专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

41. 发明专利

JP4033303B2 Multistage turbine with a single blade row and a gas turbine using the same 有权
公开(公告)号：JP4033303B2
公开(公告)日：2008-01-16
申请号：JP2005107211
申请日：2005-04-04
申请人：独立行政法人宇宙航空研究開発機構
发明人：識岩瀬 , 喜夫齊藤
IPC分类号： F01D1/12
CPC分类号： F01D1/12 , F01D5/142 , F02C3/073 , F05D2240/12 , Y02T50/673

42. 实用新型

JPS6415703U 失效
公开(公告)号：JPS6415703U
公开(公告)日：1989-01-26
申请号：JP10898587
申请日：1987-07-17
IPC分类号： F01D1/12

43. 发明专利

JPS6354155B2 失效
公开(公告)号：JPS6354155B2
公开(公告)日：1988-10-26
申请号：JP3928981
申请日：1981-03-18
申请人： SECR DEFENCE BRIT
发明人： KORIN ANDORYUU MIRAA TEIRAA
IPC分类号： F01D1/12 , F04D19/00 , F04D23/00 , F04D29/54

44. 发明专利

JPS5523322A AXIALLFLOW TURBINE 失效
公开(公告)号：JPS5523322A
公开(公告)日：1980-02-19
申请号：JP9453178
申请日：1978-08-04
申请人： MITSUBISHI HEAVY IND LTD
发明人： TAKENO SHINYA
IPC分类号： F01D1/12
摘要： PURPOSE:To provide an arrangement for multiple-stage axial-flow turbine, in which partition plates and rotor blades are both divided into an outer peripheral portion and an inner central portion, whereby it is enabled to reduce the axial length and the entire weight of the axial-flow turbine without affecting its performance. CONSTITUTION:High-pressure and high-temperature steam or gas introduced into steam chamber 60 is passed through the outer peripheral portions 21, 31 respectively of partition plates and rotor blades and then enters into steam chamber 70. In the steam chamber 70, steam flow is reversed, and passing through inner central portions 22, 32 respectively of the partition plates and rotor blades, discharged into exhaust chamber 80. Thus, in accordance with the arrangement of this invention, steam flows in two reversed passages in the turbine casing. Accordingly, it is enabled to reduce diameter of the center shaft and axial length required for the same number of stages and also to reduce the weight of rotors 10. Further, since thrust force acted to rotors 10 and deflection of partition plates are cancelled on the inner and outer sides of the same, since pressure distribution at the front and back of the partition plates and rotor blades is reversed in the turbine casing. Thus, thickness of partition plates 20 can be made small and thrust bearing 90 can be made compact.

45. 发明授权

EP3181866B1 GAS TURBINE ENGINE FOR AN AIRCRAFT 有权
公开(公告)号：EP3181866B1
公开(公告)日：2018-07-04
申请号：EP15382630.0
申请日：2015-12-16
申请人： Airbus Operations, S.L.
发明人： GARDE LA CASA, Alexandre
IPC分类号： F02C7/10 , F02C3/14 , F01D1/12 , B64D27/10 , B64D41/00 , F01D5/02 , F01D15/10 , F01D15/12 , F01D17/10 , F02C3/04 , F02C7/08 , F02C9/18 , F01D9/04
CPC分类号： F02C7/08 , B64D27/10 , B64D41/00 , B64D2041/002 , F01D1/12 , F01D5/02 , F01D9/041 , F01D15/10 , F01D15/12 , F01D17/105 , F02C3/04 , F02C3/145 , F02C7/10 , F02C9/18 , F05D2220/323 , F05D2220/50 , F05D2240/35 , F05D2240/60 , Y02T50/671
摘要： A gas turbine engine (1) for an aircraft comprising a compressor (3), a combustion chamber (7), and a turbine (5) having at least one stator (8, 10), and at least one rotor (9, 11). Each stator and rotor formed by a plurality of blades, a fluid channel formed between two consecutive blades, and each blade having two opposing surfaces. The compressor (3) is in fluid communication with a first group of stator channels (28), and the combustion chamber (7) is in fluid communication with a second group of stator channels (29), such that heat exchange can be performed through two opposing surfaces of at least one stator blade. The outer and the inner walls (2, 4) defining a duct for the passage of the heated fluid through the rotor blades, and the outer wall (4) being also arranged for directing the compressed air towards the combustion chamber (7).

46. 发明公开

EP2412430A4 BLADED REACTOR FOR THE PYROLYSIS OF HYDROCARBONS 有权转让
标题翻译：铲反应器的烃类热
公开(公告)号：EP2412430A4
公开(公告)日：2015-07-22
申请号：EP09842387
申请日：2009-07-07
申请人： COOLBROOK OY
发明人： BUSHUEV VLADIMIR ANDREEVICH
IPC分类号： B01J3/08 , B01J6/00 , B01J19/00 , B01J19/18 , F01D1/12 , F01D1/16 , F01D5/02 , F01D5/12 , F01D5/14 , F01D25/24 , F02C3/16 , F02C6/10 , F02C6/18
CPC分类号： F01D1/12 , B01J6/008 , B01J19/0066 , B01J19/18 , F01D1/16 , F01D5/022 , F01D5/142 , F01D25/24 , F02C3/16 , F02C6/10 , F02C6/18
摘要： A bladed reactor for pyrolysis of hydrocarbons comprises a rotor with blades (3) they form an axial-flow blade cascade, a fixed torus-shaped hoop (10) that adjoins the tips of said blades, and a housing (5) that encloses the hoop and a rotor periphery so that a passage having a ring shape of its meridian section is formed. One or more partitions are installed in the passage, an inlet port (18) is located directly after each partition while an outlet port (19) is located directly in front of each partition. Nozzle vanes (20) forming a nozzle cascade are installed upstream of the blade cascade, and diffusing vanes (21) forming a diffusing cascade are installed downstream of the blade cascade. There is a vaneless space (22) between the exit from the defusing cascade and the entry into the nozzle cascade. A group of nozzle vanes arranged directly after each partition may be separated off from the remaining nozzle vanes by a bulkhead so that a channel is formed which connects the corresponding inlet port (18) with separated group of nozzle vanes to simplify the reactor starting. Geometrical parameters of the nozzle and diffusing cascades can vary in the circumferential direction to provide the identical pressure at an inlet of the blade cascade throughout a length thereof and to provide the identical pressure at an outlet of the blade cascade throughout the length thereof, which reduces radial leakages through gaps between the rotor and the housing.

47. 发明申请

WO2008029269A1 MOTEUR A TURBINE A GAZ 审中-公开
标题翻译：气体涡轮发动机
公开(公告)号：WO2008029269A1
公开(公告)日：2008-03-13
申请号：PCT/IB2007/002636
申请日：2007-09-20
申请人： FAUCONNIER, Bruno
发明人： FAUCONNIER, Bruno
IPC分类号： F01D1/02 , F02C3/045 , F01D1/12
CPC分类号： F01D1/026 , F01D1/12 , F02C3/045
摘要： Turbine à gaz dont le compresseur et la turbine radiale ne forment qu'un seul élément, et permettant de remédier aux problèmes de refroidissement des aubes de turbines et d'avoir moins de pièces en mouvement, d'être plus légère, facile d'entretien avec un potentiel plus important qu'un moteur quatre-temps. Il comporte un orifice d'entrée d'air puis un compresseur-turbine radial formant un seul et même élément compressant et alimentant en air la chambre de combustion, ce même compresseur- turbine transformant une partie de l'énergie des gaz de combustion en énergie mécanique. La turbine comporte un carter (1), une entrée d'air (7), puis un compresseur-turbine (4) (turcomp) alimentant en air dans sa partie basse la chambre de combustion (9). Les gaz sont transformés en énergie mécanique par le compresseur- turbine (4) (turcomp) dans sa partie supérieure, puis évacués dans l'échappement (10). Des cloisons servant de déflecteurs sont intercalées (6-6a et 5). La turbine selon l'invention est particulièrement destinée à l'aviation de tourisme et d'affaire et de transport dans des versions turbopropulseurs. Il peut aussi équiper les hélicoptères. En version réacteur, il peut équiper l'aviation d' affaire.
摘要翻译：其中压缩机和径向涡轮机形成但是一个元件的燃气轮机，所述涡轮机克服了与涡轮叶片的冷却相关的问题，具有较少的运动部件并且更轻便，易于维护并且具有比四冲程更大的潜力发动机。它包括进气孔，随后是径向涡轮压缩机，其形成一个元件压缩空气并将其供应到燃烧室，该相同的涡轮压缩机将一些燃烧气体的能量转换成机械能。涡轮机包括壳体（1），空气进口（7）以及涡轮压缩机（4）（turcomp），其向下方供应燃烧室（9）中的空气。气体由其上部的涡轮压缩机（4）（turcomp）转化为机械能，然后排放到排气（10）中。插入作为偏转器的挡板（6-6a和5）。根据本发明的涡轮机特别用于在涡轮螺旋桨发动机版本中的快乐和商业航空和运输。它也可以安装在直升机上。在喷气发动机版本中，它可以用于商务航空旅行。

48. 发明申请

WO00015948A1 TOROIDAL TURBINE 审中-公开
公开(公告)号：WO00015948A1
公开(公告)日：2000-03-23
申请号：PCT/RU1998/000285
申请日：1998-09-14
IPC分类号： F01D1/12 , F01D1/08
CPC分类号： F01D1/12
摘要： The present invention pertains to the field of turbine machines and can be used as a small-dimension turbine actuator. The toroidal turbine includes a body as well as a working wheel mounted on bearings and surrounding said body so as to define a gap, wherein the body and the working wheel define together a toroidal working channel. The turbine also includes a plurality of working vanes and a separator which are arranged in the channel and are respectively mounted on the wheel and on the body, as well as inlet and outlet ducts that communicate with the channel on the various sides of the separator. The turbine is further fitted with a system for relieving the radial load applied on the bearings. The toroidal working channel comprises gaskets at the end surfaces of the wheel and of the body, and is made at its median cross section in the form of two semi-oval components. The inlet duct communicates with the channel through a nozzle having its slot offset relative to the wheel rotation plane that crosses the small semi-axes of the channel semi-oval components, while the outlet duct communicates with the channel through a window.
摘要翻译：本发明涉及涡轮机的领域，并且可以用作小尺寸涡轮致动器。环形涡轮机包括主体以及安装在轴承上并围绕所述主体的工作轮以限定间隙，其中主体和工作轮将环形工作通道一起限定。涡轮机还包括布置在通道中并分别安装在车轮和车身上的多个工作叶片和分离器，以及与分离器各侧通道连通的入口和出口管道。涡轮机还装有用于减轻施加在轴承上的径向载荷的系统。环形工作通道包括在车轮和车身的端面处的垫片，并且以其两个半椭圆形部件的中间横截面制成。入口管道通过一个喷嘴连通，该喷嘴的槽口相对于与通道半椭圆形部件的小半轴交叉的车轮旋转平面偏移，同时出口管道通过窗口与通道连通。

49. 发明申请

WO2011080584A4 PROPULSEUR A HAUTE PERFORMANCE, INDÉPENDANT DU MILIEU EXTÉRIEUR 审中-公开
公开(公告)号：WO2011080584A4
公开(公告)日：2011-07-07
申请号：PCT/IB2010/003391
申请日：2010-12-29
申请人： LY, Gilbert
发明人： LY, Gilbert
IPC分类号： F01D1/10 , F01D1/12 , F01D1/14 , F03B3/10 , F03B17/00 , F03G7/10
摘要： L'invention concerne un dispositif de propulsion écologique, permettant d'obtenir une poussée optimale et indépendante du milieu extérieur. Il est constitué d'une Turbine spéciale du Type Francis (1) d'où, le fluide est éjecté axialement à la sortie de l'aube (1'), avec une vitesse relative, W2t et est recueilli dans un certain espace libre d'une Pompe radiale droite (2). Sous l'action de la force centrifuge, la limite des lignes de courant forme une barrière virtuelle fixe, Y t empêchant ainsi le fluide centrifugé d'atteindre le fond de la Pompe dans la zone de l'espace libre, MNBCPQ; ce qui élimine la force antagoniste exercée sur cette zone. Il en résulte que la force de propulsion exercée par le fluide sur la Turbine reste intacte. A la sortie de la Pompe, le fluide est réinjecté axialement avec une vitesse relative, W 2p dans une bâche (4) pour réalimenter la Turbine. Il y a donc échange d'énergie entre la Pompe et la Turbine qui forment un circuit fermé, l'ensemble étant entraîné par un moteur (10). On démontre que la force de propulsion P = (1/2) pπω 2 r 4 ; p étant la masse volumique du fluide centrifugé en Kg/m 3 ; ω, la vitesse angulaire de la Turbine en rad/s; r, son rayon en mètre et P en Newtons. Le calcul montre que la poussée produite est très importante; ledit propulseur peut servir à produire de l'énergie mécanique partout dans l'espace, et en particulier à propulser les engins volants plus performants.

50. 发明申请

WO02034408A1 A CENTRIFUGAL SEPARATOR HAVING A ROTOR AND DRIVING MEANS THEREOF 审中-公开
标题翻译：具有转子和驱动装置的离心分离器
公开(公告)号：WO02034408A1
公开(公告)日：2002-05-02
申请号：PCT/SE2001/002284
申请日：2001-10-19
IPC分类号： B01D53/06 , B04B5/00 , B04B5/08 , B04B5/12 , B04B9/06 , F01D1/12 , F01D1/14
CPC分类号： F01D1/14 , B04B5/005 , B04B5/08 , B04B5/12 , B04B9/06 , B04B2005/125 , F01D1/12
摘要： In a centrifugal separator, the rotor (19) of which is adapted to be driven by means of a gaseous driving fluid, the rotor itself supports a ring of turbine blades (34) extending around the rotational axis (R) of the rotor. A stationary nozzle (40) is adapted to direct a flow of the driving fluid towards the ring of turbine members (34). After the driving fluid has passed between the turbine blades (34) and has influenced them for driving of the centrifugal rotor, it enters a reversing chamber (41) formed by a stationary reversing member (42). In the reversing chamber the driving fluid is caused to change its direction and is then conducted again towards the ring of turbine members (34) in order to be utilized a second time for driving of the centrifugal rotor.
摘要翻译：在离心分离器中，其转子（19）适于通过气体驱动流体驱动，转子本身支撑围绕转子的旋转轴线（R）延伸的涡轮叶片（34）环。固定喷嘴（40）适于将驱动流体的流动引向涡轮机构件（34）的环。在驱动流体在涡轮叶片（34）之间通过并且已经影响它们用于驱动离心转子的驱动流体之后，它进入由固定反向构件（42）形成的反转室（41）。在换向室中，使驱动流体改变其方向，然后再次朝着涡轮机构（34）的环传导，以便第二次用于驱动离心式转子。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式