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公开(公告)号：US06931858B2
公开(公告)日：2005-08-23
申请号：US10422314
申请日：2003-04-24
申请人： Kattalaicheri Srinivasan Venkataramani , Lawrence Butler , Ching-Pang Lee , Harvey Michael Maclin
发明人： Kattalaicheri Srinivasan Venkataramani , Lawrence Butler , Ching-Pang Lee , Harvey Michael Maclin
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：US06990797B2
公开(公告)日：2006-01-31
申请号：US10656518
申请日：2003-09-05
IPC分类号： F02C7/0472 , F02K3/04
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.发明授权Rotary pulse detonation system with aerodynamic detonation passages for use in a gas turbine engine 有权具有用于燃气涡轮发动机的空气动力学爆震通道的旋转脉冲爆震系统公开(公告)号：US07124573B2
公开(公告)日：2006-10-24
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：US07093446B2
公开(公告)日：2006-08-22
申请号：US10941508
申请日：2004-09-15
IPC分类号： F02C6/08
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.
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公开(公告)号：US20080229751A1
公开(公告)日：2008-09-25
申请号：US11657829
申请日：2007-01-25
IPC分类号： F02C7/08
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：US07096674B2
公开(公告)日：2006-08-29
申请号：US10941546
申请日：2004-09-15
申请人： Robert Joseph Orlando , Kattalaicheri Srinivasan Venkataramani , Ching-Pang Lee , Thomas Ory Moniz , Kurt David Murrow
发明人： Robert Joseph Orlando , Kattalaicheri Srinivasan Venkataramani , Ching-Pang Lee , Thomas Ory Moniz , Kurt David Murrow
IPC分类号： F02C6/08
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：US07739873B2
公开(公告)日：2010-06-22
申请号：US11256786
申请日：2005-10-24
申请人： Kattalaicheri Srinivasan Venkataramani , William Joseph Myers, Jr. , Robert Joseph Orlando , Paul Cooker , Ching-Pang Lee
发明人： Kattalaicheri Srinivasan Venkataramani , William Joseph Myers, Jr. , Robert Joseph Orlando , Paul Cooker , Ching-Pang Lee
IPC分类号： F02C9/00
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：US06981841B2
公开(公告)日：2006-01-03
申请号：US10718149
申请日：2003-11-20
IPC分类号： F03D11/00
CPC分类号： F01D25/12 , F01D5/082 , F01D5/084 , F01D5/085 , F02C7/18 , Y02T50/673 , Y02T50/676
摘要： A turbofan engine includes in serial flow communication a first fan, second fan, multistage compressor, combustor, first turbine, second turbine, and third turbine. The first turbine is joined to the compressor by a first shaft. The second turbine is joined to the second fan by a second shaft. And, the third turbine is joined to the first fan by a third shaft. First, second, and third cooling circuits are joined to different stages of the compressor for cooling the forward and aft sides and center bore of the first turbine with different pressure air.
摘要翻译： 涡轮风扇发动机包括串联流动连通的第一风扇，第二风扇，多级压缩机，燃烧器，第一涡轮机，第二涡轮机和第三涡轮机。 第一涡轮机通过第一轴连接到压缩机。 第二涡轮机通过第二轴连接到第二风扇。 并且，第三涡轮机通过第三轴接合到第一风扇。 第一，第二和第三冷却回路连接到压缩机的不同阶段，用不同的压力空气冷却第一涡轮机的前后侧和中心孔。
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公开(公告)号：US06832889B1
公开(公告)日：2004-12-21
申请号：US10616023
申请日：2003-07-09
IPC分类号： F03D1100
CPC分类号： F01D5/20 , F01D5/184 , F01D5/186 , Y02T50/673 , Y02T50/676
摘要： A turbine blade includes a hollow airfoil integrally joined to a dovetail. The airfoil includes a perforate first bridge defining a flow channel behind the airfoil leading edge. A second bridge is spaced behind the first bridge and extends from a pressure sidewall of the airfoil short of the airfoil trailing edge. A third bridge has opposite ends joined to the pressure sidewall and the second bridge to define with the first bridge a supply channel for the leading edge channel, and defines with the second bridge a louver channel extending aft along the second bridge to its distal end at the pressure sidewall.
摘要翻译： 涡轮机叶片包括与燕尾形整体连接的中空翼片。 翼型件包括限定在翼型件前缘后面的流动通道的穿孔第一桥。 第二桥隔开在第一桥后面并且从机翼后缘的翼型的压力侧壁延伸出来。 第三桥具有连接到压力侧壁和第二桥的相对端，第一桥与第一桥形成用于前缘通道的供应通道，并且与第二桥一起限定沿着第二桥向后延伸到其远端的百叶窗通道 压力侧壁。
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公开(公告)号：US07186091B2
公开(公告)日：2007-03-06
申请号：US10984292
申请日：2004-11-09
IPC分类号： F01D5/18
CPC分类号： F23R3/002 , F01D5/183 , F01D5/186 , F01D5/288 , F05D2230/90 , F05D2300/611 , F23R2900/03041
摘要： A method of cooling a gas turbine engine component having a perforate metal wall includes providing a plurality of pores in the wall, wherein the pores extend substantially perpendicularly through the wall, and wherein the pores are covered and sealed closed at first ends thereof by a thermal barrier coating disposed over a first surface of the wall, and providing a plurality of film cooling holes in the wall, wherein the holes extend substantially perpendicularly through the wall and the thermal barrier coating. The method also includes providing cooling fluid to the plurality of pores and the plurality of film cooling holes along a second surface of the wall, channeling the cooling fluid through the pores for back side cooling an inner surface of the thermal barrier coating, and channeling the cooling fluid through the holes for film cooling an outer surface of the thermal barrier coating.
摘要翻译： 一种冷却具有穿孔金属壁的燃气涡轮发动机部件的方法包括在壁中提供多个孔，其中孔基本上垂直延伸穿过壁，并且其中孔在其第一端被热封 屏障涂层，其设置在所述壁的第一表面上，并且在所述壁中提供多个膜冷却孔，其中所述孔基本上垂直延伸穿过所述壁和所述热障涂层。 该方法还包括沿着壁的第二表面向多个孔和多个膜冷却孔提供冷却流体，将冷却流体引导通过孔，用于背面冷却热障涂层的内表面，并且引导 冷却流体通过孔，用于薄膜冷却隔热涂层的外表面。
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