公开(公告)号：US07677870B1

公开(公告)日：2010-03-16

申请号：US11409926

申请日：2006-04-22

申请人： Alfred P. Matheny

发明人： Alfred P. Matheny

IPC分类号： F01D5/32

CPC分类号： F01D5/3053

摘要： A turbo machine airfoil, such as a blade or a vane in a compressor, in which the airfoil root portion includes screw threads having a dove tail cross sectional shape, and the rotor disk includes holes having similar screw threads such that a blade or vane can be easily replaced by unscrewing the old blade or vane and screwing in a new blade or vane. A locking pin biased by a spring is located in the root of the airfoil to lock the airfoil in the threaded hole to prevent the airfoil from loosening due to vibrations and to lock the airfoil in place at a desired angle of attack for maximum efficiency of the turbo machine. The removable cover plate is located on the casing and over the rotor disk such that the blade can be removed through the opening without the need to disassemble the turbo machine.

摘要翻译： 涡轮机翼型件，例如压缩机中的叶片或叶片，其中翼型件根部包括具有鸽尾截面形状的螺纹，并且转子盘包括具有相似螺纹的孔，使得叶片或叶片可 可以通过旋松旧的叶片或叶片并拧入新的叶片或叶片来轻松更换。 由弹簧偏压的锁定销定位在翼型件的根部中，以将翼型件锁定在螺纹孔中，以防止机翼由于振动而松动，并将翼型件以期望的迎角锁定在适当位置，以最大限度地提高效率 涡轮增压机。 可拆卸的盖板位于壳体上并且位于转子盘上，使得叶片可以通过开口移除，而不需要拆卸涡轮机。

公开(公告)号：US07661931B1

公开(公告)日：2010-02-16

申请号：US11708215

申请日：2007-02-20

申请人： Alfred P. Matheny

发明人： Alfred P. Matheny

IPC分类号： F01D5/32

CPC分类号： F01D5/3053

摘要： A fan type compressor includes a rotor disk with a plurality of root insertion openings to receive a blade. Each insertion opening includes two shear pin slots on the sides, and the blade includes a root portion with shear pin slots formed on the pressure side and the suction side of the root. The blade is inserted into the insertion opening such that the slots are aligned, and a shear pin is inserted into both slots to secure the blade within the rotor disk. The shear pin slots are formed below the airfoil curvature and follow the airfoil curvature at the root portion. The shear pins are flexible enough to bend during insertion into the slots, and are strong enough to prevent from shearing off during rotor disk operation. The blade attachment structure provides for reduction of the dead weight from the attachment structure in order to simulate an IBR while providing for easy removal and replacement of a damaged blade.

摘要翻译： 风扇式压缩机包括具有多个根部插入开口以接收叶片的转子盘。 每个插入开口包括两侧的两个剪切销槽，并且该叶片包括根部，该根部具有形成在根部的压力侧和吸力侧的剪切销槽。 将刀片插入到插入口中，使得狭槽对准，并且将剪切销插入两个狭槽中，以将刀片固定在转子盘内。 剪切销槽形成在翼型曲率下方，并跟随根部的翼型曲率。 剪切销具有足够的柔性，可在插入槽内弯曲，并且足够坚固以防止在转盘运行过程中剪切。 叶片附接结构提供了减少来自附接结构的自重以便模拟IBR，同时提供易于拆卸和更换损坏的叶片。

公开(公告)号：US07410342B2

公开(公告)日：2008-08-12

申请号：US11206527

申请日：2005-08-18

申请人： Alfred P. Matheny

发明人： Alfred P. Matheny

IPC分类号： F01D9/04 ,  F01D9/06 ,  F01D5/14 ,  F01D5/18

CPC分类号： F01D5/147 ,  F01D5/187 ,  F01D5/282 ,  F01D5/284 ,  F05D2230/60 ,  F05D2240/80 ,  F05D2300/21 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676 ,  Y10T29/49337 ,  Y10T29/49341 ,  Y10T29/49343 ,  Y10T29/49801

摘要： A blade or a vane preferably used in a gas turbine engine, the blade or vane being formed of a metallic core or insert with a ceramic airfoil surface bonded to the metallic insert. The insert includes a series of concave and convex portions arranged along the outer surface, in which a plurality of hoop fibers are secured within a resin matrix to firmly secure the metallic insert to the ceramic airfoil body. Axial loads between the insert and the ceramic body are transferred to the hoop fibers. The hoop fibers are strong enough to resist extending in length that would permit the hoop fibers from sliding over the widest portion of the insert.

摘要翻译： 优选用于燃气涡轮发动机中的叶片或叶片，叶片或叶片由金属芯或插入件形成，陶瓷翼型表面结合到金属插入件上。 插入件包括沿着外表面布置的一系列凹凸部分，其中多个环箍纤维固定在树脂基体内，以将金属插入物牢固地固定在陶瓷翼型体上。 插入件和陶瓷体之间的轴向载荷被传递到环箍纤维。 箍纤维足够坚固以抵抗长度上的延伸，这将允许环箍纤维在插入物的最宽部分上滑动。

公开(公告)号：US4568247A

公开(公告)日：1986-02-04

申请号：US594608

申请日：1984-03-29

申请人： John C. Jones ,  Alfred P. Matheny

发明人： John C. Jones ,  Alfred P. Matheny

IPC分类号： F01D5/22 ,  F01D5/10

CPC分类号： F01D5/22 ,  Y02T50/671 ,  Y02T50/673 ,  Y10S416/50

摘要： A blade vibration damper for a rotor assembly of an axial flow machine seats simultaneously on a radially inwardly facing surface of a blade platform and the radially inwardly facing surface of an adjacent element, such as the platform of a circumferentially adjacent blade. The damper has its mass center of gravity nearer one contact area than the other so as to reduce the normal load on the blade platform generated by centrifugal force. By properly locating the center of gravity of the damper, the size of the normal force can be optimized to maximize damping.

摘要翻译： 用于轴流式机器的转子组件的叶片减振器同时位于叶片平台的径向向内的表面上以及相邻元件的径向向内的表面，例如周向相邻的叶片的平台。 减震器的质心重心比另一方接近一个接触面积，以减少由离心力产生的叶片平台上的正常负荷。 通过适当地定位阻尼器的重心，可以优化法向力的大小以最大化阻尼。

公开(公告)号：US07931443B1

公开(公告)日：2011-04-26

申请号：US11827055

申请日：2007-07-10

申请人： Brian Potter ,  Alfred P. Matheny

发明人： Brian Potter ,  Alfred P. Matheny

IPC分类号： F01D5/26

CPC分类号： F01D5/26 ,  F01D5/282 ,  F05D2260/96 ,  Y10S416/50

摘要： A turbomachine with a row of blades in which the blades are structured such that the blades can untwist at higher rotational speeds in order to provide optimal aerodynamics at different rotational speeds. Each blade is formed with a thin slot between the pressure side wall and the suction side wall so that stresses from centrifugal forces occurring during high rotations will not pass from adjacent walls and allow for the blade to untwist more than a solid blade. Each blade is formed from a fiber laminated composite material with the fibers oriented at different directions to form different stiffness in each direction so that a desired untwist can occur based upon a given blade mass and rotational speed. A thin sheet of a slippery material can be placed within the thin slot and between the adjacent airfoil walls to allow slippage between the adjacent walls and to promote damping for the blade.

摘要翻译： 具有一排叶片的涡轮机，其中叶片被构造成使得叶片能够以更高的旋转速度解开，以便在不同的转速下提供最佳的空气动力学。 每个叶片在压力侧壁和吸力侧壁之间形成有薄的狭槽，使得在高转速期间产生的离心力的应力将不会从相邻的壁通过，并且允许刀片比固体刀片解捻更多。 每个叶片由纤维层压复合材料形成，其中纤维在不同方向上定向，以在每个方向上形成不同的刚度，使得基于给定的叶片质量和转速可以发生所需的解捻。 可以在薄槽内和相邻的翼型件壁之间放置薄的滑动材料，以允许相邻壁之间滑动并促进叶片的阻尼。

公开(公告)号：US07686571B1

公开(公告)日：2010-03-30

申请号：US11784782

申请日：2007-04-09

申请人： Alfred P. Matheny

发明人： Alfred P. Matheny

IPC分类号： F01B25/16

CPC分类号： F01D9/041 ,  F01D9/042 ,  F01D9/044 ,  F05D2300/607

摘要： A stator vane assembly for a gas turbine engine, the stator vane including an airfoil portion formed from a single crystal material and two platforms attached to the ends of the airfoil by shear pins that fit within slots formed between the platform and airfoil. The shear pin slots extend along the contour of the airfoil where the lowest stress levels are located. The platforms include openings having the same cross sectional shape as the curved airfoil. Because of the shear pin retainers between the airfoil and the platforms, the airfoil can be formed from a single crystal material while the platforms are un-coupled from the airfoil and can be made from a different material.

摘要翻译： 一种用于燃气涡轮发动机的定子叶片组件，所述定子叶片包括由单晶材料形成的翼型部分和通过剪切销附接到所述翼型件的端部的两个平台，所述剪切销装配在所述平台和翼型之间形成的槽内。 剪切销槽沿着最低应力水平所在的翼型轮廓延伸。 平台包括具有与弯曲翼型相同的横截面形状的开口。 由于翼型件和平台之间的剪切销保持器，翼型件可以由单晶材料形成，同时平台与翼型件不联接并且可以由不同的材料制成。

公开(公告)号：US07578655B1

公开(公告)日：2009-08-25

申请号：US11437487

申请日：2006-05-20

申请人： Alfred P. Matheny

发明人： Alfred P. Matheny

IPC分类号： F01D5/22

CPC分类号： F02K3/04 ,  F01D5/147 ,  F01D5/225 ,  F01D5/282 ,  F02C3/073 ,  F04D29/023 ,  F04D29/322 ,  F04D29/324 ,  F04D29/329 ,  F05D2300/603

摘要： A composite turbine blade and fan blade assembly for use in a turbo machine such as a gas turbine engine. The turbine blade assembly includes a plurality of metallic turbine blades secured to a rotor disk and forming an outer shroud assembly. A fiber reinforced composite fan blade assembly includes an annular ring with a plurality of fan blades extending there from. The annular ring has a conical shape to allow for easy installation over the outer shroud assembly, and is secured to the outer shroud assembly to force the fan blade assembly to rotate with the turbine blades, yet allow for a slight radial movement between the fan blades and the turbine blades. The turbine blades are formed of a high temperature super alloy to allow for use in a gas turbine engine, and the fan blade assembly is made from a fiber reinforced composite to allow for higher rotational speeds and smaller diameters for smaller gas turbine engines without exceeding allowable stress limits.

摘要翻译： 一种用于涡轮机例如燃气涡轮发动机的复合涡轮机叶片和风扇叶片组件。 涡轮叶片组件包括固定到转子盘并形成外护罩组件的多个金属涡轮叶片。 纤维增强复合风扇叶片组件包括具有从其延伸的多个风扇叶片的环形环。 环形环具有圆锥形形状以允许容易地安装在外护罩组件上，并且固定到外护罩组件以迫使风扇叶片组件与涡轮机叶片一起旋转，但允许在风扇叶片之间进行轻微的径向运动 和涡轮叶片。 涡轮叶片由高温超合金形成以允许在燃气涡轮发动机中使用，并且风扇叶片组件由纤维增强复合材料制成，以允许更小的燃气涡轮发动机具有更高的转速和更小的直径，而不超过允许 压力极限

公开(公告)号：US07435055B2

公开(公告)日：2008-10-14

申请号：US11093162

申请日：2005-03-29

申请人： Christian M. Hansen ,  Alfred P. Matheny ,  Brian Potter

发明人： Christian M. Hansen ,  Alfred P. Matheny ,  Brian Potter

IPC分类号： F01D5/32

CPC分类号： F01D5/32 ,  F01D5/3038

摘要： A locking spacer assembly for filling a void between adjacent components in a turbine engine. In at least one embodiment, the locking spacer assembly may be configured to be inserted between adjacent turbine blades in a disc groove in a turbine blade stage assembly. The locking spacer assembly may be formed from fore and aft end supports and a locking device having fore and aft angled surfaces for urging the fore and aft end supports into lateral recesses in the disc groove. The locking spacer assembly may also include a mid spacer positioned between the fore and aft end supports. A retainer may be attached to the locking device to draw the fore and aft angled surfaces of the locking device into contact with the fore and aft support surfaces and urge the first and second end supports into lateral recesses in the disc groove.

摘要翻译： 一种用于填充涡轮发动机中的相邻部件之间的空隙的锁定间隔件组件。 在至少一个实施例中，锁定间隔件组件可构造成在涡轮叶片级组件中的盘槽中插入相邻的涡轮叶片之间。 锁定间隔件组件可以由前端支撑件和后端支撑件形成，并且锁定装置具有前后成角度的表面，用于将前端支撑件和后端支撑件推进到盘槽中的横向凹槽中。 锁定间隔件组件还可以包括位于前端支撑件和后端支架之间的中间间隔件。 保持器可以附接到锁定装置以拉动锁定装置的前后角度的表面与前后支撑表面接触并且将第一和第二端部支撑件推动到盘槽中的侧向凹部中。

公开(公告)号：US5601401A

公开(公告)日：1997-02-11

申请号：US576413

申请日：1995-12-21

申请人： Alfred P. Matheny ,  Brian H. Terpos

发明人： Alfred P. Matheny ,  Brian H. Terpos

IPC分类号： F01D17/16 ,  F01D17/12

CPC分类号： F01D17/162

摘要： An apparatus for actuating variable stage vanes is provided having a plurality of pivot arms, a synchronizing ring, and apparatus for pivotly attaching the pivot arms to the synchronizing ring. Each pivot arm includes a first end for fixed attachment with one of the vanes. The synchronizing ring includes a first flange, a second flange, a web extending between the flanges, and a plurality of openings disposed in the web. The apparatus for pivotly attaching the pivot arms to the synchronizing ring are disposed within the openings.

摘要翻译： 提供了一种用于致动可变级叶片的装置，其具有多个枢转臂，同步环和用于将枢转臂枢转地附接到同步环的装置。 每个枢转臂包括用于与其中一个叶片固定连接的第一端。 同步环包括第一凸缘，第二凸缘，在凸缘之间延伸的腹板和布置在腹板中的多个开口。 用于将枢转臂枢轴连接到同步环的装置设置在开口内。