公开(公告)号：US07878762B2

公开(公告)日：2011-02-01

申请号：US11718517

申请日：2004-12-01

Applicant: Gabriel L. Suciu ,  James W. Norris ,  Craig A. Nordeen

Inventor： Gabriel L. Suciu ,  James W. Norris ,  Craig A. Nordeen

IPC: F01D5/30

CPC classification number: F02C3/08 ,  F01D5/225 ,  F01D5/3007 ,  F02C3/073 ,  F02K3/068 ,  F05D2260/30 ,  F05D2260/33 ,  Y10T29/49245

Abstract: A tip-turbine engine comprises a fan-turbine rotor assembly that includes one or more turbine ring rotors. Each turbine ring is assembled from a multitude of turbine blade clusters. By forming the turbine blades in clusters, leakage between adjacent blade platforms is minimized which increases engine efficiency. Assembly of the turbine blade clusters to a diffuser surface includes axial installation and radial locking of each turbine blade cluster. This is accomplished by attachment lugs protruding from the underside of the arcuate base of the turbine blade clusters. Torque load surfaces are also integrated into the arcuate base.

Abstract translation: 顶端涡轮发动机包括包括一个或多个涡轮机环形转子的风扇 - 涡轮机转子组件。 每个涡轮环由多个涡轮机叶片组装配。 通过将涡轮机叶片组成簇，相邻叶片平台之间的泄漏被最小化，这提高了发动机效率。 将涡轮机叶片组组装到扩散器表面包括每个涡轮叶片组的轴向安装和径向锁定。 这是通过从涡轮机叶片组的弧形底部的下侧突出的附接凸耳来实现的。 扭矩负载表面也集成在弧形底座中。

公开(公告)号：US20100293946A1

公开(公告)日：2010-11-25

申请号：US12784986

申请日：2010-05-21

Applicant: Michael J. Vick

Inventor： Michael J. Vick

IPC: F01K27/00 ,  F28F1/24

CPC classification number: F28D9/0043 ,  F02C3/08 ,  F02C7/10 ,  F05D2220/76 ,  F23D14/66 ,  F23L15/04 ,  F28D9/0018 ,  F28D9/0056 ,  F28D21/0003 ,  F28F21/04 ,  Y02E20/348 ,  Y02T50/671

Abstract: An annular design heat exchanger is formed from an arrangement of wedge-shaped stacks of wafers. Each wafer includes sheets of material separated by peripheral and supporting walls that define interior flow channels through which a first fluid can flow. Holes in the sheets provide inlets and outlets to the channels, and walls surrounding the holes mate with neighboring wafers in the stack, forming integral inlet and outlet manifolds, while ensuring uniform spacing between the wafers. A second fluid can flow around the manifolds and through the spaces between the wafers in a counterflow pattern. In the annular assembly, the manifolds are oriented substantially axially, and the flow channels are oriented substantially radially. The heat exchanger can be formed from a ceramic material, and can be incorporated into an engine assembly or a heat-recirculating combustor.

Abstract translation: 环形设计热交换器由楔形的晶片叠层组成形成。 每个晶片包括由外围和支撑壁隔开的材料片，其限定内部流动通道，第一流体可以流经第一流体。 板中的孔向通道提供入口和出口，并且围绕孔的壁与堆叠中的相邻晶片配合，形成整体的入口和出口歧管，同时确保晶片之间的均匀间隔。 第二流体可以以歧管流动并且以逆流模式通过晶片之间的空间。 在环形组件中，歧管基本上轴向定向，并且流动通道基本上径向定向。 热交换器可以由陶瓷材料形成，并且可以结合到发动机组件或热循环燃烧器中。

公开(公告)号：US20100232953A1

公开(公告)日：2010-09-16

申请号：US12404573

申请日：2009-03-16

Applicant: STEPHEN A. ANDERSON ,  RONALD TRUMPER ,  GARY WEIR

Inventor： STEPHEN A. ANDERSON ,  RONALD TRUMPER ,  GARY WEIR

IPC: F04D19/02 ,  F04D29/26 ,  F04D29/40 ,  F04D29/54

CPC classification number: F04D29/542 ,  F02C3/08 ,  F02C9/52 ,  F04D17/025 ,  F04D29/284 ,  F04D29/403

Abstract: A hybrid gas compressor has at least one rotor and shroud which define a compressor gas path extending from an inlet to an outlet. The compressor includes at least two compression stages and one diffusion stage between the inlet and outlet, the compression stages including respective circumferential arrays of blades extending from the rotor and the diffusion stage including a circumferential array of vanes between the compression stages. Blade aerodynamic loadings may be controlled, particularly in the last stage, to provide desired compression characteristics across the compressor. A bleed outlet is optionally located between the inlet and outlet for bleeding from the gas path.

Abstract translation: 混合气体压缩机具有至少一个转子和护罩，其限定从入口延伸到出口的压缩机气体路径。 压缩机包括至少两个压缩级和在入口和出口之间的一个扩散级，压缩级包括从转子和扩散级延伸的相应的周向阵列，其包括在压缩级之间的周向阵列的叶片。 叶片空气动力学载荷可以被控制，特别是在最后阶段，以提供压缩机所需的压缩特性。 排气口可选地位于入口和出口之间，用于从气体路径渗出。

公开(公告)号：US20100098553A1

公开(公告)日：2010-04-22

申请号：US12288052

申请日：2008-10-16

Applicant: Joseph Carl Smith

Inventor： Joseph Carl Smith

IPC: F01D5/14

CPC classification number: F01D5/145 ,  F02C3/08 ,  Y02T50/673

Abstract: In one embodiment, a centrifugal impeller is described having a front side with airfoils and a back side. A conduit may be formed between the front side and the back side, or any other side, and may convey pressurized working fluid between the two. The conduit may pass relatively high pressure working fluid between any two locations such as from the front side to the back side. The conduit may include an aperture located on the front side and an aperture located on the back side. Any number of conduits may be defined within the centrifugal impeller. Apertures located on the front side of the impeller may be formed in any suitable place, such as a hub of the impeller or an airfoil surface, to set forth just two non-limiting examples.

Abstract translation: 在一个实施例中，描述了具有前翼面和后侧的离心式叶轮。 可以在前侧和后侧或任何其它侧面之间形成导管，并且可以在两者之间输送加压的工作流体。 管道可以在任何两个位置之间通过相对高压的工作流体，例如从前侧到后侧。 导管可以包括位于前侧的孔和位于背侧的孔。 任何数量的导管可以在离心式叶轮内限定。 位于叶轮前侧的孔可以形成在任何合适的位置，例如叶轮的轮毂或翼型表面，仅列出两个非限制性实例。

公开(公告)号：US20090293485A1

公开(公告)日：2009-12-03

申请号：US12130021

申请日：2008-05-30

Applicant: Nick Nolcheff ,  Dan Frias

Inventor： Nick Nolcheff ,  Dan Frias

IPC: F01D1/02 ,  F02C7/057

CPC classification number: F01D9/02 ,  F02C3/08 ,  F05D2270/172 ,  F15D1/06 ,  F15D1/14

Abstract: A diffuser is provided that includes a first wall, a second wall, and a first plasma actuator. The first wall has a radially-extending section and a curved section. The second wall has a radially-extending section and a curved section that are spaced apart from the radially-extending section and the curved section of the first wall such that the curved section of the second wall is disposed radially inwardly from the curved section of the first wall and a flow path is defined therebetween. The first plasma actuator is disposed on the curved section of the second wall, and the first plasma actuator is adapted to generate a first electric field to ionize a first portion of air flowing along the flow path to form a plurality of ionized species capable of inducing a second portion of air to flow in a desired direction.

Abstract translation: 提供了包括第一壁，第二壁和第一等离子体致动器的扩散器。 第一壁具有径向延伸部分和弯曲部分。 第二壁具有径向延伸部分和弯曲部分，其与第一壁的径向延伸部分和弯曲部分间隔开，使得第二壁的弯曲部分从第二壁的弯曲部分径向向内设置 第一壁和流路之间限定。 第一等离子体致动器设置在第二壁的弯曲部分上，并且第一等离子体致动器适于产生第一电场以电离沿着流动路径流动的空气的第一部分以形成能够诱导的多个离子化物质 空气的第二部分在期望的方向上流动。

公开(公告)号：US20090232676A1

公开(公告)日：2009-09-17

申请号：US12073980

申请日：2008-03-12

Applicant: R. Jan Mowill

Inventor： R. Jan Mowill

IPC: F04D25/04 ,  F02C7/00 ,  F04D17/10

CPC classification number: F02C3/145 ,  F01D5/043 ,  F01D9/026 ,  F02C3/05 ,  F02C3/08 ,  F02C3/103 ,  F04D17/162 ,  F05D2220/50 ,  Y02T50/673

Abstract: A compact, single shaft gas turbine gas generator uses a high pressure ratio dual-entry single stage centrifugal compressor, can combustors, and a radial inflow turbine with the compressor configured to achieve an overall pressure ratio of about 12:1 or greater and Mach Numbers less than or equal to about 1.4. The radial inflow turbine is configured to provide an expansion ratio of about 4:1 to about 5:1, to provide partially expanded combustion gases to a free-power turbine or an expansion nozzle, in a work-producing engine configuration. A ball bearing assembly in front of the compressor is used in conjunction with a thrust piston assembly to take up turbine thrust load, while a radial tilt pad bearing assembly is used in front of the turbine. A collector with scroll-shaped sector portions collects compressed air from an annular vaned diffuser, and respective crossover ducts channel the collected diffused compressed air from each sector portion to a plenum feeding can combustors. Bleed systems at each compressor inlet provide increased diffuser stability margins. Gas turbine engines configured with the above gas generator may provide 30% thermal efficiency or more in a rated power range of about 4 Mw or less.

Abstract translation: 紧凑型单轴燃气轮机气体发生器使用高压比双入口单级离心压缩机，可燃烧器和径向流入涡轮机，压缩机构造成实现大约12:1或更大的总体压力比和马赫数 小于或等于约1.4。 径向流入涡轮机被配置为在工作发动机构造中提供约4:1至约5:1的膨胀比，以将部分膨胀的燃烧气体提供给自由动力涡轮机或膨胀喷嘴。 在压缩机前面的滚珠轴承组件与推力活塞组件结合使用以承担涡轮机推力负载，而在涡轮机前方使用径向倾斜瓦块轴承组件。 具有涡旋形扇形部分的收集器从环形叶片扩散器收集压缩空气，并且相应的交叉导管将收集的扩散压缩空气从每个扇形部分引导到供气罐燃烧器的增压室。 每个压缩机入口处的排气系统提供增加的扩散器稳定裕度。 配置有上述气体发生器的燃气涡轮发动机可以在约4Mw或更小的额定功率范围内提供30％的热效率或更高。

公开(公告)号：US20080219833A1

公开(公告)日：2008-09-11

申请号：US11718353

申请日：2004-12-01

Applicant: Gabriel L. Suciu ,  Craig A. Nordeen ,  Brian Merry

Inventor： Gabriel L. Suciu ,  Craig A. Nordeen ,  Brian Merry

IPC: F02C3/073 ,  F02C3/08 ,  F02K3/068

CPC classification number: F01D5/022 ,  F02C3/073 ,  F02C3/08 ,  F02K3/068 ,  F05D2260/60 ,  Y02T50/672

Abstract: A fan-turbine rotor assembly for a tip turbine engine includes an inducer with an inducer inlet section and an inducer passage section in communication with a core airflow passage within a fan blade. Each inducer inlet section is canted toward a rotational direction of the fan-turbine rotor assembly such that the inducer inlet section operates as an air scoop during rotation of the fan-turbine rotor assembly. Both axial and centrifugal compression of the airflow occurs within the inducer passage section to effectively pump the airflow through the inducer section and into the core airflow passage.

Abstract translation: 用于顶端涡轮发动机的风扇涡轮转子组件包括具有导流器入口部分和与风扇叶片内的气流通道连通的导流通道部分的导流器。 每个诱导器入口部分朝着风扇 - 涡轮转子组件的旋转方向倾斜，使得在风扇 - 涡轮转子组件旋转期间，导流器入口部分作为空气铲斗操作。 气流的轴向和离心压缩都发生在导流通道部分内，以有效地泵送通过导流部分并进入芯气流通道的气流。

公开(公告)号：US20080134659A1

公开(公告)日：2008-06-12

申请号：US11635123

申请日：2006-12-06

Applicant: Frederick M. Schwarz ,  Jesse W. Smith

Inventor： Frederick M. Schwarz ,  Jesse W. Smith

IPC: F02C3/14 ,  F03B3/06

CPC classification number: F04D29/051 ,  F01D11/08 ,  F01D11/22 ,  F02C3/08 ,  F02C7/06 ,  F04D29/052 ,  F04D29/059 ,  F04D29/622 ,  F04D29/624 ,  F05D2240/52

Abstract: A turbine engine includes an engine housing enclosing: a centrifugal compressor having a rotor; at least one centrifugal compressor bore mounted to the rotor; at least one blade mounted to each of the at least one centrifugal bore and disposed proximate to at least one static wall; a turbine disposed in connection with the centrifugal compressor; a thrust bearing disposed in connection with the rotor; and means for moving said rotor with reference to the at least one static wall attached to the thrust bearing.

Abstract translation: 涡轮发动机包括发动机壳体，其包围：具有转子的离心式压缩机; 至少一个安装在转子上的离心式压缩机孔; 至少一个叶片安装到所述至少一个离心孔中的每一个并且设置成邻近至少一个静态壁; 与离心式压缩机连接设置的涡轮机; 与转子相连的推力轴承; 以及用于相对于连接到推力轴承的至少一个静态壁移动所述转子的装置。

公开(公告)号：US20080124211A1

公开(公告)日：2008-05-29

申请号：US11718525

申请日：2004-12-01

Applicant: Gabriel L. Suciu ,  James W. Norris ,  Craig A. Nordeen

Inventor： Gabriel L. Suciu ,  James W. Norris ,  Craig A. Nordeen

IPC: F01D5/14

CPC classification number: F01D5/326 ,  F02C3/073 ,  F02C3/08

Abstract: A fan-turbine rotor assembly includes a diffuser section (114) which turns and diffuses the airflow from a radial core airflow passage (80) toward an axial airflow direction. Diffuser flow passages communicate with the diffuser passages (144) at a location which reduces separation of the airflow as the airflow is turned from the radial core airflow passage (80) toward an axial airflow direction through airflow aspiration at the potentially turbulent locations.

Abstract translation: 风扇 - 涡轮转子组件包括扩散器部分（114），其将来自径向芯气流通道（80）的气流朝向轴向气流方向扩散。 扩散器流动通道在一个位置处与扩散通道（144）连通，当气流从径向核心气流通道（80）通过在潜在湍流位置处的气流抽吸朝向轴向气流方向转动时，气流的分离减小。

公开(公告)号：US20080044281A1

公开(公告)日：2008-02-21

申请号：US11718420

申请日：2004-12-01

Applicant: Gabriel Suciu ,  Brian Merry ,  Lawrence Portlock

Inventor： Gabriel Suciu ,  Brian Merry ,  Lawrence Portlock

IPC: F01D25/24

CPC classification number: F02C7/32 ,  F02C3/073 ,  F02C3/08 ,  F02C7/36 ,  F02K3/02 ,  F02K3/068 ,  F05D2260/40311

Abstract: A non-rotating compartment along an engine centerline of a tip turbine engine is defined between an inner support housing, an outer support housing and an aft housing. The non-rotating compartment provides a space that may be utilized for a multitude of engine accessories and components including an engine lubricating fluid system.

Abstract translation: 沿着顶部涡轮发动机的发动机中心线的非旋转舱被限定在内部支撑壳体，外部支撑壳体和后部壳体之间。 非旋转隔室提供可用于多个发动机附件和部件的空间，包括发动机润滑流体系统。