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公开(公告)号：US20050028531A1
公开(公告)日：2005-02-10
申请号：US10422314
申请日：2003-04-24
摘要： A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough includes a rotatable cylindrical member having a forward surface, an aft surface, and an outer circumferential surface, where a plurality of spaced detonation passages are disposed therethrough. Each detonation passage includes at least a portion having a longitudinal axis extending therethrough oriented at a circumferential angle to the longitudinal centerline axis. The pulse detonation system further includes a shaft rotatably connected to the cylindrical member and a stator configured in spaced arrangement with the forward surface of the cylindrical member and a portion of the shaft. The stator has at least one group of ports formed therein alignable with the detonation passages as the cylindrical member rotates. In this way, detonation cycles are performed in the detonation passages so that combustion gases exit the aft surface of the cylindrical member to create a torque which causes the cylindrical member to rotate. Each detonation passage further includes a first end located adjacent the forward surface of the cylindrical member and a second end located adjacent the aft surface of the cylindrical member.
摘要翻译： 用于具有延伸穿过其中的纵向中心线轴的燃气涡轮发动机的脉冲爆震系统包括具有前表面，后表面和外周表面的可旋转圆柱形构件，其中多个间隔开的爆震通道穿过其中。 每个爆震通道包括至少一个具有延伸穿过的纵向轴线的部分，该纵向轴线以与纵向中心线轴线成圆周方向定位。 脉冲爆震系统还包括可旋转地连接到圆柱形构件的轴和定子，其与圆柱形构件的前表面和轴的一部分间隔开地配置。 定子具有至少一组端口，当圆柱形构件旋转时，该组端口可与引爆通道对准。 以这种方式，在引爆通道中进行爆震循环，使得燃烧气体离开圆柱形构件的后表面以产生使圆柱形构件旋转的扭矩。 每个引爆通道还包括位于圆柱形构件的前表面附近的第一端和位于圆柱形构件的后表面附近的第二端。
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公开(公告)号：US20050050877A1
公开(公告)日：2005-03-10
申请号：US10656518
申请日：2003-09-05
IPC分类号： F02C7/047
CPC分类号： F02C7/047 , F05D2260/208 , Y02T50/672 , Y02T50/675
摘要： A method facilitates assembling a turbine engine to facilitate preventing ice accumulation on the turbine engine during engine operation. The method comprises coupling at least one heat pipe to the engine such that a first end of the at least one heat pipe is coupled in thermal communication with a heat source, and coupling a second end of the at least one heat pipe in thermal communication with an outer surface of an engine component that is upstream from the heat source.
摘要翻译： 一种方法有利于组装涡轮发动机以便于在发动机运转期间防止在涡轮发动机上的积冰。 该方法包括将至少一个热管耦合到发动机，使得至少一个热管的第一端与热源热连通地联接，并将至少一个热管的第二端与热源连通 发动机部件的外表面，其位于热源的上游。
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3.发明申请ROTARY PULSE DETONATION SYSTEM WITH AERODYNAMIC DETONATION PASSAGES FOR USE IN A GAS TURBINE ENGINE 有权用于气体涡轮发动机的具有气动爆震通道的旋转脉冲爆震系统公开(公告)号：US20060207261A1
公开(公告)日：2006-09-21
申请号：US10803293
申请日：2004-03-18
CPC分类号： F02K7/02 , Y02T50/671
摘要： A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough. The pulse detonation system includes a rotatable cylindrical member having a forward surface, an aft surface, and an outer circumferential surface, where at least one stage of circumferentially spaced detonation passages are disposed therethrough. Each detonation passage further includes: a leading portion positioned adjacent the forward surface of the cylindrical member, with the leading portion having a centerline therethrough oriented at a designated angle to an axis extending substantially parallel to the longitudinal centerline axis within a specified plane; a trailing portion positioned adjacent the aft surface of the cylindrical member, with the trailing portion having a centerline therethrough oriented at a designated angle to the axis within the specified plane; and, a middle portion connecting the leading and trailing portions, with the middle portion having a centerline therethrough with a substantially constantly changing slope in the specified plane. A shaft is rotatably connected to the cylindrical member and a stator is configured in spaced arrangement with the forward surface of the cylindrical member and a portion of the shaft. The stator further includes at least one group of ports formed therein alignable with the leading portions of the detonation passages as the cylindrical member rotates. In this way, detonation cycles are performed in the detonation passages so that combustion gases interact therewith to create a torque which causes the cylindrical member to rotate.
摘要翻译： 一种用于燃气涡轮发动机的脉冲爆震系统，其具有延伸穿过其中的纵向中心线轴线。 脉冲爆震系统包括具有前表面，后表面和外圆周表面的可旋转圆柱形构件，其中周向间隔开的爆炸通道的至少一级设置穿过其中。 每个引爆通道还包括：与圆柱形构件的前表面相邻定位的引导部分，前导部分具有穿过中心线的中心线，该中心线以与指定平面内的纵向中心线轴线基本平行延伸的轴指定角度定位; 后部部分邻近圆柱形构件的后表面定位，后部具有穿过其中心线的中心线，该中心线以指定平面内的轴线指定角度; 以及连接前后部分的中间部分，其中间部分具有穿过其中心线的特定平面内基本上恒定变化的倾斜度。 轴可旋转地连接到圆柱形构件，并且定子被构造成与圆柱形构件的前表面和轴的一部分隔开布置。 定子还包括至少一组在圆柱形构件旋转时可与引爆通道的引导部分对准的端口。 以这种方式，在引爆通道中执行爆震循环，使得燃烧气体与其起作用以产生使圆柱形构件旋转的扭矩。
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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：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：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：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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9.发明申请公开(公告)号：US20060042228A1
公开(公告)日：2006-03-02
申请号：US10932169
申请日：2004-09-01
CPC分类号： F02K7/005 , Y02T50/671
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 the fan section, the booster compressor including a first compressor blade row and a second compressor blade row connected to a second drive shaft and interdigitated with the first compressor blade row; and, a pulse detonation system for powering the first and second drive shafts. The pulse detonation system powers only the second drive shaft during a first designated condition of the gas turbine engine and both the first drive shaft and the second drive shaft during a second designated condition of the gas turbine engine. The first and second drive shafts are powered independently of each other by the pulse detonation 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; 位于所述风扇部分下游的增压压缩机，所述增压压缩机包括连接到第二驱动轴并与所述第一压缩机叶片排交叉的第一压缩机叶片排和第二压缩机叶片排; 以及用于为第一和第二驱动轴供电的脉冲爆震系统。 在燃气涡轮发动机的第一指定状态期间，在燃气涡轮发动机的第二指定状态期间，脉冲爆震系统仅为第二驱动轴供电，而在第一驱动轴和第二驱动轴两者之间。 第一和第二驱动轴通过脉冲爆震系统彼此独立地供电。
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10.发明申请公开(公告)号：US20060216476A1
公开(公告)日：2006-09-28
申请号：US11091800
申请日：2005-03-28
申请人： Suryaprakash Ganti , Tao Deng , Veera Rajendran , Anthony Ku , Judith Stein , Gregory O'Neil , Azar Alizadeh , Margaret Blohm , Kattalaicheri Venkataramani
发明人： Suryaprakash Ganti , Tao Deng , Veera Rajendran , Anthony Ku , Judith Stein , Gregory O'Neil , Azar Alizadeh , Margaret Blohm , Kattalaicheri Venkataramani
IPC分类号： E01F9/04
CPC分类号： C23C18/02 , C23C18/122 , C23C18/1233 , C23C18/1279 , E01F9/40 , Y10T428/24355 , Y10T428/24372
摘要： An article comprises a textured surface disposed on a substrate. The surface has an effective liquid wettability sufficient to generate, with a reference liquid, a contact angle in a range from about 120° to about 180°. The surface comprises a material having a nominal liquid wettability sufficient to generate, with the reference liquid, a nominal contact angle in a range from about 60° to about 90°, the material comprising at least one material selected from the group consisting of a polymer and a ceramic. The properties of the surface may include low-drag or low-friction, self-cleaning capability, and resistance to icing, fouling, and fogging, and the like. Methods of making such a surface are also described.
摘要翻译： 一种制品包括设置在基底上的纹理表面。 该表面具有足够的有效的液体润湿性，可以用参考液体产生约120°至约180°范围内的接触角。 表面包括具有足以产生参考液体在约60°至约90°范围内的标称接触角的标称液体润湿性的材料，该材料包含选自聚合物 和陶瓷。 表面的性质可以包括低阻力或低摩擦，自清洁能力，耐结冰，结垢和起雾等。 还描述了制造这种表面的方法。
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