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公开(公告)号：US5010729A
公开(公告)日：1991-04-30
申请号：US292802
申请日：1989-01-03
CPC分类号： F02K3/072 , F02C3/067 , F02C3/107 , Y02T50/671
摘要： High by-pass fan jet engine includes counterrotating turbine blade sets for receiving hot combustion gases from a core engine portion and driving the fan blades through a planetary gear-type reduction gear assembly. Lightweight, highspeed, concentric, counterrotating shafts transmit power from both turbine blade sets to the fan via the reduction gear assembly. A pair of planetary gear assemblies with fixed fing gears and a rotatable common planetary gear carrier is used to drive a single set of fan blades via the carrier, and a pair of planetary gear assemblies with a fixed common planetary gear carrier and rotatable ring gears is used to drive two or more counterrotating fan blade sets via the ring gears. A low pressure "booster" compressor feeding the core engine portion can be directly driven from one of the two high speed shafts.
摘要翻译： 高级旁路风扇喷气发动机包括用于从核心发动机部分接收热燃气并且通过行星齿轮减速齿轮组件驱动风扇叶片的反转涡轮机叶片组。 轻便，高速，同心的反转轴通过减速齿轮组件将动力从涡轮叶片组传递到风扇。 一对具有固定指针齿轮和可转动共用行星齿轮架的行星齿轮组件用于通过载体驱动一组风扇叶片，一对具有固定公共行星齿轮架和可旋转环形齿轮的行星齿轮组件是 用于通过环形齿轮驱动两个或多个逆转风扇叶片组。 可以从两个高速轴之一直接驱动供给核心发动机部分的低压“增压”压缩机。
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2.发明授权Turbofan engine having a counterrotating partially geared fan drive turbine 失效涡轮风扇发动机具有逆转部分齿轮风扇驱动涡轮机
公开(公告)号：US4969325A
公开(公告)日：1990-11-13
申请号：US292841
申请日：1989-01-03
申请人： Arthur P. Adamson , Robert A. Wall
发明人： Arthur P. Adamson , Robert A. Wall
CPC分类号： F02C3/067 , F02C3/107 , Y02T50/671
摘要： A high bypass ratio turbofan engine having a fan section, a booster compressor disposed aft of the fan section relative to the flow of combustion gases through the engine, and a core section disposed aft of the booster compressor. A low pressure counterrotating turbine, disposed aft of the core section, is used for driving the fan section and the booster compressor. The counterrotating turbine includes at least one set of rotating turbine blades and at least one set of oppositely rotating counterrotating turbine blades. A twin spool shaft is provided for coupling the turbine blades to the booster compressor and for coupling the counterrotating turbine blades to the fan section. A reduction gear is disposed in the drive shaft for coupling the turbine blades to the fan section and for reducing the rotational speed of the turbine output power to match the rotational speed of the fan section thereby splitting the usable work of the turbine blades between the fan section and the booster.
摘要翻译： 具有风扇部分的高旁通比涡扇风扇发动机，相对于通过发动机的燃烧气体的流动而设置在风扇部分的后方的增压压缩机，以及设置在增压压缩机的后方的芯部。 用于驱动风扇部分和增压压缩机的低压逆转涡轮机设置在芯部的后方。 逆转涡轮机包括至少一组旋转涡轮机叶片和至少一组相反旋转的反转涡轮机叶片。 提供一个双卷轴，用于将涡轮机叶片耦合到增压压缩机，并将逆转涡轮机叶片耦合到风扇部分。 减速齿轮设置在驱动轴中，用于将涡轮机叶片耦合到风扇部分并且用于降低涡轮机输出功率的转速以匹配风扇部分的转速，从而将涡轮叶片的可用功分拆分在风扇之间 部分和助推器。
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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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4.发明授权
公开(公告)号：US4916894A
公开(公告)日：1990-04-17
申请号：US294091
申请日：1989-01-03
申请人： Arthur P. Adamson , Lawrence Butler
发明人： Arthur P. Adamson , Lawrence Butler
摘要： The present invention provides a high bypass turbofan engine configuration wherein a fan drive turbine is divided into first and second turbine sections mounted for independent rotation within the engine frame. The first, higher pressure, higher speed turbine section is coupled to the fan section drive shaft via a gear box which reduces the rotational speed of the power delivered by the higher pressure first turbine section to match the design rotational speed of the fan section. The second turbine section, having a larger diameter and lower rotational speed as compared to the first turbine section, is directly connected to the fan section and drives the fan section at the same rotational speed as that of the second turbine section. In this manner, the fan drive shaft horsepower is provided while reducing the weight and size of the necessary gearing between the fan drive turbine and the fan. The weight and size of the fan drive turbine and the booster compressor are also reduced.
摘要翻译： 本发明提供了一种高旁通涡扇风扇发动机配置，其中风扇驱动涡轮分为安装成在发动机机架内独立旋转的第一和第二涡轮部分。 第一，较高压力的较高速度的涡轮机部分经由齿轮箱联接到风扇部分驱动轴，齿轮箱降低由高压第一涡轮机部分输送的功率的转速以匹配风扇部分的设计转速。 与第一涡轮部分相比具有较大直径和较低转速的第二涡轮机部分直接连接到风扇部分，并以与第二涡轮部分相同的转速驱动风扇部分。 以这种方式，提供风扇驱动轴马力，同时减小风扇驱动涡轮机和风扇之间必要的传动装置的重量和尺寸。 风扇驱动涡轮机和增压压缩机的重量和尺寸也减小。
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公开(公告)号：US4132069A
公开(公告)日：1979-01-02
申请号：US753452
申请日：1976-12-22
IPC分类号： F02C7/04 , B64D27/18 , B64D29/00 , F02C7/20 , F02K3/00 , F02K3/04 , F02K3/06 , F02C3/06 , F02K1/20
CPC分类号： F02C7/20 , B64D27/18 , B64D29/00 , F04D29/526 , F04D29/685 , Y02T50/44 , Y02T50/672 , Y10T137/0536
摘要： A nacelle for use with a gas turbine engine is provided with an integral webbed structure resembling a spoked wheel for rigidly interconnecting the nacelle and engine. The nacelle is entirely supported in its spacial relationship with the engine by means of the webbed structure. The inner surface of the nacelle defines the outer limits of the engine motive fluid flow annulus while the outer surface of the nacelle defines a streamlined envelope for the engine.
摘要翻译： 与燃气涡轮发动机一起使用的机舱设置有类似于轮辐的整体网状结构，用于刚性地连接机舱和发动机。 机舱通过蹼状结构与发动机的空间关系完全支撑。 机舱的内表面限定了发动机运动流体流动环的外部限制，而机舱的外表面限定了发动机的流线型封套。
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公开(公告)号：US4913623A
公开(公告)日：1990-04-03
申请号：US196888
申请日：1988-05-20
IPC分类号： B64C11/34
CPC分类号： B64C11/346 , Y02T50/66
摘要： A pitch feathering system for a gas turbine driven aircraft propeller having multiple variable pitch blades utilizes a counter-weight linked to the blades. The weight is constrained to move, when effecting a pitch change, only in a radial plane and about an axis which rotates about the propeller axis. The system includes a linkage allowing the weight to move through a larger angle than the associated pitch change of the blade.
摘要翻译： 具有多个可变桨距叶片的具有多个变桨距叶片的燃气轮机驱动的飞机螺旋桨的俯仰羽化系统利用与叶片连接的配重。 当仅在径向平面中和围绕围绕螺旋桨轴线旋转的轴线时，重量被限制为在实现桨距变化时移动。 该系统包括一个联动装置，其允许重物移动比叶片的相关桨距变化更大的角度。
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公开(公告)号：US4047840A
公开(公告)日：1977-09-13
申请号：US581751
申请日：1975-05-29
CPC分类号： F04D29/323 , F01D5/3007 , F01D5/3053 , F01D7/00 , F02K3/06 , F05D2260/36 , F05D2260/4031 , F05D2260/74 , F05D2260/79
摘要： A variable pitch blade and blade mount which is suitable for propellers, fans and the like and which has improved impact resistance. The invention is particularly directed to composite fan blades and blade mounting arrangements wherein the blades are permitted to pivot relative to a turbine hub about an axis generally parallel to the centerline of the engine upon impact of a large foreign object, such as a bird. By thus providing for the pivoting of the blades upon impact, centrifugal force recovery becomes the principal energy absorbing mechanism and a blade having improved impact strength is obtained.
摘要翻译： 适用于螺旋桨，风扇等的变桨距叶片和叶片座，具有改善的抗冲击性。 本发明特别涉及复合风扇叶片和叶片安装装置，其中当大型异物（例如鸟）撞击时，叶片允许相对于涡轮机枢轴围绕大致平行于发动机的中心线的轴线枢转。 通过这样提供叶片在冲击时的枢转，离心力恢复成为主要的能量吸收机构，并获得具有改善的冲击强度的叶片。
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公开(公告)号：US5135185A
公开(公告)日：1992-08-04
申请号：US703720
申请日：1991-05-22
申请人： Arthur P. Adamson , Wu-Yang Tseng
发明人： Arthur P. Adamson , Wu-Yang Tseng
CPC分类号： B64D27/12
摘要： An aircraft engine is mounted on an aircraft wing such that the wing wake sheds along a zone at a predetermined position on the engine disk thereby minimizing dynamic loads or resonance. For a prechosen or design set of engine conditions the strength of the dynamic load is a function of the radial location of the zone on the disk having at least one relative minima between the centerline and the perimeter of the disk. The zone is positioned on the disk such that the value of the function is essentially a relative minima.
摘要翻译： 飞机发动机安装在飞行器机翼上，使得机翼沿着发动机盘上的预定位置的区域脱落，从而最小化动态载荷或共振。 对于发动机条件的预先设计或设计，动态载荷的强度是盘的区域的径向位置的函数，该区域在盘的中心线和周边之间具有至少一个相对最小值。 该区域位于盘上，使得该函数的值基本上是相对最小值。
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公开(公告)号：US4296599A
公开(公告)日：1981-10-27
申请号：US25300
申请日：1979-03-30
申请人： Arthur P. Adamson
发明人： Arthur P. Adamson
CPC分类号： F02C7/18 , F23R3/26 , F23R2900/00001
摘要： The cooling air flowpath for a turbomachine includes a plurality of valves placed in mutually parallel relationship to collectively provide for the modulation of the cooling airflow. Minimum flow requirements are assured while economizing on air to increase efficiency. Any single valve passes only a small portion of the total air so that a valve failure does not appreciably reduce the overall cooling function.
摘要翻译： 用于涡轮机的冷却空气流路包括以彼此平行的关系放置的多个阀，以共同地提供冷却气流的调制。 在节省空气以提高效率的同时确保最低流量要求。 任何单个阀只通过总空气的一小部分，使得阀故障不会明显降低总体冷却功能。
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公开(公告)号：US4222234A
公开(公告)日：1980-09-16
申请号：US818471
申请日：1977-07-25
申请人： Arthur P. Adamson
发明人： Arthur P. Adamson
CPC分类号： F02K3/065 , B64C29/0066 , F02K1/006 , F02K3/025 , Y02T50/671
摘要： A core engine with a single shaft driving both a forward and a rear fan, with the fans discharging into separate nozzles which are variable to direct exhaust gases in either the downward or rearward direction or in any direction therebetween. Separate flow modulating means are provided with the fans to selectively vary the respective thrusts produced. By selective modulation of the nozzles and the flow-varying means, both engine angle control and position control may be obtained in all three planes. A third variable position nozzle is provided to direct the discharge flow of the core turbine between the downward and rear directions to thereby augment the thrust and control functions.
摘要翻译： 具有驱动前风扇和后风扇的单个轴的核心发动机，其中风扇排放到单独的喷嘴中，所述喷嘴可以在向下或向后方向或其间的任何方向上引导废气。 单独的流量调节装置设置有风扇以选择性地改变所产生的各个推力。 通过选择性地调节喷嘴和流量变化装置，可以在所有三个平面中获得发动机角度控制和位置控制。 提供第三可变位置喷嘴以引导芯涡轮机在向下和向后方向之间的排放流，从而增加推力和控制功能。
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