公开(公告)号：US08336206B1

公开(公告)日：2012-12-25

申请号：US13157364

申请日：2011-06-10

Applicant: Wesley D Brown ,  William L Plank

Inventor： Wesley D Brown ,  William L Plank

IPC: B21D53/78 ,  B63H1/26

CPC classification number: F01D5/28 ,  F01D5/18 ,  Y10T29/49332 ,  Y10T29/49336 ,  Y10T29/49337

Abstract: A turbine rotor blade made from the spar and shell construction in which the shell formed from a plurality of shell segments each being a thin wall shell segment made from a high temperature resistant material that is formed by a wire EDM process, and where the shell segments are each secured to the spar separately using a retainer that is poured into retainer occupying spaces formed in the shell segments and the spar, and then hardened to form a rigid retainer to secure each shell segment to the spar individually. The spar includes a number of radial extending projections each with a row of cavities that form the retainer occupying spaces in order to spread the loads around. The retainer can be a bicast material, a transient liquid phase bonding material, or a sintered metal. An old shell can be easily removed and replaced with a new shell by removing parts of the retainer and re-pouring a new retainer with a new shell in place.

Abstract translation: 一种由翼梁和壳体结构制成的涡轮转子叶片，其中壳体由多个壳段形成，每个壳段均由由电线EDM工艺形成的耐高温材料制成的薄壁壳段，并且其中壳段 各自使用保持器分别固定到翼梁上，该保持器被注入到形成在壳段和翼梁中的保持器占据空间中，然后硬化以形成刚性保持器，以将每个壳段单独地固定到翼梁。 翼梁包括多个径向延伸的突起，每个具有一排空腔，形成保持器占据空间，以便使负载周围扩展。 保持器可以是组播材料，瞬态液相粘合材料或烧结金属。 可以通过移除保持器的部件并将新的保持器重新装入新的壳体中，可以容易地移除旧壳体并用新的壳体代替。

公开(公告)号：US07874804B1

公开(公告)日：2011-01-25

申请号：US11801594

申请日：2007-05-10

Applicant: Wesley D. Brown

Inventor： Wesley D. Brown

IPC: F01D5/30

CPC classification number: F01D5/3007 ,  F05D2230/50 ,  F05D2240/80 ,  F05D2260/36 ,  F05D2260/94 ,  F05D2260/941

Abstract: A turbine blade with a detached platform in which the platform has a central opening in which the blade is inserted and held in place. The blade includes a root portion with a fir tree configuration to fit within a slot of a rotor disc. The platform includes two legs that also have a fir tree configuration to fit within the slot of the rotor disc. The blade is inserted into the central opening and the fir tree configurations of the blade root and the platform legs form substantially an aligned set of fir trees that fit within the rotor disc slot to retain both the blade and the platform within the slot. The blade is therefore separated from the platform such that thermal stresses are uncoupled. Also, the blade can be made from a different material than is the platform. The centrifugal load applied to the platform is not transferred onto the blade.

Abstract translation: 具有分离平台的涡轮机叶片，其中平台具有中心开口，叶片插入并保持在其中。 叶片包括具有杉木构造的根部，以配合在转子盘的槽内。 该平台包括两条腿，它们也具有杉木结构以配合在转子盘的槽内。 刀片插入中央开口，并且叶片根部和平台腿部的杉木构造基本上形成一组适配于转子盘槽内的对准的冷杉树，以将叶片和平台保持在槽内。 因此，刀片与平台分离，使得热应力解耦。 此外，刀片可以由与平台不同的材料制成。 施加到平台的离心负荷不会转移到叶片上。

公开(公告)号：US20100290917A1

公开(公告)日：2010-11-18

申请号：US12843935

申请日：2010-07-27

Applicant: Jack W. Wilson, JR. ,  Wesley D. Brown

Inventor： Jack W. Wilson, JR. ,  Wesley D. Brown

IPC: F04D29/38

CPC classification number: F01D5/147 ,  F01D5/189 ,  F01D5/20 ,  Y10T29/49327 ,  Y10T29/49339 ,  Y10T29/49341

Abstract: A turbine rotor blade with a spar and shell construction, where the shell has an airfoil shape and is formed of two shell segments with an upper shell half and a lower shell half. The upper shell half is radially supported by a tip of the spar while the lower shell half is radially loaded by an attachment so that its load is not carried by the upper shell half and the tip of the spar in order to reduce overall stress levels.

Abstract translation: 具有翼梁和壳结构的涡轮转子叶片，其中壳体具有翼型形状，并且由具有上壳体半壳体和下半壳体的两个壳段形成。 上壳体半部由翼片的尖端径向地支撑，而下壳体半部通过附件径向地加载，使得其负载不被上半壳体和翼梁的末端承载，以便降低总的应力水平。

公开(公告)号：US20090193657A1

公开(公告)日：2009-08-06

申请号：US12355353

申请日：2009-01-16

Applicant: Jack W. Wilson, JR. ,  Wesley D. Brown

Inventor： Jack W. Wilson, JR. ,  Wesley D. Brown

IPC: B23P15/02 ,  B23K9/00

CPC classification number: F01D5/147 ,  F01D5/189 ,  F01D5/20 ,  Y10T29/49327 ,  Y10T29/49339 ,  Y10T29/49341

Abstract: The present invention is a vane for us in a gas turbine engine, in which the vane is made of an exotic, high temperature material that is difficult to machine or cast. The vane includes a shell made from either Molybdenum, Niobium, alloys of Molybdenum or Niobium (Columbium), Oxide Ceramic Matrix Composite (CMC), or SiC-SiC ceramic matrix composite, and is formed from a wire electric discharge process. The shell is positioned in grooves between the outer and inner shrouds, and includes a central passageway within the spar, and forms a cooling fluid passageway between the spar and the shell. Both the spar and the shell include cooling holes to carry cooling fluid from the central passageway to an outer surface of the vane for cooling. This cooling path eliminates a serpentine pathway, and therefore requires less pressure and less amounts of cooling fluid to cool the vane.

Abstract translation: 本发明是一种用于燃气涡轮发动机的叶片，其中叶片由难以加工或铸造的外来高温材料制成。 叶片包括由钼，铌，钼或铌（铌），氧化物陶瓷基复合材料（CMC）或SiC-SiC陶瓷基体复合材料制成的壳体，并由导线放电工艺形成。 壳体定位在外护罩之间的凹槽中，并且在翼梁内部包括中心通道，并且在翼梁和壳体之间形成冷却流体通道。 翼梁和壳都包括冷却孔，以将冷却流体从中心通道运送到叶片的外表面用于冷却。 该冷却路径消除了蛇形通道，因此需要较少的压力和较少量的冷却流体来冷却叶片。

公开(公告)号：US20090169395A1

公开(公告)日：2009-07-02

申请号：US12355386

申请日：2009-01-16

Applicant: Jack W. Wilson, JR. ,  Wesley D. Brown

Inventor： Jack W. Wilson, JR. ,  Wesley D. Brown

IPC: F01D5/18

CPC classification number: F01D5/28 ,  F05D2300/13

Abstract: The present invention is a vane for us in a gas turbine engine, in which the vane is made of an exotic, high temperature material that is difficult to machine or cast. The vane includes a shell made from Tungsten, and is formed from a wire electric discharge process. The shell is positioned in grooves between the outer and inner shrouds, and includes a central passageway within the spar, and forms a cooling fluid passageway between the spar and the shell. Both the spar and the shell include cooling holes to carry cooling fluid from the central passageway to an outer surface of the vane for cooling. This cooling path eliminates a serpentine pathway, and therefore requires less pressure and less amounts of cooling fluid to cool the vane.

Abstract translation: 本发明是一种用于燃气涡轮发动机的叶片，其中叶片由难以加工或铸造的外来高温材料制成。 叶片包括由钨制成的壳体，并且由电线放电过程形成。 壳体定位在外护罩之间的凹槽中，并且在翼梁内部包括中心通道，并且在翼梁和壳体之间形成冷却流体通道。 翼梁和壳都包括冷却孔，以将冷却流体从中心通道运送到叶片的外表面用于冷却。 该冷却路径消除了蛇形通道，因此需要较少的压力和较少量的冷却流体来冷却叶片。

公开(公告)号：US20080260538A1

公开(公告)日：2008-10-23

申请号：US12146816

申请日：2008-06-26

Applicant: Jack W. Wilson ,  Wesley D. Brown

Inventor： Jack W. Wilson ,  Wesley D. Brown

IPC: F01D5/18 ,  F01D5/14

CPC classification number: F01D5/147 ,  F01D5/189 ,  F01D5/20 ,  Y10T29/49327 ,  Y10T29/49339 ,  Y10T29/49341

Abstract: 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 foot 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 foot 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, The shell is made from a high temperature resistant material, such as Molybdenum or Niobium, and is formed from a wife EDM process.

Abstract translation: 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 以及纵向延伸的根部，具有用于接收所述脚部的中心开口和平台部分的附接部分。 根部装配到中心开口中并且通过横向穿过附件和脚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。 壳体的端部装配在尖端部分和平台上形成的凹槽中。壳体由诸如钼或铌的耐高温材料制成，并且由妻子EDM工艺形成。

公开(公告)号：US08475112B1

公开(公告)日：2013-07-02

申请号：US13526601

申请日：2012-06-19

Applicant: John E Ryznic ,  Wesley D Brown

Inventor： John E Ryznic ,  Wesley D Brown

IPC: F01D5/14 ,  F03B11/00 ,  F03D11/00 ,  F04D29/38

CPC classification number: F02C6/08 ,  F02C7/18 ,  F04D29/324 ,  F04D29/542 ,  F04D29/5826 ,  F04D29/584 ,  F05D2260/205 ,  F05D2260/208 ,  Y02T50/676

Abstract: A high compression ratio compressor having multiple stages of airfoils to produce the high pressure rations, where the last stage airfoils are cooled by drawing heat away from the airfoils using a heat pipe, and then passing cooling air through a heat exchanger associated with the heat pipe to draw heat away from the heat pipe. The cooling air used for cooling the airfoils is bled off from an earlier stage than the last stage and then discharged into a stage upstream from the bleed off location.

Abstract translation: 具有多级翼型件以产生高压口径的高压缩比压缩机，其中最后一级机翼通过使用热管从翼型件中抽出热而冷却，然后使冷却空气通过与热管相关联的热交换器 将热量从热管中吸走。 用于冷却翼型的冷却空气从比最后阶段更早的阶段排出，然后排放到排放位置上游的阶段。

公开(公告)号：US07997057B1

公开(公告)日：2011-08-16

申请号：US12487903

申请日：2009-06-19

Applicant: Mark M. Harris ,  Wesley D. Brown ,  Angel M. Garcie

Inventor： Mark M. Harris ,  Wesley D. Brown ,  Angel M. Garcie

IPC: F02C7/06 ,  F16C19/50

CPC classification number: F01D25/162 ,  F01D25/125 ,  F02C7/06 ,  F16C19/163 ,  F16C33/58 ,  F16C37/007 ,  Y10S384/90

Abstract: A small gas turbine engine where the compressor and turbine are supported on a rotary shaft, and a main bearing is supported on the rotary shaft, the main bearing being located in a hot zone of the combustor. The main bearing includes cooling air passages within the races to provide cooling for the bearing. A cooling air is diverted from the compressor and passed through the bearing cooling passages for cooling the bearing, and then the cooling air is directed into the combustor. The cooling air is also passed through a guide nozzle before being passed through the bearing to cool both the guide nozzle and the bearing. A swirl cup injector is used to deliver the compressed air from the compressor and the cooling air from the bearing into the combustor, the swirl cup injector also acting to draw the cooling air through the bearing.

Abstract translation: 一种小型燃气轮机，其中压缩机和涡轮机支撑在旋转轴上，主轴承支撑在旋转轴上，主轴承位于燃烧器的热区中。 主轴承包括座圈内的冷却空气通道，为轴承提供冷却。 冷却空气从压缩机转向并通过轴承冷却通道以冷却轴承，然后冷却空气被引导到燃烧器中。 冷却空气在通过轴承之前也通过引导喷嘴，以冷却引导喷嘴和轴承。 涡旋杯喷射器用于将来自压缩机的压缩空气和来自轴承的冷却空气输送到燃烧器中，旋转杯喷射器还用于将冷却空气抽吸通过轴承。

公开(公告)号：US07942009B1

公开(公告)日：2011-05-17

申请号：US12484503

申请日：2009-06-15

Applicant: Mark M Harris ,  Wesley D Brown ,  Angel M Garcia

Inventor： Mark M Harris ,  Wesley D Brown ,  Angel M Garcia

IPC: F02C6/08 ,  F02C7/12

CPC classification number: F01D25/162 ,  F01D25/125 ,  F02C7/06 ,  F16C19/163 ,  F16C33/58 ,  F16C37/007 ,  Y10S384/90

Abstract: A small gas turbine engine with a compressor, a combustor, and a turbine located downstream of the combustor. The compressor and turbine are supported on a rotary shaft, and a main bearing is support on the rotary shaft, the main bearing being located in a hot zone of the combustor. The main bearing includes cooling air passages within the races to provide cooling for the bearing. A cooling air is diverted from the compressor and passed through the bearing cooling passages for cooling the bearing, and then the cooling air is directed into the combustor. The cooling air is also passed through a guide nozzle before being passed through the bearing to cool both the guide nozzle and the bearing. A swirl cup injector is sued to deliver the compressed air from the compressor and the cooling air from the bearing into the combustor, the swirl cup injector also acting to draw the cooling air through the bearing.

Abstract translation: 具有位于燃烧器下游的压缩机，燃烧器和涡轮的小型燃气涡轮发动机。 压缩机和涡轮机支撑在旋转轴上，主轴承支撑在旋转轴上，主轴承位于燃烧器的热区中。 主轴承包括座圈内的冷却空气通道，为轴承提供冷却。 冷却空气从压缩机转向并通过轴承冷却通道以冷却轴承，然后冷却空气被引导到燃烧器中。 冷却空气在通过轴承之前也通过引导喷嘴，以冷却引导喷嘴和轴承。 涡旋杯喷射器被起动以将来自压缩机的压缩空气和来自轴承的冷却空气输送到燃烧器中，旋转杯喷射器还用于将冷却空气抽吸通过轴承。

公开(公告)号：US07568343B2

公开(公告)日：2009-08-04

申请号：US11224906

申请日：2005-09-12

Applicant: Mark M. Harris ,  Wesley D. Brown ,  Angel M. Garcia

Inventor： Mark M. Harris ,  Wesley D. Brown ,  Angel M. Garcia

IPC: F02C3/00

CPC classification number: F02C7/22 ,  F01D25/12 ,  F02C3/14 ,  F05D2250/80 ,  F23R3/38

Abstract: 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.

Abstract translation: 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。