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公开(公告)号：US08061144B1
公开(公告)日：2011-11-22
申请号：US05886537
申请日：1978-03-02
摘要： In a by-pass gas turbine engine having a lobed type by-pass air and turbine exhaust mixer unit, the reheat gutters are arranged in the mixer in the turbine exhaust duct. The gutters extend radially and are substantially Y-shaped, each of the two legs of the Y extending radially along the sides of a mixer lobe.
摘要翻译： 在具有叶形旁通空气和涡轮排气混合器单元的旁通燃气涡轮发动机中，再热槽布置在涡轮机排气管道中的混合器中。 沟槽径向延伸并且大致为Y形，Y的两个腿中的每一个沿着混合器叶片的侧面径向延伸。
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公开(公告)号：US08061143B1
公开(公告)日：2011-11-22
申请号：US05886070
申请日：1978-03-02
摘要： A gas turbine reheat system is provided with channel-shaped gutters, with a wall portion spaced from each gutter to form a space therebetween. The space is supplied with cooling air conveniently from the engine by-pass duct.
摘要翻译： 燃气轮机再热系统设置有通道形槽，其中壁部分与每个沟槽间隔开，以在它们之间形成空间。 发动机旁路管道方便地供应冷却空气。
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公开(公告)号：US07823826B1
公开(公告)日：2010-11-02
申请号：US06325355
申请日：1981-11-04
申请人： William James Lewis
发明人： William James Lewis
CPC分类号： B64C21/04 , B64C29/005 , F02K9/80 , Y02T50/166
摘要： An aircraft having a gas turbine engine with vectorable cold and hot nozzles. The aircraft is provided with a ducting in the wing which extends from an inlet facing downwards to an outlet in the upper surface of the wing directed rearwardly. The cold vectorable nozzles of the engine are designed so that they can be swung from a vertical downward position to provide vertical lift to a horizontal position directed rearwardly to produce forward thrust, to a position where they are directed upwardly and discharged into the ducting 24. In this way, the air discharged through the outlet of the ducting 24 enhances the aerodynamic lift produced by the wing at slower speeds by inducing the air flow over the wing. In addition, the forward component of the thrust produced in the ducting provides a forward thrust on the aircraft, whilst additional forward thrust is produced by swiveling the hot nozzles.
摘要翻译： 具有具有可导向的冷热喷嘴的燃气涡轮发动机的飞机。 飞机在机翼中设有管道，该管道从面向下的入口延伸到向后指向的翼的上表面中的出口。 发动机的冷的可向导的喷嘴被设计成使得它们可以从垂直向下的位置摆动，以提供垂直提升到指向后方的水平位置以产生向前的推力，到达它们被向上引导并被排放到管道24中的位置。 以这种方式，通过管道24的出口排出的空气通过引导机翼上的空气流动来增强机翼以更慢的速度产生的空气动力学提升。 此外，在管道中产生的推力的前向分量在飞行器上提供向前的推力，而通过旋转热喷嘴产生额外的向前推力。
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公开(公告)号：US4826645A
公开(公告)日：1989-05-02
申请号：US741583
申请日：1985-06-05
申请人： James P. Angus
发明人： James P. Angus
CPC分类号： F01D5/282 , B29C45/0005 , B29C45/0013 , B29C45/14786 , F01D5/34 , F04D29/023 , F04D29/321 , B29L2031/08 , F05D2300/43 , F05D2300/603 , F05D2300/6032 , F05D2300/614
摘要： A method of manufacturing a bladed disc from a fiber reinforced composite material which comprises injecting a mixture of short fibers and a matrix material into a dividable die so configured as to define the form of a disc having integral radially extending aerofoil blades. The mixture is injected into the die at such a location that the short fibers within the aerofoil-defining portions of the die are radially aligned. The die contains two support rings which are coaxially disposed within the bladed disc after injection molding so as to provide radial support for the aerofoil blades of the thus formed bladed disc. The method may be modified to provide the bladed disc with an integral shroud.
摘要翻译： 一种从纤维增强复合材料制造叶片的方法，其包括将短纤维和基质材料的混合物注入到可分割模具中，所述模具被构造成限定具有整体径向延伸的翼型叶片的盘的形式。 将混合物注入到模具中，使得模具的机翼限定部分内的短纤维径向对齐。 模具包含两个支撑环，其在注射成型之后同轴地设置在叶片盘内，以便为由此形成的叶片盘的翼型叶片提供径向支撑。 该方法可以被修改以提供具有整体护罩的叶片盘。
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5.发明授权
公开(公告)号：US4638946A
公开(公告)日：1987-01-27
申请号：US78053
申请日：1979-09-24
申请人： John M. Hall
发明人： John M. Hall
CPC分类号： F02K1/006 , B64D33/04 , F02K1/1261 , F02K1/60 , Y02T50/671
摘要： A gas turbine jet propulsion engine has a rectangular exhaust gas outlet 14. A pair of U-shaped tracks 21,22 one on each side of the outlet and which extend downstream of it, support rollers carrying the plates 24a etc. of a pair of articulated deflectors 24,26, one above and one below the outlet. The deflectors are translatable along the tracks between the final exhaust discharge opening of the engine. The configurations include a convergent divergent nozzle, a thrust vectoring nozzle and thrust reversing outlets.
摘要翻译： 燃气轮机喷气推进发动机具有矩形排气出口14.一对U形轨道21,22，一个在出口的每一侧，并在其下游延伸，支撑承载一对 铰接偏转器24,26，一个在出口之上和一个下方。 导流器可沿着发动机的最终排气口之间的轨道平移。 这些配置包括收敛发散喷嘴，推力矢量喷嘴和推力反向出口。
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公开(公告)号：US4637449A
公开(公告)日：1987-01-20
申请号：US737280
申请日：1985-05-22
申请人： David Mills , Anthony T. Lindahl , Alan D. Kington
发明人： David Mills , Anthony T. Lindahl , Alan D. Kington
IPC分类号： B22C9/10
CPC分类号： B22C9/106
摘要： A reinforced tubular core for casting gas turbine engine blades with cooling air passages therein is disclosed. A method of casting is also disclosed in which the blades are directionally solidified to produce columnar grained or single crystal blades and in which non-linear passages can be produced. The problem in producing such articles is that the moulds and cores used in the casting process are held at temperatures in excess of 1500.degree. for long periods and presently used Silica cores deform during the process. Stronger cores of Alumina or Silicon Nitride cannot be easily bent were believed to be non-leachable from the casting. The present invention provides a core having a tubular silica sheath with a solid alumina rod inside it for support. The sheath can be bent and the straight alumina rods can be inserted from opposite ends of the sheath.
摘要翻译： 公开了一种用于铸造具有冷却空气通道的燃气涡轮发动机叶片的加强管状芯。 还公开了一种铸造方法，其中叶片被定向凝固以产生柱状晶粒或单晶叶片，并且其中可以产生非直线通道。 制造这种制品的问题在于，铸造过程中使用的模具和芯体长时间保持在1500度以上的温度，并且在使用过程中目前使用的硅胶芯变形。 氧化铝或氮化硅的较强核心不容易弯曲，据信是不能从铸件中浸出的。 本发明提供一种具有管状二氧化硅护套的芯，其内部具有用于支撑的固体氧化铝棒。 护套可以弯曲，并且直的氧化铝棒可以从护套的相对端插入。
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公开(公告)号：US4623087A
公开(公告)日：1986-11-18
申请号：US614244
申请日：1984-05-25
申请人： Ralph I. Conolly
发明人： Ralph I. Conolly
CPC分类号： B05D1/28 , B23K20/22 , C23C24/08 , Y10T29/49341 , Y10T29/49805 , Y10T29/4981 , Y10T29/49982
摘要： It is known to apply coatings which have desired characteristics, e.g., wear resistance, thermal barrier capabilities anti-oxidation, to articles the material of which does not have the desired characteristic, wherein the coating is applied directly to the article. Some article materials, e.g. titanium are highly reactive which immediately obviates several known methods of applying coatings. The invention uses a member (12) which would normally be preformed to mate with the article surface to be coated. The member (12) is manufactured from cheap, non-reactive material, as a base to which the coating (14) is applied by the most suitable of any of the known means. The member (12) is then placed against the article with the coating (14) therebetween and the whole hot isostatically pressed. The member (12) is afterwards removed, e.g. by machining or etching.
摘要翻译： 已知施加具有所需特性（例如耐磨性，抗热氧化能力抗氧化）的涂层到其材料不具有所需特性的制品，其中涂层直接施加到制品上。 一些物品，例如 钛是高反应性的，其立即消除了几种已知的施加涂层的方法。 本发明使用通常预成型的构件（12）与要涂覆的制品表面配合。 构件（12）由便宜的非反应性材料制成，作为通过最适合的任何已知方法施加涂层（14）的基底。 然后将构件（12）放置在其间具有涂层（14）的物品上，并且全部热等静压。 该构件（12）之后被移除，例如 通过机械加工或蚀刻。
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公开(公告)号：US4606191A
公开(公告)日：1986-08-19
申请号：US755434
申请日：1985-07-16
CPC分类号： F02C9/36 , F02C9/28 , F05D2270/101
摘要： A fuel control unit forms part of a control system of a gas turbine aeroengine. The control unit is in communication with a main fuel line leading to the aeroengine and comprises a fuel accumulator, i.e. volume varied by free piston, which is controllable by the control system to take fuel from the fuel line to reduce temporarily but substantially the mass flow of fuel to the aeroengine. This is helpful in combating surge conditions in the aeroengine caused by temporary overfueling of the aeroengine by the fuel control system.
摘要翻译： 燃料控制单元构成燃气轮机航空发动机的控制系统的一部分。 控制单元与通向航空发动机的主燃料管线连通，并且包括燃料蓄积器，即，由自由活塞变化的容积，其由控制系统控制以从燃料管线中获取燃料以暂时减少但基本上质量流量 的燃料到航空发动机。 这有助于消除燃料控制系统由航空发动机暂时过度燃油引起的航空发动机的喘振条件。
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公开(公告)号：US4603546A
公开(公告)日：1986-08-05
申请号：US755433
申请日：1985-07-16
申请人： Brian J. Collins
发明人： Brian J. Collins
CPC分类号： F02C9/52 , F04D27/0207
摘要： Surge conditions in the compressor of a gas turbine aeroengine can be automatically controlled by a surge control system in which compressor outlet pressure is monitored and a signal P corresponding to it is processed in a surge detector to determine the ratio P/P and to compare the value of the ratio with a predetermined reference value, surge correction control signals being outputted whenever a surge is detected. Surge is controlled as these signals actuate various units linked with the surge detector, these units achieving bleeding off of air from the compressor, reduction of the mass flow of fuel to the aeroengine, and maintenance of fuel ignition for a predetermined period.
摘要翻译： 燃气轮机航空发动机的压缩机的浪涌状况可以由其中监测压缩机出口压力的浪涌控制系统自动控制，并且在浪涌检测器中处理与其对应的信号P以确定比率P / P，并将 具有预定参考值的比率值，每当检测到浪涌时，浪涌校正控制信号被输出。 控制浪涌，因为这些信号致动与浪涌检测器连接的各种单元，这些单元实现了从压缩机排出的空气，减少了燃料到航空发动机的质量流量，并在一段预定的时间段内维持燃油点火。
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公开(公告)号：US4598542A
公开(公告)日：1986-07-08
申请号：US681258
申请日：1984-12-13
申请人： Graham A. Reynolds
发明人： Graham A. Reynolds
摘要： A gas turbine engine is of a size suitable for generating electrical and heat energy for domestic and other purposes. The engine has a low number of components, and some of the components are capable of performing more than one function. For example, the engine has a centrifugal compressor driven by a centripetal turbine through a shaft. The compressor and turbine are mounted in a casing comprising a two part core and two end plates. The gas flow ducting is formed by surfaces on the compressor and turbine rotors, the core and the two end plates.
摘要翻译： 燃气涡轮发动机的尺寸适合于为家庭和其他目的产生电能和热能。 发动机具有低数量的部件，并且一些部件能够执行多个功能。 例如，发动机具有通过轴由向心涡轮机驱动的离心式压缩机。 压缩机和涡轮机安装在包括两部分芯和两个端板的壳体中。 气体流动管道由压缩机和涡轮转子，铁芯和两个端板上的表面形成。
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