公开(公告)号：US20140341716A1

公开(公告)日：2014-11-20

申请号：US14369522

申请日：2011-12-30

Applicant: Jinju Sun ,  Ke Wang ,  Peng Song

Inventor： Jinju Sun ,  Ke Wang ,  Peng Song

IPC: F03B3/02 ,  F03B11/00 ,  F03B3/18

CPC classification number: F03B3/02 ,  F01D1/08 ,  F01D5/025 ,  F01D9/026 ,  F01D17/165 ,  F01D25/145 ,  F03B3/183 ,  F03B11/006 ,  F03B11/02 ,  F05B2210/11 ,  F05D2210/11 ,  F05D2250/131 ,  Y02E10/223 ,  Y02E10/226

Abstract: A cryogenic liquid turbine is provided, wherein, an impeller end of the rotor and a nozzle assembly are received into a cavity of a volute (1), and a main part of the volute (1) is put into a perlite cold box (3); an insulation pad (2) is used between the volute (1) and a machine housing (9) to insulate heat; an impeller outlet is connected to a diffuser pipe (20). A nozzle assembly is connected to the machine housing (9) by a nozzle compression flange (27); a nozzle compression plate adjusts a compactness of nozzle vanes (18) by a disc spring (25); a nozzle turntable (14) is axially and rotatably connected on a nozzle chassis (17), and adjusts the nozzle vane stagger angle by a adjusting mechanism passing through the volute (1); impeller shroud side seal is axially fixed on the nozzle compression flange (27), and a shaft seal (5) is axially fixed on a seal gas part (4); the seal gas part (4) and an oil seal (6) are axially fixed on the machine housing (9) by a bolt (15). The cryogenic liquid turbine uses a cold barrier for reducing coldness loss, decreases a flow loss, improves operation reliability and provides convenience of orientating and installing a complete machine in an axial direction.

Abstract translation: 提供了一种低温液体涡轮机，其中，转子的叶轮端和喷嘴组件被容纳在蜗壳（1）的空腔中，并且将蜗壳（1）的主要部分放入珍珠岩冷箱（3 ）; 在蜗壳（1）和机壳（9）之间使用绝缘垫（2）来隔热; 叶轮出口连接到扩散管（20）。 喷嘴组件通过喷嘴压缩凸缘（27）连接到机器壳体（9）; 喷嘴压缩板通过盘簧（25）调节喷嘴叶片（18）的致密度; 喷嘴转台（14）轴向和可旋转地连接在喷嘴底座（17）上，并通过通过蜗壳（1）的调节机构调节喷嘴叶片交错角度; 叶轮护罩侧密封件轴向固定在喷嘴压缩凸缘（27）上，轴密封件（5）轴向固定在密封气体部件（4）上; 密封气体部分（4）和油封（6）通过螺栓（15）轴向地固定在机器壳体（9）上。 低温液体涡轮机使用冷屏障来减少冷却损失，降低流量损失，提高操作可靠性，并提供沿轴向定向和安装整个机器的方便。

公开(公告)号：US07654094B2

公开(公告)日：2010-02-02

申请号：US10589976

申请日：2004-03-09

Applicant: Manabu Yagi ,  Kuniyoshi Tsubouchi ,  Tadaharu Kishibe ,  Susumu Nakano ,  Satoshi Dodo

Inventor： Manabu Yagi ,  Kuniyoshi Tsubouchi ,  Tadaharu Kishibe ,  Susumu Nakano ,  Satoshi Dodo

IPC: F02C6/08

CPC classification number: F01D1/08 ,  F01D5/187 ,  F01D17/165 ,  F02C3/00

Abstract: A turbine nozzle (2) that, among components constructing a turbine, reaches particularly high temperature is efficiently cooled with a relatively simple structure. A double casing structure in which a turbine casing (7) is provided outside a turbine shell (5) is formed. The turbine casing (7) functions as a flow path (24) for compressed air (20→21) before combustion. The turbine shell (5) covers a turbine nozzle (2) and a radial turbine impeller (3) and forms flow paths (15, 16) for combustion gas (10→11→12→13). The compressed air (21) before combustion flowing in the flow path (24), for compressed air, having air-tightness between itself and the outside air is blown to the turbine nozzle (2) through a through-hole (51) penetrating both wall surfaces of the turbine shell (5) so that the turbine nozzle (2) is evenly cooled and the compressed air used to cool the turbine nozzle is made to flow toward the turbine impeller (3).

Abstract translation: 在构成涡轮机的部件达到特别高的温度下的涡轮喷嘴（2）以相对简单的结构被有效地冷却。 形成涡轮壳体（7）外侧的涡轮壳体（5）的双壳体结构。 在燃烧之前，涡轮机壳体（7）用作用于压缩空气（20-> 21）的流动路径（24）。 涡轮壳体（5）覆盖涡轮喷嘴（2）和径向涡轮叶轮（3）并形成用于燃烧气体（10-> 11-> 12-> 13）的流动路径（15,16）。 在流动路径（24）中流动的压缩空气（21）之间的压缩空气（其自身与外部空气之间具有气密性）通过贯穿两者的通孔（51）吹送到涡轮喷嘴（2） 涡轮壳体（5）的壁表面，使得涡轮喷嘴（2）被均匀地冷却，并且使用于冷却涡轮喷嘴的压缩空气流向涡轮机叶轮（3）。

公开(公告)号：US07404299B2

公开(公告)日：2008-07-29

申请号：US10526966

申请日：2003-09-05

Applicant: Kenneth William Patterson Drysdale ,  Paul Thomas Eves ,  Robert Thomas Casey

Inventor： Kenneth William Patterson Drysdale ,  Paul Thomas Eves ,  Robert Thomas Casey

IPC: F25B49/00 ,  F25B1/00

CPC classification number: F01D1/026 ,  F01D1/023 ,  F01D1/08 ,  F01D15/005 ,  F25B11/02 ,  F25B2400/141

Abstract: A turbine for generating power has a rotor chamber, a rotor rotatable about a central axis within the rotor chamber, and at least one nozzle for supplying a fluid from a fluid supply to the rotor to thereby drive the rotor and generate power. The flow of the fluid from the nozzle exist is periodically interrupted by at least one flow interrupter means, thereby raising a pressure of the fluid inside the nozzle. A thermo-dynamic cycle is also disclosed including a compressor, a first turbine downstream of the compressor, a heat exchanger located downstream of the first turbine and operable to reject heat from the cycle to another thermodynamic cycle, an evaporator downstream of the heat exchanger and a second turbine downstream of the evaporator and upstream of the compressor.

Abstract translation: 用于发电的涡轮机具有转子室，能够围绕转子室内的中心轴旋转的转子，以及至少一个用于将流体从流体供给器供给到转子的喷嘴，从而驱动转子并产生动力。 存在来自喷嘴的流体的流动由至少一个流动断续器装置周期性地中断，从而提高喷嘴内的流体的压力。 还公开了一种热动态循环，其包括压缩机，压缩机下游的第一涡轮机，位于第一涡轮机下游的热交换器，其可操作以将循环中的热量排除到另一热力循环，热交换器下游的蒸发器， 在蒸发器下游的第二涡轮机和压缩机的上游。

公开(公告)号：US3558084A

公开(公告)日：1971-01-26

申请号：US3558084D

申请日：1968-06-05

Applicant: ROBERT B COTTON

Inventor： COTTON ROBERT B

IPC: B64F1/06 ,  F01D1/02 ,  F01D1/08

CPC classification number: F01D1/026 ,  B64F1/06 ,  F01D1/08

Abstract: A gas flow turbine for use in conjunction with a jet engine includes a series of radially disposed blades mounted about a periphery of a circular support wheel. The edges of the blades are substantially free of obstruction to minimize impediment to the flow of gas directed against them. This causes the turbine wheel to derive a substantial thrust from the gas flowing against it without materially impeding such flow. A convenient form of such turbine includes slightly curved blades centrally mounted in cantilever manner to a rotatable disc with their ends extending therefrom. Despite the minimal reaction imparted to the wheel by the gases, substantial energy is derived from the gases discharged from a jet engine without materially reducing the engine''s efficiency. The turbine''s energy may be advantageously utilized for a multitude of purposes including general augmentation of jet engine thrust, particularly for improving efficiency of launching thrust and auxiliary uses in conjunction with jet engine exhaust including electric power generation.

公开(公告)号：US2944786A

公开(公告)日：1960-07-12

申请号：US38635853

申请日：1953-10-15

Applicant: THOMPSON RAMO WOOLDRIDGE INC

Inventor： ANGELL PIERCE T ,  ANDERSON ROBERT J ,  HOPPER MALCOLM M

IPC: F01D1/08 ,  F01D9/02 ,  F01D17/14

CPC classification number: F01D9/026 ,  F01D1/08 ,  F01D17/146

公开(公告)号：US2280585A

公开(公告)日：1942-04-21

申请号：US23869938

申请日：1938-11-03

Applicant: PETER KAPITZA

Inventor： PETER KAPITZA

IPC: F01D1/08 ,  F25B9/06

CPC classification number: F01D1/08 ,  F25B9/06 ,  Y10S62/91

公开(公告)号：US1186726A

公开(公告)日：1916-06-13

申请号：US3170315

申请日：1915-06-02

Applicant: ALLEN JOHN D

Inventor： ALLEN JOHN D

CPC classification number: F01D1/08

公开(公告)号：US20190234301A1

公开(公告)日：2019-08-01

申请号：US16254820

申请日：2019-01-23

Applicant: NUOVO PIGNONE TECNOLOGIE SRL

Inventor： Giuseppe IURISCI ,  Paola DI FESTA ,  Francesco CANGIOLI ,  Davide BILIOTTI

IPC: F02C1/02 ,  F02C7/32 ,  F01D15/12 ,  F01D13/00 ,  F01D15/06 ,  F01D5/02 ,  F01D1/08

CPC classification number: F02C1/02 ,  F01D1/08 ,  F01D5/02 ,  F01D5/04 ,  F01D5/043 ,  F01D13/003 ,  F01D15/06 ,  F01D15/12 ,  F02C6/16 ,  F02C7/32 ,  F05D2220/62 ,  F05D2260/211

Abstract: A multi-stage turboexpander and a method for generating mechanical power therewith are disclosed. The multi-stage turboexpander includes a casing and a shaft, arranged for rotation in the casing. The shaft is supported by a first bearing at a first shaft end portion and a second bearing at a second shaft end portion. A first radial impeller and a second radial impeller are arranged between the first bearing and the second bearing on the shaft for co-rotation therewith around a rotation axis.

公开(公告)号：US09982539B2

公开(公告)日：2018-05-29

申请号：US14266283

申请日：2014-04-30

Applicant: DUERR CYPLAN Ltd.

Inventor： Frank Eckert

IPC: F01D1/08 ,  F01D25/30 ,  F01D1/02 ,  F01D1/06

CPC classification number: F01D1/08 ,  F01D1/026 ,  F01D1/06 ,  F01D25/30

Abstract: Turbomachines having guide ducts are disclosed. One disclosed example turbomachine includes a rotor rotatable about an axis of rotation and having rotor blade ducts, a housing having housing ducts to allow the inflow or outflow of working medium and guide blade ducts fixed in the housing, where the rotor blade ducts are in fluid communication with the housing ducts via the guide blade ducts.

公开(公告)号：US08096777B2

公开(公告)日：2012-01-17

申请号：US11989934

申请日：2007-02-09

Applicant: Takao Yokoyama ,  Hirotaka Higashimori ,  Motoki Ebisu ,  Takashi Shiraishi

Inventor： Takao Yokoyama ,  Hirotaka Higashimori ,  Motoki Ebisu ,  Takashi Shiraishi

IPC: F01D5/14

CPC classification number: F01D5/141 ,  F01D1/08 ,  F01D5/048 ,  F05D2220/40 ,  F05D2250/611 ,  F05D2250/711 ,  F05D2250/712 ,  F05D2250/713

Abstract: A mixed flow turbine or radial turbine suppresses a rapid increase in load applied on a leading edge of a blade, and can reduce incidence loss. The mixed flow turbine or radial turbine includes a hub, and a plurality of blades provided on an outer circumference surface of the hub at substantially equal intervals. The camber line of the blade section is convex-curved to the rotational direction side as seen entirely from a leading edge side toward trailing edge side. On a leading edge section of the blade, there is provided an inflected section that is inflected so that a camber line in a sectional surface along the outer circumference surface is concave-curved to the rotational direction side.

Abstract translation: 混合涡轮机或径向涡轮机抑制施加在叶片的前缘上的载荷的快速增加，并且可以减少入射损失。 混合流动涡轮机或径向涡轮机包括毂，以及设置在轮毂的外周表面上的大致相等间隔的多个叶片。 叶片部分的弧形线从整个从前缘侧朝向后缘侧观察到的是向旋转方向侧凸曲面。 在叶片的前缘部分上设置有弯曲部，该弯曲部被弯曲，使得沿着外周面的截面中的外倾线在旋转方向侧是凹曲的。