公开(公告)号：US20100284794A1

公开(公告)日：2010-11-11

申请号：US11975674

申请日：2007-10-19

Applicant: Ryan C. McMahon ,  Jack W. Wilson, JR.

Inventor： Ryan C. McMahon ,  Jack W. Wilson, JR.

IPC: F01D11/00 ,  F01D1/24 ,  F01D5/08 ,  F01D5/02 ,  B23P15/04

CPC classification number: F01D5/026 ,  F16C3/023 ,  F16C2360/23 ,  Y02T50/671 ,  Y10S29/013 ,  Y10T29/4932

Abstract: A low pressure turbine rotor disk for a small twin spool gas turbine engine in which the rotor disk includes a forward side cavity large enough to allow for the bearing assembly that rotatably supports the rotor disk to fit within the cavity in order to shorten the axial distance between the bearings that support the inner rotor shaft on which the turbine rotor disk is secured. Minimizing the bearings spacing allows for a high critical speed for the inner rotor shaft and therefore allows for the small twin spool gas turbine engine to operate at this small scale. The turbine rotor disk also includes a plurality of axial aligned cooling air holes to allow for cooling air from the bearings to flow out from the aft end of the rotor disk. The inner surface of the cavity is an annular surface that forms a seal with knife edges extending outward from the bearing support plate also located within the cavity. The rotor disk includes an annular groove facing outward and on the rear side of the disk to allow for a tool to be inserted for removing the rotor disk from the shaft. An axial central opening in the rotor disk allows for insertion of the shaft and is formed with a bearing race abutment surface on the forward side and a nut abutment surface of the aft side used to compress the rotor disk assembly on the inner rotor shaft.

Abstract translation: 一种用于小型双卷轴燃气涡轮发动机的低压涡轮转子盘，其中转子盘包括足够大的前侧腔，以允许可旋转地支撑转子盘以装配在腔内的轴承组件，以缩短轴向距离 在支撑涡轮转子盘固定在其上的内转子轴之间。 最小化轴承间距允许内转子轴的高临界转速，从而允许小双轴卷烟机涡轮发动机以小规模运行。 涡轮转子盘还包括多个轴向排列的冷却空气孔，以允许冷却来自轴承的空气从转子盘的后端流出。 空腔的内表面是形成密封件的环形表面，刀片边缘也从也位于腔体内的轴承支撑板向外延伸。 转子盘包括面向盘的外侧和后侧的环形槽，以允许插入工具以将转子盘从轴上移除。 转子盘中的轴向中心开口允许轴插入，并且在前侧形成有轴承座抵接表面，并且在后侧形成用于压缩内转子轴上的转子盘组件的螺母邻接表面。

公开(公告)号：US20090031732A1

公开(公告)日：2009-02-05

申请号：US11975671

申请日：2007-10-19

Applicant: Jack W. Wilson, JR. ,  Robert E. deLaneuville ,  Paul E. Orndoff ,  Ryan C. McMahon

Inventor： Jack W. Wilson, JR. ,  Robert E. deLaneuville ,  Paul E. Orndoff ,  Ryan C. McMahon

IPC: F02C3/10 ,  F16C3/02

CPC classification number: F01D5/026 ,  F16C3/023 ,  F16C2360/23 ,  Y02T50/671 ,  Y10S29/013 ,  Y10T29/4932

Abstract: An inner rotor shaft for use in a small twin spool gas turbine engine, the inner rotor shaft having a hollow middle section formed of a smaller diameter hollow section on a compressor end and a larger diameter hollow section on the turbine end of the shaft. Solid shaft end extend from the hollow section to form a forward solid shaft end to secure the fan rotor disk and an aft solid shaft end to secure the turbine rotor disk. A parabolic shaped transition section joins the forward shaft end to the smaller diameter hollow section, and a conical shaped transition section joins the aft shaft end to the larger diameter hollow section. A conical shaped transition piece joins the two hollow sections together to form an inner rotor shaft that can fit within a minimal space between the compressor rotor disk and the annular combustor assembly of the engine. The conical shaped transition section on the turbine end is so shaped in order to fit within a space formed inside the high pressure turbine rotor disk of the engine in order to minimize the axial spacing between the bearings that support the inner rotor shaft and raise the critical speed of the shaft to a safe level above the operating speed of the engine in order to make such a small twin spool gas turbine engine possible.

Abstract translation: 一种用于小型双轴卷烟气发动机的内转子轴，内转子轴具有由压缩机端部的较小直径的中空部分形成的空心中部，在轴的涡轮机端部具有较大直径的中空部分。 实心轴端从中空部分延伸以形成一个向前的实心轴端，以固定风扇转子盘和一个实心轴端，以固定涡轮转子盘。 抛物线形过渡部分将前轴端连接到较小直径的中空部分，并且锥形过渡部分将后轴端连接到较大直径的中空部分。 锥形过渡件将两个中空部分连接在一起以形成内转子轴，其可以装配在压缩机转子盘和发动机的环形燃烧器组件之间的最小空间内。 涡轮机端部上的锥形过渡部分被成形以便装配在形成在发动机的高压涡轮机转子盘内部的空间内，以便最小化支撑内转子轴的轴承之间的轴向间距并且提高关键 轴的转速达到高于发动机运行速度的安全水平，以便使这种小型双阀芯燃气涡轮发动机成为可能。

公开(公告)号：US20120082563A1

公开(公告)日：2012-04-05

申请号：US12894476

申请日：2010-09-30

Applicant: Jack W. Wilson, JR. ,  John E. Ryznic ,  James P. Downs

Inventor： Jack W. Wilson, JR. ,  John E. Ryznic ,  James P. Downs

IPC: F01D5/18 ,  B23P15/02

CPC classification number: F01D5/187 ,  F01D5/081 ,  F01D5/34 ,  F01D11/001 ,  F05D2250/80 ,  F05D2260/202 ,  F05D2260/205 ,  Y02T50/676

Abstract: A micro gas turbine engine in which the turbine rotor blades are formed as an integral bladed rotor with cooling air passages formed within the blades and the rotor disk by an EDM process. an adjacent stator vane includes an air riding seal with an air cushion supplied through the vanes to provide cooling, and where the air cushion is then passed into the turbine blades and rotor disk to provide cooling for the turbine blades. With cooling of the turbine blades, higher turbine inlet temperatures for micro gas turbine engines can be produced.

Abstract translation: 一种微型燃气涡轮发动机，其中涡轮机转子叶片形成为整体叶片转子，其中通过EDM工艺在叶片和转子盘中形成冷却空气通道。 相邻的定子叶片包括具有通过叶片提供的气垫的空气骑行密封件以提供冷却，并且其中气垫然后进入涡轮机叶片和转子盘以为涡轮叶片提供冷却。 通过涡轮叶片的冷却，可以生产用于微型燃气涡轮发动机的更高的涡轮机入口温度。

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：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：US20120104762A1

公开(公告)日：2012-05-03

申请号：US12913023

申请日：2010-10-27

Applicant: Jack W. Wilson, JR. ,  John E. Ryznic

Inventor： Jack W. Wilson, JR. ,  John E. Ryznic

IPC: F03D9/00 ,  B23P17/00 ,  B23P17/04

CPC classification number: F03D3/061 ,  F03D13/25 ,  F03D80/70 ,  F05B2240/93 ,  F05B2250/86 ,  Y02E10/727 ,  Y02E10/74 ,  Y10T29/49229 ,  Y10T29/49826

Abstract: A large floating vertical axis wind turbine with a floating inner cylinder having rotor blades that rotate together as an assembly, and a floating outer cylinder with a central opening in which the floating inner cylinder rotates for support against tipping. Outriggers with floating devices on the ends extend out from the floating outer cylinder for additional stability. The floating inner cylinder is partially supported by a top bearing on the outer cylinder to carry some of the load from the rotor blades.

Abstract translation: 具有浮动内筒的大浮动垂直轴风力涡轮机，其具有作为组件一起旋转的转子叶片，以及具有中心开口的浮动外筒，浮动内筒旋转以支撑以防止倾翻。 具有浮动装置的外伸支架从浮动外筒延伸出来以获得额外的稳定性。 浮动内筒由外筒上的顶部轴承部分支撑，以承载来自转子叶片的一些载荷。

公开(公告)号：US20110164962A1

公开(公告)日：2011-07-07

申请号：US12683524

申请日：2010-01-07

Applicant: Jack W. Wilson, JR. ,  John E. Ryznic

Inventor： Jack W. Wilson, JR. ,  John E. Ryznic

IPC: F01D11/08

CPC classification number: F01D11/08 ,  F05D2300/2112 ,  F05D2300/614

Abstract: A turbine rotor blade with a brush seal formed between the blade tip and an outer shroud to form a seal for a blade outer air seal. The brush seal includes fibers made from a high temperature resistant material that has long wear life such as fibers of alumina-boria-silicate in order to withstand the temperature environment of a turbine rotor blade and to provide long life due to rubbing of the brush fibers on the relatively rotating brush seal surface.

Abstract translation: 具有形成在叶片顶端和外护罩之间的刷密封的涡轮转子叶片，以形成用于叶片外部空气密封的密封件。 毛刷密封件包括由具有较长磨损寿命的耐高温材料制成的纤维，例如氧化铝 - 氧化硼 - 硅酸盐的纤维，以便承受涡轮转子叶片的温度环境并且由于刷毛纤维的摩擦而提供长寿命 在相对旋转的刷子密封面上。

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。