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11. 发明授权

US3465518A Radial outflow turboshaft engine 失效
标题翻译：径向流出涡轮发动机
公开(公告)号：US3465518A
公开(公告)日：1969-09-09
申请号：US3465518D
申请日：1966-12-14
申请人： GEN ELECTRIC
发明人： ERWIN JOHN R
IPC分类号： F02C3/045 , F02C3/08 , F02G3/00 , F02C7/08
CPC分类号： F02C3/085 , F02C3/045

12. 发明授权

US3172260A Gas turbine engine 失效
公开(公告)号：US3172260A
公开(公告)日：1965-03-09
申请号：US15193161
申请日：1961-11-13
申请人： CONTINENTAL MOTORS CORP
发明人： RICHARD CHUTE
IPC分类号： F02C3/08
CPC分类号： F02C3/085 , Y02T50/671

13. 发明授权

US3052096A Gas turbine power plant having centripetal flow compressors and centrifugal flow turbines 失效
标题翻译：具有向心流量压缩机和离心式涡轮机的燃气轮机发电厂
公开(公告)号：US3052096A
公开(公告)日：1962-09-04
申请号：US75962458
申请日：1958-09-08
申请人： PAVLECKA VLADIMIR H
发明人： PAVLECKA VLADIMIR H
IPC分类号： F02C3/067 , F02C3/08 , F02C3/09
CPC分类号： F02C3/067 , F02C3/085 , F02C3/09 , Y02T50/671

14. 发明授权

US12018613B1 Disk engine with circumferential swirl radial combustor 有权
公开(公告)号：US12018613B1
公开(公告)日：2024-06-25
申请号：US17846633
申请日：2022-06-22
申请人： Government of the United States, as represented by the Secretary of the Air Force
发明人： Brian Bohan , Marc Polanka , Bennett Staton
IPC分类号： F02C3/08 , F02C7/12
CPC分类号： F02C3/08 , F02C3/085 , F02C7/12
摘要： A disk engine and system configured to provide high power at a reduced axial length is disclosed herein. The disk engine includes a radial compressor, a compressor discharge manifold positioned circumferentially about compressor, a combustion chamber positioned within the discharge manifold and a radial turbine positioned radially inward of the combustion chamber.

15. 发明授权

US11846249B1 Gas turbine engine with integral bypass duct 有权
公开(公告)号：US11846249B1
公开(公告)日：2023-12-19
申请号：US17902230
申请日：2022-09-02
申请人： Raytheon Technologies Corporation
发明人： Jose R. Paulino , Lawrence A. Binek , Sean R. Jackson
IPC分类号： F02K3/02 , F02C3/08
CPC分类号： F02K3/02 , F02C3/085 , F05D2240/128 , F05D2240/35 , F05D2260/606
摘要： A gas turbine engine is provided that includes an engine core and a bypass duct. The engine core includes a compressor section, a combustor section, a turbine section and a core flowpath. The compressor section includes a radial flow compressor rotor. The core flowpath extends through the compressor section, the combustor section and the turbine section from a core inlet to a core exhaust. The bypass duct includes a bypass flowpath that extends outside of the engine core from a bypass inlet to a bypass exhaust. The bypass inlet is disposed along the compressor section and fluidly coupled with core flowpath.

16. 发明申请

US20140338348A1 ROTARY PULSE DETONATION ENGINE 审中-公开
标题翻译：旋转脉冲爆震发动机
公开(公告)号：US20140338348A1
公开(公告)日：2014-11-20
申请号：US14365626
申请日：2012-12-17
申请人： Daniel Guy POMERLEAU , Andrew Richard HICKS
发明人： Daniel Guy Pomerleau , Andrew Richard Hicks
IPC分类号： F02K7/06 , F02K9/97
CPC分类号： F02K7/06 , F01C1/22 , F02C3/085 , F02C3/14 , F02C5/02 , F02C5/06 , F02K9/97 , F05D2220/80 , F23R7/00
摘要： This invention relates to devices for discharging high pressure exhaust, and in particular to pulse detonation engines. More specifically, the invention describes a rotary pulse detonation engine having a rotary valve system. The rotary valve includes a generally-triangular rotor having rotor tips within a rotor chamber having trochoid inner end surfaces and side surfaces. The rotor defines three working chambers defined by the rotor tips contacting the rotor surfaces. In operation, the rotor tips move in a circumferential direction around the rotor chamber as the rotor spins. During operation, each of the working chambers will sequentially pass through an intake interval, compression interval, expansion interval, and an exhaust interval to create and detonate compressed fuel air mixtures for effective release to an exhaust chamber and nozzle thereby creating a pulsed detonation sequence.
摘要翻译：本发明涉及排放高压排气装置，特别涉及脉冲爆震发动机。更具体地，本发明描述了具有旋转阀系统的旋转脉冲爆震发动机。旋转阀包括具有在具有次摆线内端面和侧表面的转子腔内的转子尖端的大致三角形的转子。转子限定由转子尖端与转子表面接触而限定的三个工作室。在操作中，当转子旋转时，转子尖端围绕转子室沿圆周方向移动。在操作期间，每个工作室将依次通过进气间隔，压缩间隔，膨胀间隔和排气间隔，以产生和引爆压缩的燃料空气混合物，以有效地释放到排气室和喷嘴，从而产生脉冲爆震序列。

17. 发明申请

US20130101393A1 REACTION TURBINE AND HYBRID IMPULSE REACTION TURBINE 有权
标题翻译：反应涡轮和混合动力反应涡轮机
公开(公告)号：US20130101393A1
公开(公告)日：2013-04-25
申请号：US13659492
申请日：2012-10-24
申请人： HYBRID TURBINE GROUP
发明人： Howard Purdum , William Downs , L. Vann Downs
IPC分类号： F01D1/16
CPC分类号： F01D1/16 , F02C3/062 , F02C3/085 , F02C3/16 , F02K7/005 , F02K7/08
摘要： A reaction turbine has channels formed in the top surface of a disc to create nozzles. The channels can be covered by a membrane sealed to the disc or by the housing extended from a combustor. Each channel may have a first section extending radially outwardly from an inlet of the reaction turbine and a second curved section extending from the first section to a periphery of the disc. A reaction turbine may also receive input from an impulse turbine. Fluid flows through the impulse turbine and fluid from the impulse turbine enters an inlet of the reaction turbine. The reaction turbine may have cooling channels and cooling fins to lower the temperature of the disc during operation. In addition, magnets may provide bearing support and electricity generation. In addition, the reaction turbine may have a dual shaft construction, with each shaft connected to a reaction turbine. One reaction turbine powers a compressor, while the second reaction turbine powers a load through the second shaft.
摘要翻译：反应涡轮机具有形成在盘的顶表面中的通道，以形成喷嘴。通道可以被密封到盘上的膜或从燃烧器延伸的壳体覆盖。每个通道可以具有从反应涡轮机的入口径向向外延伸的第一部分和从第一部分延伸到盘的周边的第二弯曲部分。反应涡轮机还可以接收来自脉冲涡轮机的输入。流体流过脉冲涡轮机，并且来自脉冲涡轮机的流体进入反应涡轮机的入口。反应涡轮机可以具有冷却通道和冷却翅片，以在操作期间降低盘的温度。此外，磁体可以提供轴承支撑和发电。此外，反应涡轮机可以具有双轴结构，每个轴连接到反应涡轮机。一个反应涡轮机为压缩机供电，而第二反应涡轮机通过第二轴来驱动负载。

18. 发明授权

US08281588B2 Turbomachine system and turbine therefor 有权
标题翻译：涡轮机系统和涡轮机
公开(公告)号：US08281588B2
公开(公告)日：2012-10-09
申请号：US12319717
申请日：2009-01-09
申请人： Stephen Garrett , Richard Owen Evans
发明人： Stephen Garrett , Richard Owen Evans
IPC分类号： F02B33/34 , F01D9/04 , F01D17/00
CPC分类号： F02B37/013 , F01D1/06 , F01D5/043 , F02B37/004 , F02B37/005 , F02B37/007 , F02B37/025 , F02B37/16 , F02B37/18 , F02B37/22 , F02B39/00 , F02C3/085 , F02C6/12 , F05B2240/33 , F05D2210/42 , F05D2220/40 , Y02T10/144
摘要： A turbomachine system comprises a first turbocharger comprising an exhaust gas flow first turbine for location in an exhaust path and a first compressor driven by said first turbine; a turbomachine for location in the exhaust path upstream or downstream of said first turbocharger and comprising an exhaust gas flow second turbine and a second compressor driven by said second turbine. The first turbine has an outlet that is in fluid communication with an inlet of the second turbine. One of said first and second turbines is a radial outflow turbine. The arrangement provides for a relatively compact package. The radial outflow turbine may have a particular structure in which there is provided a deflector member at or near its inlet for directing the gas outwards, a stator for introducing swirl and a downstream turbine rotor. A shroud is fixed to blades of the turbine rotor to prevent leakage and to provide additional structural rigidity.
摘要翻译：涡轮机系统包括第一涡轮增压器，其包括用于排放在排气路径中的废气流第一涡轮机和由所述第一涡轮机驱动的第一压缩机; 用于位于所述第一涡轮增压器的上游或下游的排气路径中的涡轮机，并且包括排气流量第二涡轮机和由所述第二涡轮机驱动的第二压缩机。第一涡轮机具有与第二涡轮机的入口流体连通的出口。所述第一和第二涡轮机中的一个是径向流出涡轮机。该装置提供了相对紧凑的包装。径向流出涡轮机可以具有特定的结构，其中在其入口处或附近设置偏转构件以将气体向外引导，用于引入涡流的定子和下游的涡轮转子。护罩固定到涡轮转子的叶片上以防止泄漏并提供额外的结构刚度。

19. 发明授权

US07886544B2 Propeller or propeller drive 有权
标题翻译：螺旋桨或螺旋桨驱动
公开(公告)号：US07886544B2
公开(公告)日：2011-02-15
申请号：US11410581
申请日：2006-04-24
申请人： Christian Koenig
发明人： Christian Koenig
IPC分类号： F02C6/04
CPC分类号： B64D35/00 , B64C11/02 , B64D27/02 , F01D7/02 , F01D15/12 , F02C3/08 , F02C3/085 , F02C3/145 , F02C6/206 , F02C7/275 , F02C7/36 , F02C9/58 , F05D2220/324 , F05D2220/325 , F05D2220/76 , F05D2260/4021 , F05D2260/74 , F05D2260/85 , Y02T50/673
摘要： A propeller or propeller drive, the propeller being carried by a support shaft (3) which projects from the body (53) of the missile or vehicle and about which the propeller rotates, the drive unit for the propeller being situated in front of the propeller (23) in the propulsion direction or in the propeller spinner (1). According to the invention it is provided that the drive unit has at least one gas turbine (55), optionally a multiple-stage gas turbine, which is secured to the drive shaft and which drives it or jointly rotates with it, and that the drive shaft (6) is traversed by the support shaft (3) or is mounted thereon in a rotating manner and drives the propeller (23), optionally by way of a gear mechanism (14) situated between the turbine (55) and the propeller (23).
摘要翻译：螺旋桨或螺旋桨驱动器，螺旋桨由支撑轴（3）承载，支撑轴（3）从导弹或车辆的主体（53）突出并且螺旋桨旋转，螺旋桨的驱动单元位于螺旋桨的前面（23）在推进方向上或在推进器旋转器（1）中。根据本发明，驱动单元具有至少一个燃气轮机（55），可选地是多级燃气轮机，其被固定到驱动轴并且驱动它或与其共同旋转，并且驱动器轴（6）由支撑轴（3）穿过或以旋转方式安装在其上，并且可选地通过位于涡轮机（55）和螺旋桨（55）之间的齿轮机构（14）驱动推进器（23） 23）。

20. 发明申请

US20070056291A1 Propeller or propeller drive 有权
标题翻译：螺旋桨或螺旋桨驱动
公开(公告)号：US20070056291A1
公开(公告)日：2007-03-15
申请号：US11410581
申请日：2006-04-24
申请人： Christian Koenig
发明人： Christian Koenig
IPC分类号： F02C6/04
CPC分类号： B64D35/00 , B64C11/02 , B64D27/02 , F01D7/02 , F01D15/12 , F02C3/08 , F02C3/085 , F02C3/145 , F02C6/206 , F02C7/275 , F02C7/36 , F02C9/58 , F05D2220/324 , F05D2220/325 , F05D2220/76 , F05D2260/4021 , F05D2260/74 , F05D2260/85 , Y02T50/673
摘要： A propeller or propeller drive, the propeller being carried by a support shaft (3) which projects from the body (53) of the missile or vehicle and about which the propeller rotates, the drive unit for the propeller being situated in front of the propeller (23) in the propulsion direction or in the propeller spinner (1). According to the invention it is provided that the drive unit has at least one gas turbine (55), optionally a multiple-stage gas turbine, which is secured to the drive shaft and which drives it or jointly rotates with it, and that the drive shaft (6) is traversed by the support shaft (3) or is mounted thereon in a rotating manner and drives the propeller (23), optionally by way of a gear mechanism (14) situated between the turbine (55) and the propeller (23).
摘要翻译：螺旋桨或螺旋桨驱动器，螺旋桨由支撑轴（3）承载，支撑轴（3）从导弹或车辆的主体（53）突出并且螺旋桨旋转，螺旋桨的驱动单元位于螺旋桨的前面（23）在推进方向上或在推进器旋转器（1）中。根据本发明，驱动单元具有至少一个燃气轮机（55），可选地是多级燃气轮机，其被固定到驱动轴并且驱动它或与其共同旋转，并且驱动器轴（6）由支撑轴（3）穿过或以旋转方式安装在其上，并且可选地通过位于涡轮机（55）和螺旋桨（55）之间的齿轮机构（14）驱动推进器（23） 23）。

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