公开(公告)号：US06276127B1

公开(公告)日：2001-08-21

申请号：US09338246

申请日：1999-06-22

申请人： John R. Alberti

发明人： John R. Alberti

IPC分类号： F02K138

CPC分类号： F02K1/386 ,  F02K1/48 ,  F05D2260/96

摘要： The mixer has a circular forward end which is attached to the exit of a jet engine, or the core of a bypass engine. The mixer has radial lobes which increase in their radial dimension with increasing distance aft of the forward end. There are corrugations, termed circumferential lobes, in the after portions of the walls of the radial lobes. These circumferential lobes increase the ratios of wetted areas to cross sectional areas of the passageways through the mixer. Also, the dimensions of these lobes are small relative to the radius of the mixer.

摘要翻译： 混合器具有连接到喷气发动机的出口或旁路引擎的核心的圆形前端。 混合器具有径向叶片，其随着前端的后部距离的增加而增加其径向尺寸。 在径向叶片的壁的后部分中有波纹，称为圆周波瓣。 这些周向凸起增加了通过混合器的通道的润湿面积与横截面积的比率。 此外，这些叶片的尺寸相对于混合器的半径较小。

公开(公告)号：US06418709B1

公开(公告)日：2002-07-16

申请号：US09570883

申请日：2000-05-15

申请人： Andrew Narcus ,  Keith Brewer ,  Thomas F. Pechette

发明人： Andrew Narcus ,  Keith Brewer ,  Thomas F. Pechette

IPC分类号： F02K138

CPC分类号： F23R3/26

摘要： A liner for a gas turbine engine is provided that includes a first liner section and a second liner section. The first liner section includes a first flange having a first contact surface. The second liner section includes a second flange having a second contact surface and a plurality of apertures. The first and second flanges axially overlap one another, and in a circumferential liner the second flange is disposed radially outside of the first flange. A channel is formed by the two liner sections that is open to the core gas path. In a first position, the first flange axially overlaps the second flange by a first distance and the apertures are misaligned with the first flange and disposed within the channel. Cooling air entering apertures within the second flange subsequently passes into the channel. In a second position, the first flange axially overlaps the second flange by a second distance. The second distance is greater than the first distance and in the second position the apertures in the second flange are substantially aligned with the first flange. Cooling air entering the second flanges apertures subsequently impinges on the first flange.

摘要翻译： 提供了一种用于燃气涡轮发动机的衬套，其包括第一衬里部分和第二衬里部分。 第一衬里部分包括具有第一接触表面的第一凸缘。 第二衬里部分包括具有第二接触表面和多个孔的第二凸缘。 第一和第二凸缘彼此轴向重叠，并且在圆周衬套中，第二凸缘设置在第一凸缘的径向外侧。 由通向核心气体通道的两个衬垫部分形成通道。 在第一位置，第一凸缘与第二凸缘轴向重叠第一距离，并且孔与第一凸缘不对准并且设置在通道内。 在第二凸缘内进入孔的冷却空气随后进入通道。 在第二位置，第一凸缘与第二凸缘轴向重叠第二距离。 第二距离大于第一距离，而在第二位置，第二凸缘中的孔基本上与第一凸缘对准。 进入第二凸缘孔的冷却空气随后撞击在第一凸缘上。

公开(公告)号：US06487848B2

公开(公告)日：2002-12-03

申请号：US09187592

申请日：1998-11-06

申请人： Steven H. Zysman ,  Wesley K. Lord ,  Gregory A. Kohlenberg

发明人： Steven H. Zysman ,  Wesley K. Lord ,  Gregory A. Kohlenberg

IPC分类号： F02K138

CPC分类号： F02K1/386 ,  B64D33/06 ,  F02K1/46 ,  F02K3/025

摘要： The present invention relates to a gas turbine engine jet noise suppressor which does not appreciably adversely impact engine thrust and performance. The jet noise suppressor includes a nozzle, having an arrangement thereon of tabs disposed on the downstream end of the nozzle, the tabs having a length and the angular offset with respect to the engine flow such that mixing occurs primarily at the interface of the engine flow and the ambient air. In addition, various construction details are developed for the tabs including tabs that are trapezoidal with tapered sides such that the tabs minimize adverse impact to engine performance.

摘要翻译： 本发明涉及一种不明显不利地影响发动机推力和性能的燃气轮机发动机喷射噪声抑制器。 喷射噪声抑制器包括喷嘴，其上设置有设置在喷嘴下游端的突片，突片具有相对于发动机流量的长度和角度偏移，使得混合主要发生在发动机流动的界面处 和环境空气。 此外，针对包括具有锥形边梯形的翼片的翼片开发出各种构造细节，使得翼片最小化对发动机性能的不利影响。

公开(公告)号：US06260352B1

公开(公告)日：2001-07-17

申请号：US09297974

申请日：1999-07-14

申请人： Dimitrie Negulescu ,  Jörg Haarmeyer

发明人： Dimitrie Negulescu ,  Jörg Haarmeyer

IPC分类号： F02K138

CPC分类号： F01D9/065 ,  F01D5/082 ,  F01D25/125 ,  F02K1/04 ,  F02K3/04 ,  Y02T50/676

摘要： A turbofan aircraft engine has a core engine, which is arranged in a gondola, and a fan which delivers a cold air current through a bypass flow duct to a mixer within which a low-pressure turbine cone is provided and on which the hot-gas current emerging from the low-pressure turbine of the core engine is mixed with the cold-air current. A portion of the cold-air current is branched off by an ejector effect and, as a cooling air current for the low pressure turbine housing, arrives in a ring gap between the housing and a covering surrounding this housing. A portion of this cooling air current is guided by hollow outlet guide blades of a follower guide wheel of the low-pressure turbine for sealing off the rearmost ring gap between the rotor and the stator of the low-pressure turbine, while the largest portion of the cooling air current reaches the ejector. The largest portion of the cooling air current arrives through the hollow outlet guide blades in the interior of the low-pressure turbine cone which has a jet-type outlet opening at its downstream free end section. As a result, this downstream end section acts as an ejector by way of which the cooling air current is admixed to the air current coming from the mixer.

摘要翻译： 涡轮风扇飞机发动机具有布置在吊车中的核心发动机和将冷气流通过旁通流动管道传递到其中设置有低压涡轮锥体的混合器的风扇，并且热气体 从核心发动机的低压涡轮机出来的电流与冷气流混合。 冷空气电流的一部分由喷射器效应分支，并且作为用于低压涡轮机壳体的冷却气流到达壳体和围绕该壳体的覆盖物之间的环间隙。 该冷却气流的一部分由低压涡轮机的从动引导轮的中空出口引导叶片引导，用于密封低压涡轮机的转子和定子之间的最后环形空隙，而最大部分 冷却气流到达喷射器。 冷却气流的最大部分通过位于其下游自由端部处具有喷射型出口的低压涡轮锥体的内部的中空出口导向叶片。 结果，该下游端部分用作喷射器，通过该喷射器将冷却气流与来自混合器的气流混合。

公开(公告)号：US06253540B1

公开(公告)日：2001-07-03

申请号：US06396210

申请日：1982-07-08

申请人： Thomas Chew ,  William Steyer ,  Clinton Clark Moore ,  Michael Charles Harrold

发明人： Thomas Chew ,  William Steyer ,  Clinton Clark Moore ,  Michael Charles Harrold

IPC分类号： F02K138

CPC分类号： F02K1/825 ,  F05D2240/126

摘要： An infrared suppressor system for a gas turbine engine is provided for suppressing infrared radiation associated with the hot metal parts of the engine and with the hot exhaust gases exhausted from the engine. The system features a unique arrangement of multiple baffles that are connected together as a single baffle module. The baffle arrangement permits mixing of hot and cool gas flows while eliminating line-of-sight infrared radiation in an axially compact suppressor. The baffles are additionally linked together into a single insertable baffle module that permits removal of the baffle module when infrared suppression is unnecessary.

摘要翻译： 提供一种用于燃气轮机的红外抑制器系统，用于抑制与发动机的热金属部件和从发动机排出的热废气相关联的红外辐射。 该系统具有独特的多个挡板的布置，它们作为单个挡板模块连接在一起。 挡板装置允许热和冷气体流的混合，同时消除轴向紧凑抑制器中的视线红外辐射。 挡板另外连接在一起成为一个可插入的挡板模块，当不需要红外线抑制时允许拆卸挡板模块。