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1. 发明申请

US20190003483A1 COMPRESSOR WHEEL AND FLUID COMPRESSION DEVICE COMPRISING THE SAME 审中-公开
公开(公告)号：US20190003483A1
公开(公告)日：2019-01-03
申请号：US15663826
申请日：2017-07-31
申请人： NOPORVIS CO., LTD.
发明人： Yuan-Hung Tai , Hui-Hung Lin , Chun-Neng Chan
IPC分类号： F04D29/28 , F04D25/04 , F02C3/08 , F04D29/62
CPC分类号： F04D29/286 , F02B33/40 , F02C3/085 , F04D17/025 , F04D25/045 , F04D25/16 , F04D29/285 , F04D29/624 , F05D2220/40
摘要： A compressor wheel of a fluid compression device includes a wheel part, a shaft part and a plurality of connection parts. The wheel part includes a main body formed with a through hole, and a plurality of blades protruded from an outer side of the main body. The shaft part is accommodated in the through hole and configured to connect to a rotor shaft. The plurality of connection parts is connected between an inner side of the main body and the shaft part. Wherein, a fluid passage is formed between the inner side of the main body and the shaft part to allow fluid to flow to a rear side of the compressor wheel from a front side of the compressor wheel via the fluid passage.

2. 发明申请

US20160061045A1 DECOUPLED GAS TURBINE ENGINE 审中-公开
标题翻译：解除气体涡轮发动机
公开(公告)号：US20160061045A1
公开(公告)日：2016-03-03
申请号：US14842404
申请日：2015-09-01
申请人： United Technologies Corporation
发明人： Gabriel L. Suciu , Stephen K. Kramer , Jesse M. Chandler
IPC分类号： F01D9/02 , F02C7/04 , F01D5/06 , F02C3/04 , F01D5/04
CPC分类号： F01D9/02 , F01D5/04 , F01D5/06 , F01D13/003 , F02C3/04 , F02C3/05 , F02C3/085 , F02C3/10 , F02C3/103 , F02C3/14 , F02C7/04 , F05D2220/32 , F05D2240/24 , F05D2240/35 , F05D2250/312 , F05D2250/314
摘要： A decoupled gas turbine engine includes a high spool assembly and a low spool assembly each having a rotational axis that are spaced from one-another. The engine further includes a combustor that may have a centerline spaced from the rotational axes of each spool assembly. Turning ducts of the engine are configured to re-direct airflow from one spool assembly to the next and/or between one spool assembly and the combustor.
摘要翻译：解耦燃气涡轮发动机包括一个高阀芯组件和一个低阀芯组件，每个都具有一个彼此间隔开的旋转轴线。发动机还包括可具有与每个线轴组件的旋转轴线间隔开的中心线的燃烧器。发动机的转向管道被配置为将气流从一个线轴组件重新引导到下一个和/或一个线轴组件和燃烧器之间。

3. 发明申请

US20120175886A1 GAS TURBINE ENGINE CONFIGURATIONS 有权
标题翻译：气体涡轮发动机配置
公开(公告)号：US20120175886A1
公开(公告)日：2012-07-12
申请号：US13226156
申请日：2011-09-06
申请人： Frank Wegner Donnelly , David William Dewis
发明人： Frank Wegner Donnelly , David William Dewis
IPC分类号： H02K7/18 , F02C6/00 , F02C3/10
CPC分类号： F01D15/10 , F02C3/05 , F02C3/085 , F02C6/18 , F05D2260/90 , F05D2260/904 , Y02E50/12
摘要： A system of dense packaging of turbomachinery in a gas turbine engine by means of close-coupling of components and by the ability to rotate various engine components with respect to other engine components is disclosed. In addition, spool shaft rotational direction may be reversed to suit the application. In multiple engine configurations, the same ability to close-couple and rotate components and to reverse shaft rotational direction in order to rearrange the engine geometry package is used for packaging two or more gas turbine engines to achieve high power density. Dense-packing is possible because of a number of features of the basic engine. These features include: the use of compact centrifugal compressors and radial turbine assemblies; the close coupling of turbomachinery for a dense packaging; the ability to rotate certain key components so as to facilitate ducting and preferred placement of other components; the ability to control spool shaft rotational direction; and operation at high overall pressure ratios.
摘要翻译：公开了一种通过组件的紧密耦合和通过相对于其它发动机部件旋转各种发动机部件的能力在燃气涡轮发动机中的涡轮机械的密集包装系统。此外，卷筒轴旋转方向可以颠倒以适合应用。在多重发动机配置中，为了重新排列发动机几何形状组件，能够将组件相互联接和旋转以及使轴旋转方向相反的能力用于包装两个或更多个燃气涡轮发动机以实现高功率密度。由于基本引擎的许多功能，密集包装是可能的。这些功能包括：使用紧凑型离心压缩机和径向涡轮机组件; 密封包装的涡轮机械的紧密耦合; 旋转某些关键部件的能力，以便于其他组件的导管和优选的放置; 控制卷筒轴旋转方向的能力; 并在高总压比下运行。

4. 发明授权

US07571607B2 Two-shaft turbocharger 失效
标题翻译：双轴涡轮增压器
公开(公告)号：US07571607B2
公开(公告)日：2009-08-11
申请号：US11368651
申请日：2006-03-06
申请人： Gary D. Vrbas
发明人： Gary D. Vrbas
IPC分类号： F02B33/44
CPC分类号： F02C6/12 , F01D17/162 , F01D17/165 , F02B37/004 , F02B37/013 , F02B37/24 , F02C3/085 , F04D17/025 , F04D25/04 , F05D2270/10 , Y02T10/144
摘要： A turbocharger, having an axial compressor wheel and an axial turbine wheel mounted on a first shaft supported by a housing, and a radial compressor wheel and a radial turbine wheel mounted on a second shaft, the second shaft concentrically extending around the first shaft and being supported by the housing. The housing defines a first duct extending axially from the exducer of the axial compressor to the inducer of the radial compressor, and a second duct extending axially from the exducer of the radial turbine to the inducer of the axial turbine. A plurality of controllable compressor guide vanes extend through the first duct, and a plurality of controllable turbine stator vanes extend through the second duct. The housing is provided with variable diffuser vanes at the exducer of the radial compressor, and with variable turbine vanes at the inducer of the radial turbine. The variable turbine vanes and the turbine stator vanes are controlled to accurately control the rotation rate of the radial and axial turbines. The compressor guide vanes are controlled to minimize surge and maximize choke flow rate.
摘要翻译：一种涡轮增压器，其具有安装在由壳体支撑的第一轴上的轴向压缩机叶轮和轴向涡轮机叶轮，以及安装在第二轴上的径向压缩机叶轮和径向涡轮机叶轮，所述第二轴同心地围绕第一轴延伸并且是由房屋支持。壳体限定从轴向压缩机的排放器轴向延伸到径向压缩机的引导器的第一管道，以及从径向涡轮机的排放器轴向延伸到轴向涡轮机的引导器的第二管道。多个可控制的压缩机导向叶片延伸穿过第一管道，并且多个可控制的涡轮机定子叶片延伸通过第二管道。壳体在径向压缩机的排放器处设置有可变的扩散器叶片，并且在径向涡轮机的引导器处具有可变涡轮叶片。控制可变涡轮机叶片和涡轮机定子叶片以精确地控制径向和轴向涡轮机的旋转速率。控制压缩机导叶以最小化浪涌并最大限度地提高阻流流量。

5. 发明授权

US07390163B2 Radial flow turbine 失效
标题翻译：径向涡轮机
公开(公告)号：US07390163B2
公开(公告)日：2008-06-24
申请号：US11154258
申请日：2005-06-15
申请人： Luke W. Clauson
发明人： Luke W. Clauson
IPC分类号： F02C7/00
CPC分类号： F02C3/05 , F01D1/22 , F02C3/085 , F02C3/16
摘要： A multi-stage radial flow compressor and turbine includes a rotor having a first plurality of blades and a second plurality of blades radially outward from the first plurality. A stator has a plurality of blades radially positioned between the two sets of rotor blades. The stator also includes a plurality of combustors positioned radially outward from the stators. The rotor also has turbine blades radially outward from the combustors which are driven by the combusted gas.
摘要翻译：多级径流式压缩机和涡轮机包括具有第一多个叶片的转子和从第一多个叶片径向向外的第二多个叶片。定子具有径向位于两组转子叶片之间的多个叶片。定子还包括从定子径向向外定位的多个燃烧器。转子还具有从由燃烧气体驱动的燃烧器径向向外的涡轮叶片。

6. 发明授权

US06845621B2 Annular combustor for use with an energy system 失效
标题翻译：用于能源系统的环形燃烧器
公开(公告)号：US06845621B2
公开(公告)日：2005-01-25
申请号：US10275049
申请日：2001-05-01
申请人： J. Michael Teets
发明人： J. Michael Teets
IPC分类号： F02C3/08 , F23L1/00 , F23M9/06 , F23R3/04 , F23R3/50
CPC分类号： F02C3/085 , F23M9/06 , F23R3/04 , F23R3/50
摘要： An annular combustor has an annular inner shell, an annular outer shell and a dome end wall connecting the inner shell with the outer shell. A dam is positioned between the dome end wall and the exit end and extends radially from at least one of the inner shell and the outer shell to provide a reduced flow area passageway within the combustion chamber.
摘要翻译：环形燃烧器具有环形内壳，环形外壳和连接内壳与外壳的圆顶端壁。大坝定位在圆顶端壁和出口端之间，并且从内壳和外壳中的至少一个径向延伸，以在燃烧室内提供减小的流动区域通道。

7. 发明授权

US06571563B2 Gas turbine engine with offset shroud 失效
标题翻译：燃气涡轮发动机带偏心护罩
公开(公告)号：US06571563B2
公开(公告)日：2003-06-03
申请号：US09741476
申请日：2000-12-19
申请人： Thomas K. Yim , Robert A. Nims , Mike Masoudipour
发明人： Thomas K. Yim , Robert A. Nims , Mike Masoudipour
IPC分类号： F02C304
CPC分类号： F02C7/06 , F01D11/14 , F01D25/16 , F02C3/085 , F02C3/09 , F05D2250/312 , Y10T29/4932
摘要： A gas turbine engine having a housing and an axially extending shaft journaled to the housing by two axially spaced apart bearings. The bearings are located along the shaft so as to define an overhung shaft portion. A rotating component such as a turbine wheel or compressor wheel is mounted on the overhung shaft portion and is concentric about the centerline (50) of the engine. An annular shroud (40) that is part of the housing is disposed about the rotating component, the annular shroud (40) being concentric about a centerline (60) radially offset from the engine (50).
摘要翻译：一种燃气涡轮发动机，其具有壳体和轴向延伸的轴，其通过两个轴向间隔开的轴承轴颈连接到壳体。轴承沿着轴定位，以便限定悬挂轴部分。诸如涡轮机叶轮或压缩机叶轮的旋转部件安装在悬臂轴部上并且与发动机的中心线（50）同心。作为壳体的一部分的环形护罩（40）围绕旋转部件设置，环形护罩（40）围绕径向偏离发动机（50）的中心线（60）同心。

8. 发明授权

US5161945A Turbine engine interstage seal 失效
标题翻译：涡轮发动机异常密封
公开(公告)号：US5161945A
公开(公告)日：1992-11-10
申请号：US595335
申请日：1990-10-10
申请人： Lloyd L. Clevenger , Robert C. Rowan, Jr.
发明人： Lloyd L. Clevenger , Robert C. Rowan, Jr.
IPC分类号： F01D25/14 , F02C3/08
CPC分类号： F01D25/145 , F02C3/085
摘要： A turbine engine includes axially adjacent compressor and turbine rotors which define a groove therebetween. Into the groove between the rotors radially extends an annular interstage seal assembly. The seal assembly includes a thermally insulative cellular wall structure which resists thermal and pressure included distortions. At its radially inner extent the cellular wall defines a seal structure in cooperation with the rotors, and also carries heat shield members on an axial fore disposed toward the turbine rotor.
摘要翻译：涡轮发动机包括在其间限定凹槽的轴向相邻的压缩机和涡轮转子。在转子之间的凹槽中径向地延伸一个环形的阶段间密封组件。密封组件包括热绝缘的细胞壁结构，其抵抗包含热和压力的失真。在其径向内部，细胞壁与转子协调地限定密封结构，并且还在朝向涡轮转子设置的轴向前端上承载隔热构件。

9. 发明授权

US4967551A Turbine engine 失效
标题翻译：涡轮发动机
公开(公告)号：US4967551A
公开(公告)日：1990-11-06
申请号：US463772
申请日：1990-01-05
申请人： Robie Faulkner
发明人： Robie Faulkner
IPC分类号： F02C3/08 , F23C7/00 , F23R3/28 , F23R3/54
CPC分类号： F23C7/004 , F02C3/085 , F23R3/28 , F23R3/54 , F23C2202/40 , F23D2900/00016
摘要： A turbine engine including a rotary compressor 10 to be driven by a turbine wheel 12 and provided with an annular combustor 36 including an outlet 44 whereby gases of combustion may be directed to a nozzle 46 to be directed against the turbine wheel 12 to drive the same. Fuel injectors each include a simple tube 70 having a cut off end 72 disposed in a ring-like mounting element 100 which in turn mounts a plurality fo swirler vanes 106 which cooperate with a converger 94 having a central aperture 96 aligned with the end 72 of the tube 70 that provides highly stable combustion within the combustor 36.
摘要翻译：一种涡轮发动机，其包括由涡轮机叶轮12驱动并设置有包括出口44的环形燃烧器36的旋转压缩机10，由此燃烧气体可被引导到喷嘴46以引导涡轮机叶轮12驱动它。燃料喷射器各自包括简单的管70，其具有设置在环状安装元件100中的切断端72，该安装元件100又安装多个fo旋流器叶片106，其与具有与中心孔96对准的中心孔96的收敛器94配合在燃烧器36内提供高度稳定的燃烧的管70。

10. 发明授权

US4000608A Gas turbine engine combustion chamber 失效
公开(公告)号：US4000608A
公开(公告)日：1977-01-04
申请号：US482809
申请日：1974-06-24
申请人： Richard Chute
发明人： Richard Chute
IPC分类号： F02C3/08 , F02C7/06
CPC分类号： F02C7/06 , F02C3/085
摘要： A small gas turbine engine having a small, high speed shaft assembly including a central shaft member, a radial outflow compressor rotor secured to one end of the central shaft member with its inlet end disposed outboard of the shaft assembly, and a radial inflow turbine rotor secured to the other end of the central shaft member with its discharge end disposed outboard of the shaft assembly. The shaft assembly is supported at its ends, outboard of the rotors, by a pair of bearings which are axially secured but allow limited radial movement of the shaft assembly. An annular combustor is disposed between the turbine and compressor rotors in encircling relation to the central shaft member. Fuel is supplied to the combustor chamber from the exhaust end of the turbine through an axial passage in the shaft assembly opening at one end outboard of the exhaust end bearing and communicating at its other end with radial ports in the central shaft member arranged to sling fuel into the combustor chamber. The shaft assembly housing comprises two cast sections which are coupled together to enclose the combustor with the end portion of each housing section shaped to define a shroud for the radial blades of the turbine and compressor rotors, respectively. A cast nozzle plate and a diffuser plate are secured to the respective housing sections. The nozzle and diffuser plates each include an annular outer portion defining the vanes for the turbine and compressor rotors, respectively, and a central hollow hub portion embracing the central shaft member of the shaft assembly; the inboard ends of the two hub portions are axially spaced to expose the radial ports in the central shaft member and allow slinging delivery of fuel into the combustor. An annular air inlet to the compressor rotor spaces the shaft assembly housing from a transmission housing, and the compressor end of the shaft assembly is coupled, outboard of the compressor end bearing, to speed reduction gearing journalled within the transmission housing.

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