公开(公告)号：US20110305580A1

公开(公告)日：2011-12-15

申请号：US13218798

申请日：2011-08-26

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

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

IPC: B64C27/46

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：US08070450B1

公开(公告)日：2011-12-06

申请号：US12426343

申请日：2009-04-20

Applicant: John E Ryznic ,  Wesley D Brown

Inventor： John E Ryznic ,  Wesley D Brown

IPC: F01D5/18

CPC classification number: F01D5/147 ,  F05D2300/13 ,  F05D2300/131

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：US08015705B2

公开(公告)日：2011-09-13

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: F01D5/18

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.

公开(公告)号：US08007242B1

公开(公告)日：2011-08-30

申请号：US12404742

申请日：2009-03-16

Applicant: Wesley D Brown ,  William L. Plank

Inventor： Wesley D Brown ,  William L. Plank

IPC: F01D5/18

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 is a thin wall shell made from a high temperature resistant material that is formed by a wire EDM process, and where the shell is secured to the spar using a retainer that is poured into retainer occupying spaces formed in the shell and the spar, and then hardened to form a rigid retainer to secure the shell to the spar. 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，其中壳体是由通过线材EDM工艺形成的耐高温材料制成的薄壁壳，并且其中壳体使用保持器固定到翼梁 倒入形成在壳体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壳固定到翼梁。 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：US20110020137A1

公开(公告)日：2011-01-27

申请号：US12876435

申请日：2010-09-07

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

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

IPC: F01D5/18

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 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. The shell is made from a high temperature resistant material, such as Molybdenum or Niobium, and is formed from a wire 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 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。 外壳由钼或铌等耐高温材料制成，并由电火花线切割加工工艺制成。

公开(公告)号：US20100229560A1

公开(公告)日：2010-09-16

申请号：US12487882

申请日：2009-06-19

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

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

IPC: F02C7/22

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。

公开(公告)号：US07758314B2

公开(公告)日：2010-07-20

申请号：US12355386

申请日：2009-01-16

Applicant: Jack W Wilson ,  Wesley D Brown

Inventor： Jack W Wilson ,  Wesley D Brown

IPC: F01D5/14

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：US4872810A

公开(公告)日：1989-10-10

申请号：US284269

申请日：1988-12-14

Applicant: Wesley D. Brown ,  Edward C. Hill ,  Peter T. Vercellone

Inventor： Wesley D. Brown ,  Edward C. Hill ,  Peter T. Vercellone

IPC: F01D5/22 ,  F01D5/30 ,  F01D5/32 ,  F01D11/00

CPC classification number: F01D5/3015 ,  F01D11/006 ,  F01D5/22 ,  Y02T50/672 ,  Y02T50/673 ,  Y10S416/50

Abstract: Damping of a turbine rotor is attained by a weighted member trapped between pockets formed in the neck of adjacent blades at one end and a space between the disk and TOBI rotor seal and forward extending blade lug at the other end. The feather seal which is a curved plate fits over the top of the weighted member and is trapped between nubs formed on the front and rear underside of the blade platform. The front face of the rim of the disk at the disk cavity is open ended and blocked off at the rear face. This assembly allows for individual blade removal and viewing from the rear face by removing a single rim cavity cover without disturbing the remaining components of the assembly. The inverted ring supports take up the axial loads alleviating the loads heretofore taken up by the TOBI rotor seal, allowing for a lighter weight installation.

公开(公告)号：US08382439B1

公开(公告)日：2013-02-26

申请号：US13244335

申请日：2011-09-24

Applicant: Wesley D Brown

Inventor： Wesley D Brown

IPC: B23K5/18

CPC classification number: F01D5/188 ,  F01D5/147 ,  Y10T29/49341 ,  Y10T29/49343

Abstract: A turbine rotor blade made from the spar and shell construction in which the shell is a thin wall shell made from a high temperature resistant material that is formed by a wire EDM process, and where the shell is secured to the spar using a retainer that is poured into retainer occupying spaces formed in the shell and the spar, and then hardened to form a rigid retainer to secure the shell to the spar. The spar and the shell both have grooves facing each other to form a retainer groove. A retaining material, such as a liquid or a powdered metal, is poured into the grooves and hardened to form a retainer to secure the shell to the spar. The retaining material also forms a seal on the top of the spar and between the spar and shell.

Abstract translation: 一种由翼梁和壳体结构制成的涡轮转子叶片，其中壳体是由通过线材EDM工艺形成的耐高温材料制成的薄壁壳，并且其中壳体使用保持器固定到翼梁 倒入形成在壳体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壳固定到翼梁。 翼梁和壳体都具有彼此面对的槽以形成保持器槽。 将诸如液体或粉末金属的保持材料倒入槽中并硬化以形成保持器以将壳固定到翼梁。 保持材料也在翼梁的顶部和翼梁和壳体之间形成密封。

公开(公告)号：US08196407B2

公开(公告)日：2012-06-12

申请号：US12487882

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: 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.