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：US07748209B1

公开(公告)日：2010-07-06

申请号：US11636273

申请日：2006-12-08

申请人： Cheryl A. Schopf ,  Jack W. Wilson, Jr. ,  Wesley Brown

发明人： Cheryl A. Schopf ,  Jack W. Wilson, Jr. ,  Wesley Brown

IPC分类号： F02C7/06

CPC分类号： F02C9/18 ,  F01D5/082 ,  F01D25/125 ,  F02C7/06 ,  F05D2260/201 ,  F05D2260/221 ,  F16C19/163 ,  F16C19/542 ,  F16C37/007 ,  Y02T50/671 ,  Y02T50/676

摘要： A small single use gas turbine engine with a twin spool rotor shaft and a bypass fan, the rotor shafts being supported for rotation by bearings in the front and rear compartments of the engine. A portion of the bypass fan air is diverted to flow through the bearings in order to provide for cooling of the high speed bearings. Because a large amount of cooling air is required to cool the bearings, an air in tube is positioned in each of the guide vanes in the turbine section to provide for a cooling air passage leading into the rear bearings. In the front bearings, cooling air from the bypass fan is bled off from a location just upstream from the entrance to the centrifugal compressor. A fuel mist tube supplies fuel mist to the cooling air before passing through the bearings to provide extra cooling for the bearings and to provide lubrication to improve the service life of the engine. Because the cooling air is supplied by the bypass fan, the pressure is high enough and the volume is large enough to provide adequate cooling for the high rotational speed bearings used in such a small and high rotating gas turbine engine.

摘要翻译： 具有双卷轴转子轴和旁通风扇的小型单次使用燃气涡轮发动机，转子轴由发动机的前后隔室中的轴承支撑以转动。 旁路风扇空气的一部分被转向流过轴承，以便提供高速轴承的冷却。 由于需要大量的冷却空气来冷却轴承，所以在涡轮机部分的每个导向叶片中定位管中的空气以提供通向后轴承的冷却空气通道。 在前轴承中，来自旁路风扇的冷却空气从入口到离心式压缩机的上游位置排出。 燃料雾管在通过轴承之前向冷却空气提供燃料雾以为轴承提供额外的冷却并提供润滑以提高发动机的使用寿命。 由于冷却空气由旁通风扇提供，所以压力足够高，并且体积足够大以为用于这种小型和高旋转燃气涡轮发动机的高转速轴承提供足够的冷却。

公开(公告)号：US07080971B2

公开(公告)日：2006-07-25

申请号：US10793641

申请日：2004-03-04

申请人： Jack W. Wilson ,  Wesley Brown

发明人： Jack W. Wilson ,  Wesley Brown

IPC分类号： F01O5/18

CPC分类号： F01D5/147 ,  F01D5/189 ,  F01D5/20 ,  Y10T29/49327 ,  Y10T29/49339 ,  Y10T29/49341

摘要： A blade for a rotor of a gas turbine engine is constructed with a spar and shell configuration. The spar is constructed in an integral unit or multi-portions and includes a first wall adjacent to the pressure side and a second wall adjacent to the suction side, a tip portion extending in the spanwise direction and extending beyond the first wall and the second wall and a root portion extending longitudinally, an attachment portion having a central opening for receiving the root portion and a platform portion. The root portion fits into the central opening and is secured therein by a pin extending transversely through the attachment and the root portion. The shell fits over the spar and is supported thereto by a plurality of complementary hooks extending from the spar and shell. The ends of the shell fit into grooves formed on the tip portion and the platform.

摘要翻译： 用于燃气涡轮发动机的转子的叶片由翼梁和壳体构造构成。 翼梁构造成整体单元或多部分，并且包括邻近压力侧的第一壁和邻近吸力侧的第二壁，尖端部分沿翼展方向延伸并且延伸超出第一壁和第二壁 和根部，其纵向延伸，具有用于接收根部的中心开口和平台部分的附接部分。 根部装配到中央开口中并且通过横向穿过附件和根部部分的销固定在其中。 壳体装配在翼梁上，并由多个从翼梁和壳体延伸的互补钩支撑在其上。 壳体的端部装配到形成在尖端部分和平台上的凹槽中。

公开(公告)号：US20070234733A1

公开(公告)日：2007-10-11

申请号：US11224906

申请日：2005-09-12

申请人： Mark Harris ,  Wesley Brown ,  Angel Garcia

发明人： Mark Harris ,  Wesley Brown ,  Angel Garcia

IPC分类号： F02C7/22

CPC分类号： F02C7/22 ,  F01D25/12 ,  F02C3/14 ,  F05D2250/80 ,  F23R3/38

摘要： A small gas turbine engine for use in an UAV such as a cruise missile, the gas turbine having a combustor forming a primary burn zone and a secondary burn zone, and in which fuel is injected into both the primary and the secondary burn zones by either a rotary cup injector or a plurality of fuel injector nozzles. The secondary burn zone with separate fuel injection allows for the diameter of the engine to be reduced in size but still allow for adequate power and efficiency to be reached for powering the vehicle. Air flow from the compressor is used to cool the combustor walls before being injected into the combustor, and to pass through and cool the guide nozzles and a main bearing located near the hot section of the combustor prior to being introduced into the combustor.

摘要翻译： 一种用于诸如巡航导弹的无人机的小型燃气涡轮发动机，燃气轮机具有形成初级燃烧区和次级燃烧区的燃烧器，其中通过以下任一方式将燃料喷射到主燃烧区域和次燃烧区域中 旋转杯喷射器或多个燃料喷射器喷嘴。 具有单独燃料喷射的二次燃烧区允许发动机的直径减小，但是仍然允许达到足够的动力和效率来为车辆供电。 来自压缩机的空气流被用于在被注入到燃烧器中之前冷却燃烧器壁，并且在引入燃烧器之前，使引导喷嘴和位于燃烧器的热部附近的主轴承通过并冷却。

公开(公告)号：US20060120869A1

公开(公告)日：2006-06-08

申请号：US10793641

申请日：2004-03-04

申请人： Jack Wilson ,  Wesley Brown

发明人： Jack Wilson ,  Wesley Brown

IPC分类号： F01D5/18

CPC分类号： F01D5/147 ,  F01D5/189 ,  F01D5/20 ,  Y10T29/49327 ,  Y10T29/49339 ,  Y10T29/49341

摘要： A blade for a rotor of a gas turbine engine is constructed with a spar and shell configuration. The spar is constructed in an integral unit or multi-portions and includes a first wall adjacent to the pressure side and a second wall adjacent to the suction side, a tip portion extending in the spanwise direction and extending beyond the first wall and the second wall and a root portion extending longitudinally, an attachment portion having a central opening for receiving the root portion and a platform portion. The root portion fits into the central opening and is secured therein by a pin extending transversely through the attachment and the root portion. The shell fits over the spar and is supported thereto by a plurality of complementary hooks extending from the spar and shell. The ends of the shell fit into grooves formed on the tip portion and the platform.

摘要翻译： 用于燃气涡轮发动机的转子的叶片由翼梁和壳体构造构成。 翼梁构造成整体单元或多部分，并且包括邻近压力侧的第一壁和邻近吸力侧的第二壁，尖端部分沿翼展方向延伸并且延伸超出第一壁和第二壁 和根部，其纵向延伸，具有用于接收根部的中心开口和平台部分的附接部分。 根部装配到中央开口中并且通过横向穿过附件和根部部分的销固定在其中。 壳体装配在翼梁上，并由多个从翼梁和壳体延伸的互补钩支撑在其上。 壳体的端部装配到形成在尖端部分和平台上的凹槽中。

公开(公告)号：US06983606B2

公开(公告)日：2006-01-10

申请号：US10657968

申请日：2003-09-09

申请人： Wesley Brown

发明人： Wesley Brown

IPC分类号： F02C7/22

CPC分类号： F23R3/38 ,  F02C7/22

摘要： An integrated gas turbine compressor and rotary fuel injector is provided which includes a rotary cup combustor having an atomizing element for dispersal and distribution of fuel throughout the combustor. The combustor is positioned in close proximity to the compressor impeller of a gas turbine engine having a centrifugal compressor. The rear face of the impeller, or the rear face of an attachment to the impeller, is contoured to receive the fuel supply. The contour terminates at a lip disposed at a larger radius from the centerline shaft than conventional shaft-mounted slingers. The larger radius of fuel release provides better fuel atomization due to larger rim speeds, thereby improving combustor performance.

摘要翻译： 提供了一种集成的燃气轮机压缩机和旋转燃料喷射器，其包括具有用于在整个燃烧器中分散和分配燃料的雾化元件的旋转杯式燃烧器。 燃烧器定位成紧邻具有离心式压缩机的燃气涡轮发动机的压缩机叶轮。 叶轮的后表面或与叶轮的附件的后表面成轮廓以接收燃料供应。 轮廓终止于与传统的轴安装的吊带相比，从中心轴设置的唇部更大的唇缘。 由于较大的轮辋速度，燃料释放的较大半径提供了更好的燃料雾化，从而提高了燃烧器性能。