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公开(公告)号：US06666018B2
公开(公告)日：2003-12-23
申请号：US10328679
申请日：2002-12-23
IPC分类号： F02K306
摘要： A pulse detonation system for a turbofan engine including a fan assembly and a turbine sub-system, which includes at least one turbine, is configured to create a temperature rise and a pressure rise within the turbofan engine and to generate thrust for the turbofan engine. The pulse detonation system includes a pulse detonation core assembly comprising at least one detonation chamber configured to detonate a fuel mixture. The pulse detonation core assembly is positioned between the fan assembly and the turbine sub-system.
摘要翻译： 包括风扇组件和包括至少一个涡轮机的涡轮机子系统的涡轮风扇发动机的脉冲爆震系统构造成在涡轮风扇发动机内产生温度升高和压力上升，并产生用于涡轮风扇发动机的推力。 脉冲爆震系统包括脉冲爆震核心组件，其包括至少一个被配置为引爆燃料混合物的爆震室。 脉冲爆震芯组件位于风扇组件和涡轮机子系统之间。
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2.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：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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公开(公告)号：US20060093466A1
公开(公告)日：2006-05-04
申请号：US10976496
申请日：2004-10-29
申请人： Jorge Seda , Thomas Moniz , Lawrence Butler
发明人： Jorge Seda , Thomas Moniz , Lawrence Butler
IPC分类号： F01D1/24
CPC分类号： F16C17/024 , F01D1/24 , F01D25/16 , F02C3/067 , F02K3/072 , F05D2240/53 , F16C17/18 , F16C2360/23
摘要： A method for assembling a gas turbine engine that includes providing a low-pressure turbine inner rotor configured to rotate in a first direction, providing a low-pressure turbine outer rotor configured to rotate in a second direction that is opposite the first rotational direction, and coupling at least one foil bearing to at least one of the inner and outer rotors to facilitate improving clearance control between a first rotating component and at least one of a second rotating component and a non-rotating component.
摘要翻译： 一种用于组装燃气涡轮发动机的方法，包括提供构造成沿第一方向旋转的低压涡轮机内转子，提供构造成沿与第一旋转方向相反的第二方向旋转的低压涡轮机外转子，以及 将至少一个箔片轴承耦合到内转子和外转子中的至少一个，以便于改进第一旋转部件与第二旋转部件和非旋转部件中的至少一个之间的间隙控制。
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公开(公告)号：US06928804B2
公开(公告)日：2005-08-16
申请号：US10383027
申请日：2003-03-06
CPC分类号： F02C3/165 , F02K3/06 , 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 an air inlet duct in flow communication with a source of compressed air, the air inlet duct including at least one port formed therein for permitting compressed air to flow therethrough, a fuel injector mounted to the air inlet duct in circumferentially spaced relation to each port, and a device mounted to the air inlet duct in circumferentially spaced relation to each fuel injector for initiating a detonation wave. A rotatable ring member is also positioned in coaxial relation around a portion of the air inlet duct, with the ring member including at least one stage of detonation disposed therein. Accordingly, a detonation wave is produced in each detonation stage and combustion gases following each detonation wave create a torque which causes the ring member to rotate. Each detonation stage in the ring member further includes a plurality of circumferentially spaced detonation ducts extending tangentially from an inner surface of the ring member, wherein the detonation ducts are aligned with each port, the fuel injector and the initiation device in a predetermined timing and sequence so that detonation waves are produced therein.
摘要翻译： 一种用于燃气涡轮发动机的脉冲爆炸系统，其具有延伸穿过其中的纵向中心线轴线，所述脉冲爆震系统包括与压缩空气源流动连通的空气入口管道，所述进气管道包括形成在其中的至少一个端口，用于允许压缩 空气流过其中，安装到空气入口管道的燃料喷射器与每个端口沿周向间隔开的关系;以及装置，其与每个燃料喷射器周向间隔开地安装到空气入口管道，用于启动爆震波。 旋转环构件也围绕空气入口管道的一部分以同轴的关系定位，环构件包括设置在其中的至少一个爆震级。 因此，在每个爆震阶段产生爆震波，并且在每个爆震波之后的燃烧气体产生使得环件旋转的扭矩。 环形构件中的每个爆震阶段还包括多个周向间隔开的从环形构件的内表面切向延伸的爆震导管，其中爆震导管以预定的时间和顺序与每个端口，燃料喷射器和启动装置对准 使其中产生爆震波。
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公开(公告)号：US06904750B2
公开(公告)日：2005-06-14
申请号：US10418859
申请日：2003-04-18
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 at least one stage of spaced detonation passages are disposed therethrough. 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 cylindrical manner in a substantially tangential direction with respect to the outer circumferential surface to create a torque which causes the cylindrical member to rotate. Each detonation passage includes a first portion extending from the cylindrical member forward surface to a middle portion of the cylindrical member and a second portion extending from the first portion to the outer circumferential 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的圆柱形构件，其中至少一级间隔的爆震通道设置穿过其中。 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，使得燃烧气体相对于外圆周表面沿大致切线的方向离开圆柱形，以产生使圆柱形构件旋转的扭矩。 每个爆震通道包括从圆柱形构件前表面延伸到圆柱形构件的中间部分的第一部分和从圆柱形构件的第一部分延伸到外圆周表面的第二部分。
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公开(公告)号：US06629674B1
公开(公告)日：2003-10-07
申请号：US10202533
申请日：2002-07-24
申请人： Seyed Gholamali Saddoughi , Ivett Alejandra Leyva , Anthony John Dean , Bernard Francois Robic , Lawrence Butler
发明人： Seyed Gholamali Saddoughi , Ivett Alejandra Leyva , Anthony John Dean , Bernard Francois Robic , Lawrence Butler
IPC分类号： B64C2104
CPC分类号： B64C27/46 , B64C11/16 , B64C21/04 , B64C2230/04 , B64C2230/16 , B64C2230/18 , B64C2230/28 , F01D5/145 , F02K7/005 , F02K7/02 , F04D29/681 , Y02T50/166 , Y02T50/673
摘要： An apparatus comprising: an airfoil adapted for generating a lift force; and a first pulse detonation actuator disposed inside the airfoil and adapted for impulsively detonating a fuel/air mixture to produce a pressure rise and velocity increase of combustion products therein, the airfoil having a plurality of lift control holes adapted for communicating combustion product flows from the first pulse detonation actuator to an airfoil surface to modulate the lift force.
摘要翻译： 一种装置，包括：适于产生升力的翼型件; 以及第一脉冲爆震致动器，其设置在所述翼型件的内部并且适于冲击地引爆燃料/空气混合物以产生其中的燃烧产物的压力升高和速度增加，所述翼型件具有多个提升控制孔，其适于将燃烧产物流从 第一脉冲爆震致动器到翼面以调节升力。
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公开(公告)号：US4936748A
公开(公告)日：1990-06-26
申请号：US276988
申请日：1988-11-28
申请人： Arthur P. Adamson , Lawrence Butler
发明人： Arthur P. Adamson , Lawrence Butler
CPC分类号： F02C7/36 , F02C6/206 , F02C9/56 , F02K3/072 , B64D2027/005 , F05D2220/325 , Y02T50/66 , Y02T50/671
摘要： A power takeoff for an unducted fan gas turbine engine having first and second counterrotating coaxial rotors coupled respectively to first and second propellers. The rotors and propellers are oriented for rotation about a longitudinal axis of the engine. A gear is coupled to each of the rotors for rotation therewith and arranged to provide rotational motion about an axis transverse to the engine axis. A shaft is coupled to the gear for rotation about the transverse axis. Each of the propellers includes a plurality of propeller blades, each of the blades is rotatable about a corresponding blade axis, and a control is coupled to the blades for varying the pitch thereof whereby power is selectively distributed between the propellers and the power takeoff. The power takeoff may include a propeller coupled to the shaft for developing thrust substantially transverse to the engine axis and/or a pump, compressor, or generator to supply fluids or electric power to other apparatus.
摘要翻译： 具有分别连接到第一和第二螺旋桨的第一和第二反转同轴转子的未被引导的风扇燃气涡轮发动机的动力输出。 转子和螺旋桨被定向成围绕发动机的纵向轴线旋转。 齿轮联接到每个转子以与其一起旋转并且被布置成围绕横向于发动机轴线的轴线提供旋转运动。 轴联接到齿轮以围绕横向轴线旋转。 每个螺旋桨包括多个螺旋桨叶片，每个叶片可围绕相应的叶片轴线旋转，并且控制器联接到叶片以改变其间距，由此功率选择性地分布在螺旋桨和动力输出之间。 功率输出可以包括联接到轴的推进器，用于显影基本上横向于发动机轴线的推力和/或泵，压缩机或发电机，以将流体或电力供应到其他装置。
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公开(公告)号：US4738591A
公开(公告)日：1988-04-19
申请号：US905207
申请日：1986-09-09
申请人： Lawrence Butler
发明人： Lawrence Butler
CPC分类号： F01D7/00 , B64C11/32 , B64D2027/005 , B64D2027/026 , F05D2260/74 , F05D2260/76 , Y02T50/66 , Y02T50/671
摘要： An apparatus for varying the pitch of propulsor blades of a gas turbine engine by eccentrically driven gears. The gas turbine engine includes a rotating structure, an annular gas flowpath coaxial with the rotating structure, a plurality of rotor blades coupled to the rotating structure and extending into the gas flowpath such that a gas stream flowing through the flowpath causes the rotating structure to rotate with respect to the stationary member and a plurality of variable pitch propulsor blades coupled to and disposed radially outwardly of the rotating structure. The pitch of the blade is varied by a pinion gear coaxially coupled to one of the propulsor blades and an internal gear radially disposed about the pinion gear for driving the pinion gear. Annular displacement of the pinion gear causes angular displacement of the propulsor blade with respect to the rotating structure. The internal gear is revolved about the pinion gear whereby the pinion gear is angularly displaced with respect to the rotating structure.
摘要翻译： 一种用于通过偏心驱动的齿轮改变燃气涡轮发动机的推进叶片的桨距的装置。 燃气涡轮发动机包括旋转结构，与旋转结构同轴的环形气体流动路径，多个转子叶片，其联接到旋转结构并延伸到气体流路中，使得流过流路的气流使得旋转结构旋转 相对于固定构件和多个可变间距推进器叶片，其连接到并设置在旋转结构的径向外侧。 叶片的节距由同轴联接到推进器叶片之一的小齿轮和围绕小齿轮径向设置的用于驱动小齿轮的内齿轮变化。 小齿轮的环形位移导致推进式叶片相对于旋转结构的角位移。 内齿轮围绕小齿轮转动，由此小齿轮相对于旋转结构有角度位移。
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10.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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