中间压缩机连接到第二驱动轴，以及用于产生气体脉冲的燃烧系统 从提供给其入口的流体流增加压力和温度，以便在出口处产生工作流体; 以及低压涡轮机，其位于所述核心系统的下游并与所述核心系统流动连通，所述低压涡轮机用于为所述第一驱动轴提供动力。 核心系统还可以包括位于燃烧系统下游的中间涡轮机，其与工作流体流动连通，其中中间涡轮机用于为第二驱动轴提供动力。 具有预定压力的第一压缩空气源被提供给燃烧系统入口，并且提供具有大于第一压缩空气源的压力的第二压缩空气源以冷却燃烧系统。
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公开(公告)号：US20060053804A1
公开(公告)日：2006-03-16
申请号：US10941508
申请日：2004-09-15
CPC分类号： F02C5/00 , F05D2260/20 , Y02T50/676
摘要： A gas turbine engine having a longitudinal centerline axis therethrough, including: a fan section at a forward end of the gas turbine engine including at least a first fan blade row connected to a drive shaft; a booster compressor positioned downstream of the fan section including a plurality of stages, where each stage includes a stationary compressor blade row and a rotating compressor blade row connected to the drive shaft and interdigitated with the stationary compressor blade row; and, a combustion system for producing pulses of gas having increased pressure and temperature of a fluid flow provided to an inlet thereof so as to produce a working fluid at an outlet. A first source of compressed air from the booster compressor is provided to the combustion system inlet and a second source of compressed air from the booster compressor is provided to cool the combustion system, where the pressure of the compressed air from the second source has a greater pressure than that of the compressed air from the first source.
摘要翻译： 一种燃气涡轮发动机，其具有穿过其的纵向中心线轴线，包括：燃气涡轮发动机前端的风扇部分，至少包括连接到驱动轴的第一风扇叶片排; 位于风扇部分的下游的增压压缩机，包括多个级，其中每个级包括固定式压缩机叶片排和连接到驱动轴并与固定压缩机叶片排相互指向的旋转压缩机叶片排; 以及用于产生具有提高到其入口的流体流的压力和温度增加的气体脉冲以便在出口处产生工作流体的燃烧系统。 来自增压压缩机的第一压缩空气源被提供给燃烧系统入口，并且提供来自增压压缩机的第二压缩空气源以冷却燃烧系统，其中来自第二源的压缩空气的压力具有更大的压力 压力高于来自第一源的压缩空气的压力。
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公开(公告)号：US20060053801A1
公开(公告)日：2006-03-16
申请号：US10941547
申请日：2004-09-15
IPC分类号： F02C7/12
CPC分类号： F02K3/06 , F02C7/224 , F23D2214/00 , F23R3/28
摘要： A gas turbine engine having a longitudinal centerline axis therethrough, including: a fan section at a forward end of the gas turbine engine including at least a first fan blade row connected to a first drive shaft; a booster compressor positioned downstream of and in at least partial flow communication with the fan section including a plurality of stages, each stage including a stationary compressor blade row and a rotating compressor blade row connected to a drive shaft and interdigitated with the stationary compressor blade row; a core system positioned downstream of the booster compressor, the core system further comprising a combustion system for producing pulses of gas having increased pressure and temperature from a fluid flow provided to an inlet thereof so as to produce a working fluid at an outlet; a low pressure turbine positioned downstream of and in flow communication with the core system, the low pressure turbine being utilized to power the first drive shaft; and, a system for cooling the combustion system, wherein fuel is utilized as a cooling fluid prior to being supplied to the combustion system. The core system may further include an intermediate compressor positioned downstream of and in flow communication with the compressor connected to a second drive shaft; and an intermediate turbine positioned downstream of the combustion system in flow communication with the working fluid.
摘要翻译： 一种燃气涡轮发动机，其具有穿过其的纵向中心线轴线，包括：在所述燃气涡轮发动机的前端处的风扇部分，至少包括连接到第一驱动轴的第一风扇叶片排; 位于与包括多个级的风扇部分的下游并且至少部分流动连通的增压压缩机，每个级包括固定压缩机叶片排和连接到驱动轴的旋转压缩机叶片排，并与固定压缩机叶片排相互指向 ; 位于增压压缩机下游的核心系统，所述核心系统还包括燃烧系统，用于从提供给其入口的流体流产生具有增加的压力和温度的气体脉冲，以便在出口处产生工作流体; 位于所述核心系统下游并与所述核心系统流动连通的低压涡轮机，所述低压涡轮机用于为所述第一驱动轴提供动力; 以及用于冷却燃烧系统的系统，其中燃料在被供应到燃烧系统之前用作冷却流体。 核心系统可以进一步包括位于与连接到第二驱动轴的压缩机下游并与其连通的中间压缩机; 以及位于与工作流体流动连通的燃烧系统下游的中间涡轮机。
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公开(公告)号：US20060275111A1
公开(公告)日：2006-12-07
申请号：US11145837
申请日：2005-06-06
申请人： Robert Orlando , Thomas Moniz , Ching-Pang Lee , David Cherry , Robert Beacock , William Clifford , Scott Carson
发明人： Robert Orlando , Thomas Moniz , Ching-Pang Lee , David Cherry , Robert Beacock , William Clifford , Scott Carson
IPC分类号： F01D9/00
CPC分类号： F01D5/141 , F01D5/142 , F01D9/041 , F02C3/067 , F02K3/072 , F05D2220/323 , F05D2250/314 , Y02T50/671 , Y02T50/673
摘要： A turbine nozzle includes a row of vanes joined to radially outwardly inclined outer and inner bands. Each vane has camber and an acute twist angle for importing swirl in combustion gases discharged at trailing edges thereof. The trailing edges are tilted forwardly from the inner band to the outer band for increasing aerodynamic efficiency.
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公开(公告)号：US20060272314A1
公开(公告)日：2006-12-07
申请号：US11145875
申请日：2005-06-06
申请人： Thomas Moniz , Scott Carson , Robert Orlando , Ching-Pang Lee , David Cherry
发明人： Thomas Moniz , Scott Carson , Robert Orlando , Ching-Pang Lee , David Cherry
IPC分类号： F02K3/04
CPC分类号： F01D5/14 , F01D5/141 , F02C3/067 , F02K3/072 , Y02T50/671 , Y02T50/673
摘要： A turbofan engine includes a fan, compressor, combustor, single-stage high pressure turbine, and low pressure turbine joined in serial flow communication. First stage rotor blades in the low pressure turbine are oriented oppositely to the rotor blades in the high pressure turbine for counterrotation. First stage stator vanes in the low pressure turbine have camber and twist for carrying swirl directly between the rotor blades of the high and low pressure turbines.
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公开(公告)号：US20060288686A1
公开(公告)日：2006-12-28
申请号：US11145848
申请日：2005-06-06
申请人： David Cherry , Robert Beacock , William Clifford , Robert Orlando , Thomas Moniz , Ching-Pang Lee
发明人： David Cherry , Robert Beacock , William Clifford , Robert Orlando , Thomas Moniz , Ching-Pang Lee
CPC分类号： F02C3/067 , F01D5/142 , F01D9/02 , F01D9/041 , F01D9/065 , F02K3/072 , F05D2240/127 , Y02T50/671 , Y02T50/673
摘要： A turbofan engine includes a fan, compressor, combustor, high pressure turbine, and low pressure turbine joined in serial flow communication. The high pressure turbine includes two stages of rotor blades to effect corresponding exit swirl in the combustion gases discharged therefrom. A transition duct includes fairings extending between platforms for channeling the combustion gases to the low pressure turbine with corresponding swirl. First stage rotor blades in the low pressure turbine are oriented oppositely to the rotor blades in the high pressure turbine for counterrotation.
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公开(公告)号：US20070084190A1
公开(公告)日：2007-04-19
申请号：US11254018
申请日：2005-10-19
申请人： Thomas Moniz , Robert Orlando
发明人： Thomas Moniz , Robert Orlando
IPC分类号： F02K3/04
CPC分类号： F02K3/072 , F01D25/162 , F02C3/107 , F02C7/36 , F05D2230/642 , F05D2250/41 , F05D2260/40311 , F16D1/101 , F16D2001/103
摘要： A method for assembling a gas turbine engine including providing a core gas turbine engine at least partially defined by a frame and having a drive shaft rotatable about a longitudinal axis of the core gas turbine engine. A low-pressure turbine is coupled to a core turbine engine. A counter-rotating fan assembly is coupled to the low-pressure turbine. The counter-rotating fan assembly includes a first fan assembly and a second fan assembly. A booster compressor is coupled to the second fan assembly. A gearbox is securely coupled to the frame so that the gearbox is circumferentially positioned about the drive shaft. The first fan assembly is rotatably coupled to an input of the gearbox such that the first fan assembly rotates in a first direction. The second fan assembly is rotatably coupled to an output of the gearbox such that the second fan assembly rotates in a second direction opposite the first direction.
摘要翻译： 一种用于组装燃气涡轮发动机的方法，包括提供至少部分地由框架限定并具有可围绕核心燃气涡轮发动机的纵向轴线旋转的驱动轴的核心燃气涡轮发动机。 低压涡轮联接到核心涡轮发动机。 反向旋转的风扇组件联接到低压涡轮机。 反向风扇组件包括第一风扇组件和第二风扇组件。 升压压缩机联接到第二风扇组件。 齿轮箱牢固地联接到框架，使得齿轮箱围绕驱动轴周向定位。 第一风扇组件可旋转地联接到齿轮箱的输入端，使得第一风扇组件沿第一方向旋转。 第二风扇组件可旋转地联接到齿轮箱的输出，使得第二风扇组件沿与第一方向相反的第二方向旋转。
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公开(公告)号：US20050253706A1
公开(公告)日：2005-11-17
申请号：US10844224
申请日：2004-05-12
申请人： Michael Spoltore , Robert Orlando , Robert Adonailo , Scott Simon , Gordon Hope
发明人： Michael Spoltore , Robert Orlando , Robert Adonailo , Scott Simon , Gordon Hope
CPC分类号： G08B25/008 , G08B25/009 , G08B25/10 , G08B25/14 , H04M11/04
摘要： Security systems, such as in a home or other building, are interfaced with one another so that alarm messages and other information regarding a first security system are communicated to a second security system. In response, a user at the second system can send commands to the first system, such as for arming or disarming the first system. A user interface device at the second system includes an output component, such as a display screen, for displaying alarm messages from both the first and second systems. Other information, such as video and audio data from the first system, can also be provided at the second system. An input component, such as a keypad, allows the user to enter commands for controlling both the first and second systems. Communication between the security systems may be realized via an RF link, telephone link, and/or computer network.
摘要翻译： 诸如在家庭或其他建筑物中的安全系统彼此接口，使得关于第一安全系统的报警消息和其他信息被传送到第二安全系统。 作为响应，第二系统处的用户可以向第一系统发送命令，例如用于布防或撤防第一系统。 第二系统的用户接口设备包括用于显示来自第一和第二系统的警报消息的诸如显示屏的输出组件。 还可以在第二系统处提供诸如来自第一系统的视频和音频数据的其它信息。 诸如键盘的输入组件允许用户输入用于控制第一和第二系统的命令。 可以经由RF链路，电话链路和/或计算机网络来实现安全系统之间的通信。
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