公开(公告)号：US4832568A

公开(公告)日：1989-05-23

申请号：US540714

申请日：1983-10-13

申请人： Robert H. Roth ,  Bruno G. Lampsat ,  Jack L. Readnour

发明人： Robert H. Roth ,  Bruno G. Lampsat ,  Jack L. Readnour

IPC分类号： F01D9/04

CPC分类号： F01D9/042 ,  F05D2230/60 ,  Y02T50/672 ,  Y02T50/673 ,  Y10S416/50

摘要： An assembly for mounting a plurality of circumferentially spaced and radially extending airfoils. In a preferred embodiment the assembly comprises a plurality of arcuate mounting fairings each including a central boss having at least one radially extending recess disposed in a radially inner surface thereof which contains an elastomeric boot for receiving an end of one of the plurality of airfoils. The mounting fairing further includes integral first and second flanges extending circumferentially outwardly from opposite sides of the boss portion which overlap complementary second and first flanges, respectively, of adjacent mounting fairings. Fastening means connect the first and second flanges of adjacent mounting fairings to form a continuous annular shroud.

摘要翻译： 一种用于安装多个周向间隔开且径向延伸的翼型件的组件。 在优选实施例中，组件包括多个弧形安装整流装置，每个弧形安装整流装置均包括具有设置在其径向内表面中的至少一个径向延伸的凹部的中心凸台，其包含用于接收所述多个翼型件之一的端部的弹性衬套。 安装整流罩还包括从凸台部分的相对侧周向向外延伸的集成的第一和第二凸缘，其分别与相邻安装整流罩的互补的第二和第一凸缘重叠。 紧固装置连接相邻安装整流罩的第一和第二凸缘以形成连续的环形护罩。

公开(公告)号：US4786234A

公开(公告)日：1988-11-22

申请号：US390193

申请日：1982-06-21

申请人： Jack L. Readnour

发明人： Jack L. Readnour

IPC分类号： F01D5/14 ,  F01D5/18 ,  F01D5/28 ,  F01D9/02

CPC分类号： F01D5/187 ,  F01D5/147 ,  F01D5/284 ,  F05D2240/10

摘要： A turbine airfoil, such as a turbine blade or nozzle vane, is disclosed for use in a high temperature environment. The airfoil comprises a center post and at least one side piece. The side piece is attached to the center post so that, at room temperature, a clearance between the center post and the side piece permits limited relative movement between the post and side piece. This clearance space, however, is dimensioned so that at the operating temperature of the turbine, thermal expansion of the center post and/or side piece substantially eliminates the clearance as well as the limited movement between the center post and side piece.

摘要翻译： 涡轮机叶片，例如涡轮机叶片或喷嘴叶片，被公开用于高温环境中。 翼型件包括中心柱和至少一个侧件。 侧片附接到中心柱，使得在室温下，中心柱和侧片之间的间隙允许柱和侧片之间的有限的相对运动。 然而，该间隙空间的尺寸使得在涡轮机的工作温度下，中心柱和/或侧面件的热膨胀基本上消除了间隙以及中心柱和侧件之间的有限运动。

公开(公告)号：US5000399A

公开(公告)日：1991-03-19

申请号：US483693

申请日：1990-02-23

申请人： Jack L. Readnour ,  Jack D. Wright

发明人： Jack L. Readnour ,  Jack D. Wright

IPC分类号： B64D33/02 ,  F02C7/042

CPC分类号： B64D33/02 ,  F02C7/042 ,  Y02T50/671

摘要： An annular nacelle for a turbine engine of an aircraft has a variable contour annular air inlet. The variable contour annular inlet includes annular outer and inner surface-defining radially-spaced structures on the forward portion of the nacelle, an annular member disposed between the annular outer and inner structures and coupled to the annular outer structure for sliding movement along the interiors of the annular outer and inner structures, and a plurality of actuating mechanisms coupled between the nacelle body and the annular member. The actuating mechanisms are operable for moving the annular member between forward and rearward positions. At the forward position, the annular member is located between the forward ends of the annular outer and inner structures with the annular outer structure expanded to an enlarged diameter such that the annular member forms therewith an inlet lip having an aerodynamically blunt exterior contour adapted to reduce drag during takeoff and landing operation of the aircraft. At the rearward position, the annular member is spaced rearwardly from the forward ends of the annular outer and inner structures with the annular outer structure contracted to a reduced diameter permitting the annular outer and inner structures at the forward ends thereof to form an inlet lip having an aerodynamically sharp exterior contour adapted to reduce drag during cruise operation of the aircraft.

摘要翻译： 用于飞行器的涡轮发动机的环形机舱具有可变轮廓的环形空气入口。 可变轮廓环形入口包括在机舱的前部上的环形外表面和内表面限定的径向间隔的结构，环形构件，设置在环形外结构和内结构之间并且联接到环形外结构，以沿着内部结构的内部滑动 环形外部和内部结构以及联接在机舱主体和环形构件之间的多个致动机构。 致动机构可操作以使环形构件在前后位置之间移动。 在向前位置处，环形构件位于环形外部结构和内部结构的前端之间，其中环形外部结构膨胀到扩大的直径，使得环形构件与其形成具有适于减少的空气动力学钝的外部轮廓的入口唇缘 在飞机起飞和着陆操作期间拖动。 在后部位置，环形构件与环形外部结构和内部结构的前端向后间隔开，其中环形外部结构收缩到减小的直径，允许其前端处的环形外部和内部结构形成入口唇缘， 适合在航空器巡航操作期间减少阻力的空气动力学锐利的外部轮廓。

公开(公告)号：US3976394A

公开(公告)日：1976-08-24

申请号：US597061

申请日：1975-07-18

申请人： David A. Tarter ,  Jack L. Readnour

发明人： David A. Tarter ,  Jack L. Readnour

IPC分类号： F04D27/02

CPC分类号： F04D27/0215 ,  F04D29/522

摘要： A two part metering adapter ring, for providing bleed air from the compressor of an aircraft engine, having a plurality of metering air flow passages. The adapter ring is secured to the outer casing stator support member and has a movable seal engaging a member on the inner casing stator support member. A pair of spring members hold the seal in contact with the seal engaging member on the inner casing stator support member.

摘要翻译： 用于从飞机发动机的压缩机提供排气的两部分计量适配环，具有多个计量空气流动通道。 适配环固定在外壳定子支承件上，并具有与内套定子支承件上的构件啮合的活动密封件。 一对弹簧构件将密封件保持与内壳定子支撑构件上的密封接合构件接触。