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91. 发明授权

US5727378A Gas turbine engine 失效
标题翻译：燃气轮机
公开(公告)号：US5727378A
公开(公告)日：1998-03-17
申请号：US519672
申请日：1995-08-25
申请人： Jeffrey L. Seymour
发明人： Jeffrey L. Seymour
IPC分类号： F01D25/12 , F02C3/09 , F23R3/06 , F23R3/28 , F23R3/32 , F23R3/54 , F02C3/06 , F02C7/08
CPC分类号： F23R3/32 , F01D25/125 , F02C3/09 , F23R3/06 , F23R3/286 , F23R3/54 , F05D2220/329 , Y02T50/675
摘要： This invention pertains to small air breathing gas turbine engines (1). Engines of the invention employ improved combustion systems, including improved fuel injection systems and improved combustor design. These improvements enable the engine to idle at speeds as low as one-tenth the maximum operating speed of the engine, which gives the engine an increased range of operating speeds. The improved designs generally provide for pre-mix assemblies intimate with the fuel injectors, a typically flame-free primary "A" mixing zone in the combustion chamber, and a primary "B" combustion zone, in addition to the secondary combustion zone and the dilution zone. In preferred embodiments, the bearing assembly is located between the compressor and the turbine wheel. A cooling cavity is provided between the turbine wheel and the bearing assembly, thus protecting the bearings from the turbine heat. A toroidally-shaped compressor discharge plenum between the compressor and the turbine wheel serves as an air accumulator, an air shock absorber, and an air stabilizer. Resiliently deflectable leaf spacers position the dome of the combustor from the rear casing wall.
摘要翻译：本发明涉及小型空气呼吸燃气涡轮发动机（1）。本发明的发动机采用改进的燃烧系统，包括改进的燃料喷射系统和改进的燃烧室设计。这些改进使得发动机以低至发动机的最大运行速度的十分之一的速度怠速，这给发动机提供了更高的操作速度范围。改进的设计通常提供与燃料喷射器紧密的预混合组件，燃料喷射器是除了二次燃烧区域之外的燃烧室中的典型的无焰初级“A”混合区域和初级“B”燃烧区域稀释区。在优选实施例中，轴承组件位于压缩机和涡轮机叶轮之间。在涡轮机叶轮和轴承组件之间提供冷却腔，从而保护轴承不受涡轮机热量的影响。在压缩机和涡轮机叶轮之间的环形压缩机排放气室用作空气蓄能器，空气缓冲器和空气稳定器。弹性可偏转的叶片间隔件从后壳体定位燃烧器的圆顶。

92. 发明授权

US5562404A Vaned passage hub treatment for cantilever stator vanes 失效
标题翻译：用于悬臂定子叶片的通风轮毂处理
公开(公告)号：US5562404A
公开(公告)日：1996-10-08
申请号：US372795
申请日：1994-12-23
申请人： Steven G. Koff , Bernard L. Koff , Bruce V. Lyon , Mark G. Duer
发明人： Steven G. Koff , Bernard L. Koff , Bruce V. Lyon , Mark G. Duer
IPC分类号： F01D5/06 , F01D5/14 , F01D11/00 , F01D11/02 , F01D11/08 , F01D11/10 , F02C3/06 , F02C7/18 , F04D27/02 , F04D29/54
CPC分类号： F01D11/10 , F01D11/001 , F01D11/08 , F01D5/145 , F04D29/321 , F04D29/685 , Y02T50/671 , Y02T50/673 , Y10S415/914 , Y10T29/49316 , Y10T29/4932
摘要： The cantilevered stator vanes of the compressor section of the gas turbine engine are treated by including a rotating hub having a by-pass passage for removing the low momentum fluid from the main air stream adjacent to the tips of the stator vanes in the compressor and returning it back into the main air stream after having treated the air while avoiding penalties and excessive heating. A plurality of vanes are circumferentially spaced in the by-pass passage for removing vortices and streamlining the flow before injected the air back into the airstream. The vane passage hub treatment is fabricated in a single cast piece in one embodiment, in a three ring configuration in another embodiment and in a segmented ring configuration in still another embodiment.
摘要翻译：燃气涡轮发动机的压缩机部分的悬臂式定子叶片通过包括具有旁通通道的旋转轮毂来处理，该旁路通道用于从邻近压缩机中的定子叶片的顶端的主空气流中除去低动量流体并返回经过处理空气后又回到主要空气流中，同时避免了处罚和过度加热。多个叶片在旁路通道中周向间隔开，以便在将空气注入空气流之前去除涡流并使流动简化。在一个实施例中，叶片通道毂处理在单个铸件中制造，在另一个实施例中为三环结构，在另一个实施例中为分段环形结构。

93. 发明授权

US5402963A Acoustically shielded exhaust system for high thrust jet engines 失效
标题翻译：用于高推力喷气发动机的隔音排气系统
公开(公告)号：US5402963A
公开(公告)日：1995-04-04
申请号：US138569
申请日：1993-10-18
申请人： John P. Carey , Robert Lee , Rudramuni K. Majjigi
发明人： John P. Carey , Robert Lee , Rudramuni K. Majjigi
IPC分类号： F02C3/06 , F02K1/34 , F02K1/46 , B64D33/04
CPC分类号： F02K1/34 , F02C3/064 , F02K1/46 , Y02T50/671
摘要： A flade exhaust nozzle for a high thrust jet engine is configured to form an acoustic shield around the core engine exhaust flowstream while supplementing engine thrust during all flight conditions, particularly during takeoff. The flade airflow is converted from an annular 360.degree. flowstream to an arcuate flowstream extending around the lower half of the core engine exhaust flowstream so as to suppress exhaust noise directed at the surrounding community.
摘要翻译：用于高推力喷气发动机的溢流排气喷嘴构造成在所有飞行条件下，特别是在起飞期间补充发动机推力，在核心发动机排气流动流周围形成声屏蔽。苍蝇气流从环形360°流动流转换到围绕核心发动机排气流动流的下半部分延伸的弓形流动流，以便抑制针对周围社区的排气噪声。

94. 发明授权

US5351474A Combustor external air staging device 失效
标题翻译：燃烧器外部空气分级装置
公开(公告)号：US5351474A
公开(公告)日：1994-10-04
申请号：US75360
申请日：1993-04-16
申请人： Gale V. Slocum , Albert Myers , Kenneth W. Beebe
发明人： Gale V. Slocum , Albert Myers , Kenneth W. Beebe
IPC分类号： F02C3/06 , F02C3/26 , F02C9/18 , F23R3/26 , F02C9/00
CPC分类号： F23R3/26
摘要： A gas turbine combustion system includes a plurality of combustors within a pressure vessel, each combustor including a combustion liner defining a combustion chamber having a reaction zone and a dilution zone, the liner in the dilution zone provided with a plurality of circumferentially spaced dilution air feed holes. A flow shield surrounds each combustion liner in radially spaced relation thereto for feeding compressor discharge air to the combustion chamber. Air staging apparatus directly controls the amount of compressor discharge air fed into each combustion chamber dilution zone via the dilution air feed holes. The apparatus includes a plurality of pressure vessel extraction ports and associated conduits for introducing compressor discharge air into a first manifold common to the plurality of combustors; a dilution air control valve located between each extraction port and the first manifold; and a second, annular manifold surrounding the flow shield and including feed tubes connecting the second manifold to each of the dilution air feed holes in the combustion liner.
摘要翻译：燃气轮机燃烧系统包括在压力容器内的多个燃烧器，每个燃烧器包括限定具有反应区和稀释区的燃烧室的燃烧衬套，所述稀释区中的衬里设置有多个周向间隔开的稀释空气进料孔。流动屏蔽围绕每个燃烧衬套以与其径向间隔的关系围绕，用于将压缩机排放空气供给到燃烧室。空气分级设备直接控制通过稀释空气供给孔供给到每个燃烧室稀释区域的压缩机排放空气的量。该装置包括多个压力容器抽出口和相关导管，用于将压缩机排出空气引入到多个燃烧器共同的第一歧管中; 位于每个抽出口和第一歧管之间的稀释空气控制阀; 以及围绕所述流动屏蔽件的第二环形歧管，并且包括将所述第二歧管连接到所述燃烧衬套中的每个所述稀释空气供给孔的进料管。

95. 发明授权

US4706452A Engine 失效
标题翻译：发动机
公开(公告)号：US4706452A
公开(公告)日：1987-11-17
申请号：US911325
申请日：1986-09-25
申请人： Gaston Lavoie
发明人： Gaston Lavoie
IPC分类号： F02C3/05 , F02C3/045 , F02C3/14 , F02C3/16 , F02C7/04 , F23R3/42 , F23R3/52 , F02C3/06
CPC分类号： F23R3/52 , F02C3/045 , F02C3/165
摘要： The present invention provides an internal combustion engine comprising a main body portion defining a combustion chamber in the form of a toroidal cavity with a generally circular axis, an air intake, compressor means for drawing air from said intake and delivering it to said toroidal cavity under pressure in a generally tangential direction to impart a swirl motion to gases in said cavity about said circular axis, means for exhausting combustion gases from said cavity, drive means disposed adjacent said exhaust means so as to be acted on by said combustion gases to perform mechanical work and thereby provide an output of the engine, and means coupling said drive means to said compressor means for providing power thereto.
摘要翻译：本发明提供一种内燃机，其包括主体部分，其限定具有大致圆形轴线的环形腔形式的燃烧室，进气口，用于从所述进气口抽取空气并将其输送到所述环形空腔下面的压缩机装置在大致切线方向上的压力以围绕所述圆形轴线对所述空腔中的气体施加漩涡运动，用于从所述空腔排出燃烧气体的装置，与所述排气装置相邻设置的驱动装置，以便被所述燃烧气体作用以执行机械从而提供发动机的输出，以及将所述驱动装置联接到所述压缩机装置以便向其提供动力的装置。

96. 发明授权

US4640092A Combustion chamber rear outer seal 失效
标题翻译：燃烧室后外密封
公开(公告)号：US4640092A
公开(公告)日：1987-02-03
申请号：US835136
申请日：1986-03-03
申请人： Robert E. Coburn , John A. Matthews
发明人： Robert E. Coburn , John A. Matthews
IPC分类号： F02C7/28 , F01D9/02 , F02C3/06 , F02C1/00 , F02C7/20
CPC分类号： F01D9/023 , Y02T50/675
摘要： A sealing device which is adapted to cooperate with and be secured to the outwardly extending tabs on the inlet vanes for the turbine in which the tabs provide a forwardly facing surface and the sealing device has a rearwardly facing surface in contact with one another and with the parts secured together by a row of bolts in which the sealing element has a flange along the outer edge of the element between certain bolts to reinforce the plate and between other bolts the sealing element is reinforced by plates extending between adjacent bolts and secured to the forward side of the sealing element by said bolts.
摘要翻译：一种密封装置，其适于与用于涡轮机的入口叶片上的向外延伸的突出部配合并固定，其中突片提供向前的表面，并且密封装置具有彼此接触的向后的表面，并且与通过一排螺栓固定在一起的部件，其中密封元件沿着元件的外边缘在某些螺栓之间具有凸缘以加强板和在其它螺栓之间，密封元件由在相邻螺栓之间延伸并固定到前部的板被增强密封元件的侧面。

97. 发明授权

US4344282A Compressor bleed system 失效
标题翻译：压缩机排气系统
公开(公告)号：US4344282A
公开(公告)日：1982-08-17
申请号：US217071
申请日：1980-12-16
申请人： Larry E. Anders
发明人： Larry E. Anders
IPC分类号： F01D17/10 , F02C9/18 , F04D27/02 , F02C3/06
CPC分类号： F01D17/105 , F02C9/18 , F04D27/0215 , F04D27/023 , F04D29/545 , Y10T137/86718
摘要： A fan engine having a core engine and a fan duct has bleed ports positioned circumferentially around the compressor housing of the core engine to bleed flow into the fan duct. A strap covers the circumferential line of holes and it is moved between an open and closed position by a U-shaped flexure element which biases the bleed port seal strap to an open position while an actuator moves the seal strap to a position to close the bleed ports. The ends of said U-shaped flexure elements are connected to the ends of the seal strap and are connected to links which insure that the ends of the strap are moved in a predetermined path.
摘要翻译：具有核心引擎和风扇通道的风扇引擎具有围绕核心发动机的压缩机壳体周向定位的排放口，以使流入风扇管道。带子覆盖孔的圆周线，并且其在打开和关闭位置之间通过U形弯曲元件移动，U形挠曲元件将排出口密封带偏压到打开位置，同时致动器将密封带移动到关闭出口的位置港口。所述U形弯曲元件的端部连接到密封带的端部并且连接到确保带的端部在预定路径中移动的链节。

98. 发明授权

US4214440A Composite gas turbine engine for V/STOL aircraft 失效
标题翻译：用于V / STOL飞机的复合燃气涡轮发动机
公开(公告)号：US4214440A
公开(公告)日：1980-07-29
申请号：US947690
申请日：1978-10-02
申请人： Gerhard Rucker
发明人： Gerhard Rucker
IPC分类号： F02C3/04 , F02K3/06 , F02K3/075 , F02K3/04 , F02C3/06
CPC分类号： F02K3/075 , F02C3/04 , F02K3/06 , Y02T50/672
摘要： A composite gas turbine engine including a fan, a lift device, a compressor, and a turbine for operating the fan, lift device, and compressor. An inner annular duct leads air from the fan to the compressor and turbine, and an outer annular duct leads air from the fan so that it bypasses the compressor and turbine. A supercharger is located between the fan and compressor and within the inner duct. A drive shaft rotated by the turbine is alternatively coupled either to the fan or to the supercharger and lift device. The supercharger raises air pressure flowing to the compressor to a greater degree than does the fan. The drive shaft is connected to a fan shaft and a supercharger shaft through a gearset, and brakes are provided for arresting the motion of the latter two shafts. A third duct leads from the fan to the inner duct while bypassing the supercharger, and means are provided for optionally guiding air into the third duct when the fan is operating, or to the supercharger when the fan is immobilized. The flow of air to the supercharger is varied according to the speed of the supercharger. Intake of hot exhaust by the compressor and supercharger is prevented.
摘要翻译：一种复合燃气涡轮发动机，包括风扇，升降装置，压缩机和用于操作风扇，升降装置和压缩机的涡轮机。内部环形管道将空气从风扇引导到压缩机和涡轮机，并且外部环形管道从风扇引导空气，使得其绕过压缩机和涡轮机。增压器位于风扇和压缩机之间以及内管内。由涡轮机旋转的驱动轴可选地耦合到风扇或增压器和升降装置。增压器将与压缩机流动的空气压力升高到比风扇大的程度。驱动轴通过齿轮组连接到风扇轴和增压器轴，并且制动器用于阻止后两个轴的运动。在旁路增压器的同时，第三管道从风扇引导到内部管道，并且提供用于当风扇运行时可选地将空气引导到第三管道中的装置，或者当风扇被固定时到达增压器。增压器的空气流量根据增压器的速度而变化。防止压缩机和增压器进入热排气。

99. 发明授权

US4050242A Multiple bypass-duct turbofan with annular flow plug nozzle and method of operating same 失效
标题翻译：具有环形流动喷嘴喷嘴的多个旁通风扇涡轮风扇及其操作方法
公开(公告)号：US4050242A
公开(公告)日：1977-09-27
申请号：US636442
申请日：1975-12-01
申请人： Donald J. Dusa
发明人： Donald J. Dusa
IPC分类号： F02K1/06 , B64D33/04 , F02K1/08 , F02K3/077 , F02C3/06 , F02K3/06
CPC分类号： F02K1/08 , F02K3/077 , Y02T50/671
摘要： A propulsion nozzle having a substantially cylindrical translatable shroud partially defining an outer flow duct and an articulated plug mounted within the shroud to partially define an inner coannular flow duct. A variable position valve comprises the downstream portion of the common wall between the ducts for modulating the relative flow rates between ducts and for creating a favorable static pressure balance therebetween. The shroud and plug cooperate to form a variable area throat for the combined duct flows.
摘要翻译：推进喷嘴，其具有基本上圆柱形的可平移的护罩，其部分地限定外部流动管道和安装在护罩内的铰接塞子，以部分地限定内部管状流动管道。可变位置阀包括管道之间的公共壁的下游部分，用于调节管道之间的相对流速并在其间形成有利的静压平衡。护罩和插头配合形成用于组合管道流动的可变区域喉部。

100. 发明授权

US4030291A Thrust reverser for a gas turbofan engine 失效
标题翻译：用于燃气涡轮风扇发动机的推力反向器
公开(公告)号：US4030291A
公开(公告)日：1977-06-21
申请号：US646074
申请日：1976-01-02
申请人： Donald Farley Sargisson
发明人： Donald Farley Sargisson
IPC分类号： F02K1/70 , F02C3/06 , F02K1/20 , F02K3/06
CPC分类号： F02K1/70
摘要： In a mixed flow gas turbine engine of the type which includes an outer nacelle spaced apart from a core engine to define an annular bypass duct therebetween, a thrust reverse is incorporated into the outer nacelle immediately aft of a fan disposed in the inlet. The thrust reverser reverses the discharge direction of the airflow exhausted from the bypass duct thereby to develop reverse thrust. The unique design and location of the thrust reverser permits the use of an aerodynamically efficient and relatively easy to manufacture cylindrical structure immediately aft of the engine fan frame.
摘要翻译：在这种类型的混合气体燃气涡轮发动机中，其包括与核心发动机间隔开的外部机舱，以在它们之间限定环形旁通管道，在设置在入口中的风扇的后方立即将外推入机构并入到外部机舱中。推力反向器反转从旁路管道排出的气流的排放方向，从而产生反向推力。推力反向器的独特设计和位置允许使用空气动力学有效且相对容易地在发动机风扇框架的后方立即制造圆柱形结构。

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