公开(公告)号：US20070144139A1

公开(公告)日：2007-06-28

申请号：US10588600

申请日：2005-08-31

Applicant: Osamu Kawamoto ,  Hiroki Nagata ,  Masayuki Fukutani ,  Mineyasu Oana

Inventor： Osamu Kawamoto ,  Hiroki Nagata ,  Masayuki Fukutani ,  Mineyasu Oana

IPC: F02C7/052

CPC classification number: F02K3/06 ,  F02C7/05 ,  F02C7/052 ,  F05D2220/326 ,  F05D2220/327 ,  F05D2250/323 ,  F05D2250/71 ,  F05D2260/607 ,  Y02T50/675

Abstract: [Object] To provide a gas turbine engine which is simple in structure but can effectively remove foreign matters from the combustion air. [Means] The intake passage 21 includes an inlet portion 29, a curved portion 30 and a reduced diameter portion 31. The bypass duct 24 is curved away from the central axial line CL in a region corresponding to the curved portion 30 and reduced diameter portion 31 of the intake passage 29. Between the intake passage 29 and bypass duct 24 is defined an annular space 32. In the reduced diameter portion 31, the outer liner 20 is formed with a large number of foreign matter introduction openings 33 in a circumferential arrangement for communication between the intake passage 21 and annular space 32. The inner casing 4 is formed with a plurality of foreign matter ejection holes 34 in a circumferential arrangement in a part thereof that curves outward for communication between the annular space 32 and bypass duct 24.

Abstract translation: 提供一种结构简单但能有效地除去燃烧空气中的异物的燃气涡轮发动机。 入口通道21包括入口部分29，弯曲部分30和缩径部分31。 在对应于进气通道29的弯曲部分30和减小直径部分31的区域中，旁通管道24从中心轴线CL弯曲。 在进气通道29和旁通管24之间限定有环形空间32。 在减径部31中，外衬套20形成有大量异物导入开口33，其周向布置成用于连通进气通道21和环形空间32。 内壳4形成有多个异物排出孔34，其周向布置在其一部分中，向外弯曲，用于环形空间32和旁路管道24之间的连通。

公开(公告)号：US20060130454A1

公开(公告)日：2006-06-22

申请号：US11018322

申请日：2004-12-22

Applicant: Chih Liang

Inventor： Chih Liang

IPC: F02C3/00

CPC classification number: F02C7/143 ,  F02C6/18 ,  F02C7/05 ,  F02C7/08

Abstract: A cooling system including a gas turbine engine compressor configured to generate an air stream and compress at least a portion of air contained in the air stream. The cooling system further includes at least one air filter configured to filter the air stream upstream from the gas turbine engine compressor, and at least one heat exchanger configured to provide cooling. The at least one heat exchanger is located in the air stream generated by the gas turbine engine compressor at a position downstream of the at least one air filter and upstream of the gas turbine engine compressor.

Abstract translation: 一种冷却系统，包括燃气涡轮发动机压缩机，所述燃气涡轮发动机压缩机构造成产生空气流并且压缩空气流中包含的至少一部分空气。 所述冷却系统还包括至少一个空气过滤器，该空气过滤器被配置为过滤来自所述燃气涡轮发动机压缩机的上游的气流，以及至少一个被配置为提供冷却的热交换器。 所述至少一个热交换器位于由所述燃气涡轮发动机压缩机在所述至少一个空气过滤器的下游位置和所述燃气涡轮发动机压缩机的上游的位置产生的气流中。

公开(公告)号：US07051509B2

公开(公告)日：2006-05-30

申请号：US10353284

申请日：2003-01-29

Applicant: Kristin E. Grimlund

Inventor： Kristin E. Grimlund

IPC: F02C7/05

CPC classification number: F02C7/05 ,  F02C7/042 ,  Y10T137/0536

Abstract: Apparatus and methods for reducing foreign object debris ingestion into aircraft engines. The apparatus includes a door disposed at a forward end portion of a housing portion of the engine. The door is movable with respect to the engine between a first position in which a first engine inlet is open and a second engine inlet is substantially blocked by the door, and a second position in which the second engine inlet is open and the first engine inlet is substantially blocked by the door. Accordingly, moving the door to its first position during taxiing, takeoff, and landing substantially reduces the risk of foreign object debris ingestion into the second engine inlet.

Abstract translation: 用于减少摄入飞机发动机的异物碎屑的装置和方法。 该装置包括设置在发动机的壳体部分的前端部的门。 门能够相对于发动机在第一位置和第二发动机入口被门打开的第一位置和第二发动机入口被第一发动机入口打开并且第二发动机入口打开的第二位置和第一发动机入口 被门大体阻挡。 因此，在滑行，起飞和着陆期间将门移动到其第一位置大大降低了异物碎片摄入第二发动机入口的风险。

公开(公告)号：US20030024233A1

公开(公告)日：2003-02-06

申请号：US10216978

申请日：2002-08-12

Inventor： Philip H. Snyder

IPC: F02C007/052

CPC classification number: B01D45/08 ,  B01D45/16 ,  F01D9/026 ,  F01D9/065 ,  F01D25/162 ,  F02C7/05 ,  F02C7/052 ,  F04D29/701 ,  F05D2250/15 ,  F05D2250/25 ,  F05D2260/607 ,  Y10T137/0536

Abstract: A particle separator for use with a turbine engine is arranged to divide a flow of air into a radially inner air flow and a radially outer air flow. The particle separator is further arranged to separate inner particles from the inner air flow to allow air from the inner air flow to enter the turbine engine without the inner particles and arranged to separate outer particles from the outer air flow to allow air from the outer air flow to enter the turbine engine without the outer particles.

Abstract translation: 用于涡轮发动机的颗粒分离器被布置成将空气流分成径向内部空气流和径向外部空气流。 颗粒分离器进一步布置成将内部颗粒与内部空气流分离，以允许来自内部空气流的空气进入涡轮发动机而没有内部颗粒，并且布置成将外部颗粒与外部空气流分离以允许来自外部空气的空气 流入涡轮发动机而没有外部颗粒。

公开(公告)号：US20030024232A1

公开(公告)日：2003-02-06

申请号：US09920566

申请日：2001-08-01

Inventor： Philip H. Snyder ,  Baily Vittal

IPC: F02C007/052

CPC classification number: F02C7/05 ,  B01D45/08 ,  B01D45/16 ,  F02C7/052 ,  F05D2260/607 ,  Y10T137/0536

Abstract: An attachment for the air intake of a gas turbine engine includes a plurality of particle separators. The particle separators cooperate to define an attachment axis and are spaced circumferentially about the attachment axis. Each particle separator includes a housing defining a separator axis, a first flow passage having at least a portion that is annular, an annular opening, and an annular second flow passage. The first and second flow passages are configured so that inertia of particles entrained in a stream of air flowing through the annular portion of the first flow passage tends to cause the particles to flow from the annular portion through the opening into the second flow passage to allow the stream of air to enter the engine flow passage free of the particles removed therefrom. The separator axes are parallel to and spaced apart from the attachment axis.

Abstract translation: 用于燃气涡轮发动机的进气的附件包括多个颗粒分离器。 颗粒分离器协作以限定附接轴线并围绕连接轴线周向间隔开。 每个颗粒分离器包括限定分离器轴线的壳体，具有至少一部分是环形的第一流动通道，环形开口和环形的第二流动通道。 第一和第二流动通道构造成使得夹带在流过第一流动通道的环形部分的空气流中的颗粒的惯性倾向于使颗粒从环形部分通过开口流入第二流动通道以允许 进入发动机流动通道的空气流没有从其中去除的颗粒。 分离器轴线与附接轴线平行并间隔开。

公开(公告)号：US06484507B1

公开(公告)日：2002-11-26

申请号：US09873693

申请日：2001-06-05

Applicant: Louis A. Pradt

Inventor： Louis A. Pradt

IPC: F02C330

CPC classification number: B01D53/1412 ,  F01D25/32 ,  F02C3/30 ,  F02C7/05 ,  F05D2260/212 ,  F05D2260/607

Abstract: A process for creating and controlling the flow of a stream of liquid droplets of a predetermined maximum size in a stream of gas in which the liquid is first passed through a means to produce a fine spray, mist, or fog in the stream of gas and in which the subsequent stream of droplets and gas is treated in a device designed to remove larger droplets and allow the stream of gas containing the small droplets of a predetermined maximum size to pass to the inlet of a gas compressor.

Abstract translation: 一种用于产生和控制气体流中预定最大尺寸的液滴流的流程，其中液体首先通过一种装置以在气流中产生细微的喷雾，雾或雾， 其中随后的液滴和气体流在被设计成去除较大液滴的装置中被处理，并允许含有预定最大尺寸的小液滴的气体流通过到气体压缩机的入口。

公开(公告)号：US6129309A

公开(公告)日：2000-10-10

申请号：US122004

申请日：1998-07-24

Applicant: David M. Smith ,  John Dorris, III

Inventor： David M. Smith ,  John Dorris, III

IPC: B64D33/02 ,  F02C7/05 ,  B64B1/24 ,  F02G3/00

CPC classification number: F02C7/05 ,  B64D33/02 ,  B64D2033/0273

Abstract: An aircraft engine apparatus with a reduced inlet vortex is provided which utilizes a vortex disruption system that periodically discharges pulses of engine bleed fluid through at least one outlet port opening through the inlet of the engine nacelle to disrupt the engine inlet vortex. The vortex disruption system thereby prevents ingestion of foreign matter into the engine inlet without sacrificing engine power, efficiency, or aircraft cruise performance.

Abstract translation: 提供了具有减小的入口涡流的飞行器发动机装置，其利用涡流破坏系统，其周期性地通过穿过发动机舱的入口的出口端口打开发动机排放流体的脉冲，以破坏发动机入口涡流。 因此，涡流破坏系统防止异物进入发动机入口，而不牺牲发动机功率，效率或飞行器巡航性能。

公开(公告)号：US5299914A

公开(公告)日：1994-04-05

申请号：US757854

申请日：1991-09-11

Applicant: Jan C. Schilling

Inventor： Jan C. Schilling

IPC: F01D5/14 ,  F02C7/05 ,  F04D29/32

CPC classification number: F02C7/05 ,  F01D5/141 ,  F04D29/324 ,  F05D2240/301 ,  Y02T50/672 ,  Y02T50/673

Abstract: A turbofan gas turbine engine fan stage having alternating relatively rugged, preferably hollow titanium, blades and staggered relatively less rugged, preferably composite, blades. The blades are staggered such that the leading edges of the rugged titanium blades are positioned forward of the leading edges of the less rugged composite blades. One embodiment provides that all fan blades have trailing edges at the same axial position while another embodiment provides that all fan blades are of the same size and shape.

Abstract translation: 涡轮风扇燃气涡轮发动机风扇台具有交替相对粗糙的，优选中空的钛，叶片和交错相对较不坚固，优选复合的叶片。 刀片交错，使得坚固的钛刀片的前缘位于较不坚固的复合刀片的前缘的前方。 一个实施例提供了所有风扇叶片具有相同轴向位置的后缘，而另一实施例规定所有风扇叶片具有相同的尺寸和形状。

公开(公告)号：US4881367A

公开(公告)日：1989-11-21

申请号：US157942

申请日：1988-02-19

Applicant: Richard J. Flatman

Inventor： Richard J. Flatman

IPC: F02C7/052 ,  B64D33/02 ,  F02C7/05

CPC classification number: F02C7/05 ,  B64D33/02 ,  B64D2033/022

Abstract: The invention relates to turbopropeller gas turbine engines of the type which have a propeller positioned upstream of the gas generator. Intake openings supply air through intake ducts and annular intake duct to the gas generator. A separating duct removes foreign bodies from the air flowing through an outlet. The separating duct has a plurality of ejector nozzles equi-spaced in the wall of the duct. The ejector nozzles induce a flow through the separating duct to draw the foreign bodies through the separating duct. The separating duct allows the passage of large foreign bodies therethrough without damage to the ejector nozzles. The ejector nozzles are supplied with air from a compressor of the gas generator, and this allows control of the flow through the separating duct by a valve.

Abstract translation: 本发明涉及一种具有位于气体发生器上游的螺旋桨的涡桨发动机燃气涡轮发动机。 进气开口通过进气管道和环形进气管道向气体发生器供应空气。 分离管道从流过出口的空气中除去异物。 分离管道具有在管道的壁上等距间隔开的多个喷射器喷嘴。 喷射器喷嘴引导通过分离管道的流动，以将异物抽出通过分离管道。 分离管允许大异物穿过其中而不损坏喷射器喷嘴。 喷射器喷嘴从气体发生器的压缩机供应空气，这允许通过阀控制通过分离管道的流量。

公开(公告)号：US4867634A

公开(公告)日：1989-09-19

申请号：US171627

申请日：1988-03-22

Applicant: Donald E. Baker ,  Joe L. Byrne ,  Leo R. Muller ,  Phillip L. Schmidt

Inventor： Donald E. Baker ,  Joe L. Byrne ,  Leo R. Muller ,  Phillip L. Schmidt

IPC: F01D25/32 ,  F02C7/05

CPC classification number: F02C7/05 ,  F01D25/32

Abstract: A turbocharger turbine housing particulate debris trap for collecting all unwanted exhaust gas entrained particles before engagement with the turbine wheel. The trap can be located anywhere in the exhaust system upstream of the turbine wheel and is designed to take advantage of both inertial and gravitational forces. Systems for purging the trap of collected debris is also disclosed.

Abstract translation: 涡轮增压器涡轮机容纳用于在与涡轮机叶轮接合之前收集所有不需要的废气夹带的颗粒的颗粒物碎片捕集器。 捕集器可以位于涡轮机叶轮上游的排气系统的任何地方，并被设计成利用惯性力和重力。 还披露了用于清除收集的碎片陷阱的系统。