公开(公告)号：US07762781B1

公开(公告)日：2010-07-27

申请号：US11715042

申请日：2007-03-06

申请人： Wesley Brown ,  Alfred P. Matheny

发明人： Wesley Brown ,  Alfred P. Matheny

IPC分类号： F01D5/30

CPC分类号： F01D5/147 ,  F01D9/042 ,  F05D2300/607

摘要： A turbine blade and platform assembly in which the platform is a separate piece that is secured to the blade through shear pins that extend along slots formed between opposed abutting parts of the blade and the platform. Because the platform is detached from the blade, the blade can be made of a single crystal superalloy with a reduction in casting defects. The platform has one or more airfoil shaped openings or slots on the outer surface in which a blade is inserted. The shear pins are inserted to secure the platform to the blade. In another embodiment, the blade root is inserted into an opening formed in the rotor disk, and shear pins are inserted into slots formed in the root and the disk opening in order to secure the blade to the rotor disk. With this embodiment, the blade can be made of a ceramic material because only compressive forces are formed to hold the blade in place.

摘要翻译： 一种涡轮机叶片和平台组件，其中平台是通过剪切销固定到叶片的分离件，该剪切销沿着形成在叶片的相对的邻接部分和平台之间的槽延伸。 因为平台与刀片分离，所以刀片可以由单晶超合金制成，铸造缺陷减少。 平台在外表面上具有一个或多个翼型形状的开口或狭槽，其中插入有叶片。 插入剪切销以将平台固定到叶片上。 在另一个实施例中，叶片根部插入形成在转子盘中的开口中，并且剪切销插入形成在根部和盘开口中的槽中，以将叶片固定到转子盘上。 利用该实施例，刀片可以由陶瓷材料制成，因为仅形成压缩力来将刀片保持在适当位置。

公开(公告)号：US07445426B1

公开(公告)日：2008-11-04

申请号：US11255129

申请日：2005-10-20

申请人： Alfred P. Matheny ,  John N. Keune

发明人： Alfred P. Matheny ,  John N. Keune

IPC分类号： F01D9/00

CPC分类号： F01D25/246 ,  F01D9/042 ,  F04D29/542

摘要： A compressor includes a stator having a plurality of vane sectors each with an outer shroud having a forward and a rearward guide vane extending there form, the vane sector being mounted in an annular slot of the casing, the guide vanes forming a gap between the tips and an inner shroud, and a spring member located on the outer shroud in the rearward portion to bias the rearward shroud in a radial direction, where a space is formed in the slot to allow for the outer shroud to move in the radial direction when the rearward guide vane tip makes contact with the inner shroud due to thermal growth of the stator components. This arrangement allows for the rearward guide vane tip to maintain contact with the inner shroud without inducing high compressive stresses in the stator components due to the thermal growth.

摘要翻译： 压缩机包括具有多个叶片部分的定子，每个叶片部分均具有外部护罩，该外部护罩具有在形式上延伸的前部和后部引导叶片，叶片部分安装在壳体的环形槽中，导向叶片在尖端之间形成间隙 内护罩，以及弹簧构件，其位于后部的外护罩上，以在径向方向上偏置后护罩，其中在狭槽中形成空间，以允许外护罩在径向方向上移动 由于定子部件的热量增长，后导向叶片尖端与内罩接触。 这种布置允许后导向叶片尖端保持与内护罩的接触，而不会由于热生长而引起定子部件中的高压缩应力。

公开(公告)号：US5482433A

公开(公告)日：1996-01-09

申请号：US372718

申请日：1995-01-13

申请人： James W. Norris ,  Alfred P. Matheny

发明人： James W. Norris ,  Alfred P. Matheny

IPC分类号： F01D5/22 ,  F01D9/04

CPC分类号： F01D9/041 ,  F01D5/22 ,  F01D9/044 ,  Y02T50/672

摘要： The inner shroud of the vane of a vane assembly for the compressor section of a gas turbine engine is fabricate from a composite material preferably imide resin reinforced with carbon fibers and is formed into an open ended box-like member segment supporting no less than two vanes or airfoils. The segments are interlocked by a necked down edge adapted to slip into the open end of the adjacent inner shroud of the stator vane that serve to seal the gas path and provide damping. Rub strips are integrally formed on the bottom surface of the inner shroud.

摘要翻译： 用于燃气涡轮发动机的压缩机部分的叶片组件的叶片的内护罩由复合材料制成，优选地由碳纤维增强的酰亚胺树脂制成，并且形成为支撑不少于两个叶片的开口的盒状构件段 或翼型。 这些段由缩颈边缘互锁，适合于滑入定子叶片的相邻内护罩的开口端，用于密封气体通道并提供阻尼。 擦拭条一体地形成在内护罩的底表面上。

公开(公告)号：US07704044B1

公开(公告)日：2010-04-27

申请号：US11605857

申请日：2006-11-28

申请人： Alfred P. Matheny

发明人： Alfred P. Matheny

IPC分类号： F01D5/30

CPC分类号： F01D5/147 ,  F01D5/3023

摘要： A rotor disc and rotor blade assembly in which the rotor blades include curved shear pins to secure the blade to the rotor disc. The blade includes an airfoil portion with an airfoil outline shape at the junction of the airfoil with the platform, and the root extends below the platform and has the general shape of the airfoil at the junction. An opening in the rotor disc also has the shape of the airfoil outline such that the root will fit snuggly within the opening in the rotor disc. Curved slots in both the opening and the root wall are formed on both sides of the opening and the blade root. Shear pins having a rectangular cross sectional shape fit within the slots to secure the blade to the disc. Because the root curvature follows the airfoil shape, the shear pins are located below the airfoil walls and absorb the shear stress caused by bending forces acting on the airfoil from the fluid reaction.

摘要翻译： 转子盘和转子叶片组件，其中转子叶片包括用于将叶片固定到转子盘的弯曲剪切销。 叶片包括在机翼与平台的接合部处具有翼型轮廓形状的翼型部分，并且根部在平台下方延伸并且具有在接合处的翼型的一般形状。 转子盘中的开口也具有翼型轮廓的形状，使得根部将紧密地配合在转子盘的开口内。 开口和根壁上的弯曲槽形成在开口和叶根的两侧。 具有矩形横截面形状的剪切销配合在槽内以将刀片固定到盘上。 由于根曲率遵循翼型形状，剪切销位于翼型壁的下方，并吸收由流体反应作用在翼型上的弯曲力引起的剪切应力。

公开(公告)号：US07658063B1

公开(公告)日：2010-02-09

申请号：US11437486

申请日：2006-05-20

申请人： Alfred P. Matheny

发明人： Alfred P. Matheny

IPC分类号： F02K1/38

CPC分类号： F02K3/077 ,  F01D9/041 ,  F02K1/34 ,  F02K3/02 ,  F02K3/04 ,  F05D2260/20 ,  F05D2260/96 ,  Y02T50/676

摘要： A gas turbine engine used in an aircraft includes a fan to provide a bypass flow through the engine. The fan delivers some airflow to the compressor for compression, and a fuel is mixed with the compressed air and delivered to a turbine to drive the engine and compressor and fan. The fan also delivers airflow to a central bypass passage located inward of the compressor. Guide vanes both upstream and downstream of the combustor each with cooling air passages therein, pass the bypass airflow from the inner bypass passage into an outer bypass passage located outward of the combustor and the turbine. The bypass flow through the guide vanes also cool the guide vanes and pass over and around the combustor to cool the combustor. The bypass airflow exits the engine at a location outward of the hot gas flow from the turbine. In an alternative embodiment, an inner bypass passage located inward of the central bypass passage also carries bypass airflow from the fan and through the engine to be mixed with the hot gas flow and the outward bypass flow.

摘要翻译： 在飞行器中使用的燃气涡轮发动机包括用于提供通过发动机的旁路流的风扇。 风扇向压缩机提供一些气流以进行压缩，并且燃料与压缩空气混合并输送到涡轮以驱动发动机和压缩机和风扇。 风扇还向位于压缩机内侧的中央旁路通道提供气流。 在燃烧器的上游和下游的导向叶片各自具有冷却空气通道，将旁路气流从内部旁路通道传递到位于燃烧器和涡轮机外部的外部旁路通道中。 通过引导叶片的旁路流还使引导叶片冷却并且在燃烧器周围并且绕过燃烧器以冷却燃烧器。 旁路气流在来自涡轮机的热气流的外部的位置处离开发动机。 在替代实施例中，位于中央旁路通道内侧的内部旁路通道还带有来自风扇和通过发动机的旁路气流，以与热气流和向外旁路流混合。

公开(公告)号：US06206642B1

公开(公告)日：2001-03-27

申请号：US09213696

申请日：1998-12-17

申请人： Alfred P. Matheny ,  Richard A. Holmes ,  Wendell V. Twelves, Jr.

发明人： Alfred P. Matheny ,  Richard A. Holmes ,  Wendell V. Twelves, Jr.

IPC分类号： F01D514

CPC分类号： F04D29/324 ,  F01D5/147 ,  F01D5/20 ,  F04D29/164 ,  F05D2300/501

摘要： A compressor blade that has a blade root, an airfoil having a first end, and a second end opposite the first end, the second end having at least one edge, and the airfoil is made of a first material having a first modulus of elasticity. A blade platform connects the blade root to the first end of the airfoil, and a flexible seal is connected to the airfoil adjacent the second end, and the seal is made of a second material having a modulus of elasticity that is substantially less than the first modulus of elasticity.

摘要翻译： 一种具有叶片根部的压缩机叶片，具有第一端的翼型和与第一端相对的第二端，所述第二端具有至少一个边缘，并且所述翼型由具有第一弹性模量的第一材料制成。 叶片平台将叶片根部连接到翼型件的第一端，并且柔性密封件连接到邻近第二端的翼型件，并且密封件由第二材料制成，该第二材料的弹性模量基本上小于第一 弹性模量。

公开(公告)号：US07780420B1

公开(公告)日：2010-08-24

申请号：US11600455

申请日：2006-11-16

申请人： Alfred P. Matheny

发明人： Alfred P. Matheny

IPC分类号： F01D5/14

CPC分类号： F01D5/14 ,  F01D5/282 ,  F04D29/324 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2300/603 ,  F05D2300/612 ,  Y02T50/672

摘要： A thin compressor blade used in a small aircraft gas turbine engine, in which the blade includes a main blade portion formed from a fiber reinforced resinous composite material to provide a lightweight and strong blade, and in which the leading edge or the trailing edge of the blade is formed from a foam metal reinforced composite material that defines a sharp edge for improved performance of the thin blade. The fibers of the main body extend into the edge region in order that the resin used to bind the foam metal will also bind with the fibers of the laminates to secure the edge to the main blade body. The blade tip can also be formed from the porous foam metal and resin material to make a strong and lightweight rotor blade.

摘要翻译： 一种用于小型飞机燃气涡轮发动机中的薄压缩机叶片，其中叶片包括由纤维增强树脂复合材料形成的主叶片部分，以提供轻质且坚固的叶片，并且其中的前缘或后缘 叶片由泡沫金属增强复合材料形成，该复合材料限定了锋利的边缘以改善薄叶片的性能。 主体的纤维延伸到边缘区域，以便用于结合泡沫金属的树脂也将与层压板的纤维结合，以将边缘固定到主叶片本体。 叶片尖端还可以由多孔泡沫金属和树脂材料形成，以制造强而轻的转子叶片。

公开(公告)号：US07780419B1

公开(公告)日：2010-08-24

申请号：US11715044

申请日：2007-03-06

申请人： Alfred P. Matheny ,  Edwin L. Kite

发明人： Alfred P. Matheny ,  Edwin L. Kite

IPC分类号： F01D5/30

CPC分类号： F01D5/34 ,  F01D5/005 ,  F04D29/023 ,  F04D29/324 ,  F05D2230/64 ,  F05D2240/121 ,  F05D2240/303 ,  F05D2300/133 ,  F05D2300/603 ,  Y02T50/672 ,  Y02T50/673

摘要： A compressor blade for a gas turbine engine that includes a composite leading edge insert attached to a titanium blade by a row of fastener pins along an aft edge of the insert to prevent unzipping. Each insert is also secured by an electrochemically disbondable composition for easy removable of a damaged insert from an integrally bladed disk. One or more of the fastener pins provides for an electrical conductive path that bypasses the disbondable composition during a lightening strike so that the insert does not release. Each replaceable insert includes a root portion that fits within a slot of the rotor disk, with each insert being secured against radial displacement by two shear pins secured within two shear pin slots formed in both the insert root portion and the rotor disk slot. The shear pin slots are curved and follow the curvature of the airfoil at the junction to the rotor disk. A retaining and balancing ring is secured within an annular groove and functions to retain the shear pins within the slots and to balance the rotor disk. The combination of the fastener pins, the electrochemically disbondable composition, and the shear pins in the slot provide for three methods of securing an insert to the blade so that a damaged insert can be easily replaced.

摘要翻译： 一种用于燃气涡轮发动机的压缩机叶片，其包括通过一排紧固件销沿着插入件的后边缘附接到钛刀片的复合前缘插入件，以防止解锁。 每个插入物也通过电化学脱粘组合物固定，以便容易地从一体式叶片的盘中移除损坏的插入物。 一个或多个紧固销提供了在减轻击打期间绕过不可分散组合物的导电路径，使得插入物不释放。 每个可替换的插入件包括装配在转子盘的槽内的根部，每个插入件通过固定在形成在插入件根部和转子盘槽中的两个剪切销槽内的两个剪切销抵抗径向位移。 剪切销槽是弯曲的，并且在与转子盘的连接处跟随翼型的曲率。 保持和平衡环固定在环形槽内，并且用于将剪切销保持在槽内并平衡转子盘。 紧固件销钉，电化学脱粘组合物和槽中的剪切销的组合提供了将插入件固定到刀片上的三种方法，使得可以容易地更换损坏的刀片。

公开(公告)号：US07401981B2

公开(公告)日：2008-07-22

申请号：US11234503

申请日：2005-09-23

申请人： Alfred P. Matheny

发明人： Alfred P. Matheny

IPC分类号： F16C27/04 ,  F16C33/58

CPC分类号： F16C27/04 ,  F16C19/06 ,  F16C33/586 ,  F16C35/077 ,  F16C2300/02

摘要： A bearing damper includes a coiled wire wrapped around projections formed on an outer race of the bearing, and supported by a casing having projections extending toward the coiled wire. Projections on the outer race are aligned with recesses on the casing, while projections on the casing are aligned with recesses in the outer race so that the coiled wire can flex between the projections that support the wire and provide a damping function. The coiled wire is formed of a plurality of strands. Flexing of the wire causes adjacent strands to rub and dissipate energy from the vibrations. The tension in the coiled wire can be adjusted in order to vary the damping capability of the bearing damper.

摘要翻译： 轴承阻尼器包括卷绕在形成在轴承的外圈上的突起的螺旋线，并且由具有朝向螺旋线延伸的突起的壳体支撑。 外圈上的突出部与壳体上的凹槽对准，而壳体上的突起与外座圈中的凹槽对准，使得线圈线可在支撑线材的突起之间弯曲并提供阻尼功能。 螺旋线由多根股线构成。 导线的弯曲会使相邻的线材从振动中摩擦和耗散能量。 为了改变轴承阻尼器的阻尼能力，可以调节盘绕线中的张力。

公开(公告)号：US4864828A

公开(公告)日：1989-09-12

申请号：US187762

申请日：1988-04-29

申请人： Alfred P. Matheny ,  Thomas A. Auxier

发明人： Alfred P. Matheny ,  Thomas A. Auxier

IPC分类号： F23R3/08

CPC分类号： F23R3/08 ,  Y02T50/675

摘要： Aircraft engine cooling apparatus having a plurality of cooling gas inlet nozzles, producing first streams of cooling gas moving in a forward direction, a plurality of first direction reversal members for splitting the first streams into second and third streams straddling the nozzles, and substantially reversed in direction relative to the direction of the first streams, a plurality of second direction reversal members, positioned between pairs of adjacent nozzles, for again substantially reversing the directions of the second and third streams, while combining the second and third streams to form a fourth stream of laminar flow cooling film, and wherein adjacent pairs of the first direction reversal members have wall portions configured to form gradually diverging channels through which the fourth stream cooling film moves.

摘要翻译： 具有多个冷却气体入口喷嘴的飞机发动机冷却装置，产生沿向前方向移动的冷却气体的第一流;多个第一方向反转构件，用于将第一流分离成跨过喷嘴的第二和第三流， 相对于第一流的方向的多个第二方向反转构件，位于相邻喷嘴对之间的多个第二方向反转构件，用于再次大体上反转第二和第三流的方向，同时组合第二和第三流以形成第四流 层流冷却膜，并且其中相邻的第一方向反转构件对具有壁部，其被配置为形成逐渐发散的通道，第四流冷却膜通过该通道移动。