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1. 发明公开

EP2617960A4 FIXED VANE-TYPE TURBO CHARGER 有权
标题翻译：涡轮增压器叶片
公开(公告)号：EP2617960A4
公开(公告)日：2016-11-16
申请号：EP11825124
申请日：2011-09-12
申请人： IHI CORP
发明人： ISHII MIKITO
IPC分类号： F02B39/00 , F01D9/04
CPC分类号： F01D25/24 , F01D9/045 , F01D25/125 , F02B37/24 , F05D2220/40 , F05D2230/642 , F05D2240/12 , F05D2260/38
摘要： The present invention relates to a fixed vane-type turbocharger provided with a fixed vane (15) in a conduit (9) between a bearing housing and a turbine housing (4). The fixed vane (15) is configured by a movable member (11) which is disposed on one of the mutually opposing front faces of the bearing housing and the turbine housing (4) so as to be capable of forward and backward movement, and by vanes (14) which are fixed to the front face of the movable member (11). A pressing means (16) is provided which presses the movable member (11) so that the distal ends of the vanes (14) are brought into pressure contact between the rear face of the movable member (11) and either the bearing housing or the turbine housing (4) with the other opposing front face of these. The pressing means (16) contacts the rear face of the movable means (11) within a range in the radial direction where the vanes (14) are disposed, and conducts pressing within this range.

2. 发明公开

EP3085888A1 TURBINENGEHÄUSE UND ZUGEHÖRIGER ABGASTURBOLADER 审中-公开
标题翻译： TURBINENGEHÄUSEUNDZUGEHÖRIGERABGASTURBOLADER
公开(公告)号：EP3085888A1
公开(公告)日：2016-10-26
申请号：EP16159778.6
申请日：2016-03-11
申请人： Bosch Mahle Turbo Systems GmbH & Co. KG
发明人： ERDEL, Florian
IPC分类号： F01D1/00 , F01D9/02 , F01D9/04
CPC分类号： F02B37/001 , F01D1/00 , F01D9/026 , F01D9/045 , F04D17/12 , F04D29/4206
摘要： Die vorliegende Erfindung betrifft ein Turbinengehäuse (1) eines Abgasturboladers (2) mit zwei spiralförmigen Abgasfluten (3,4), die über eine Trennwand (5) voneinander getrennt und nach radial außen durch das Turbinengehäuse (1) und nach radial innen durch jeweils eine Spiralzunge (6,7) begrenzt sind, wobei sich die beiden Spiralzungen (6,7) in entgegen gesetzter Richtung von der Trennwand (5) in Richtung des Turbinengehäuses (1) erstrecken.
Erfindungswesentlich ist dabei, dass sich die erste Spiralzunge (6) zwischen der Trennwand (5) und einem abgasrohrseitigen Bereich (9) des Turbinengehäuses (1) und die zweite Spiralzunge (7) zwischen der Trennwand (5) und einem lagergehäuseseitigen Bereich (8) des Turbinengehäuses (1) erstreckt und dass die beiden Spiralzungen (6,7) derart ausgebildet sind, dass bei einer steigenden thermomechanischen Belastung zuerst die erste Spiralzunge (6) versagt.
摘要翻译：排气涡轮增压器的涡轮机壳体可以包括经由隔板彼此分离的至少两个螺旋形排气通道。至少两个通道可以由涡轮机壳体径向地限定在外部，并且通过至少两个螺旋舌片径向地限定在内部。第一螺旋舌片可以与通道中的一个相关联，并且第二螺旋舌片可以与另一个通道相关联。至少两个螺旋舌片可以在朝向涡轮机壳体的方向上远离隔板的相反方向延伸。根据一个示例，至少两个螺旋舌片可以构造成使得在增加的热机械负载下，第一螺旋舌片在第二螺旋舌头之前失效。

3. 发明公开

EP3056691A1 VARIABLE DISPLACEMENT RADIAL TURBINE 审中-公开
标题翻译： RADIALTURBINE MITVERÄNDERLICHEMSCHLUCKVERMÖGEN
公开(公告)号：EP3056691A1
公开(公告)日：2016-08-17
申请号：EP16160028.3
申请日：2001-10-16
申请人： Mitsubishi Heavy Industries, Ltd.
发明人： Osako, Katsuyuki , Jinnai, Yasuaki
IPC分类号： F01D17/16 , F02B37/12
CPC分类号： F01D17/165 , F01D9/045 , F02B37/24 , F05D2220/40 , Y02T10/144
摘要： A variable displacement radial turbine comprising a plurality of movable nozzle blades (19) rotatably provided between opposed two side wall surfaces (14,15) around an outer periphery of a turbine blade wheel (7) by shaft bodies (20), respectively, and a clearance setting support pin (124,124') extending across between the two side wall surfaces (14,15)in order to maintain a distance between the two side wall surfaces (14,15) at an appropriate value. The support pin (124,124') is disposed at a position closer to a leading edge (19a) of one of the movable nozzle blades (19) than a position of the shaft body (20) of said movable nozzle blade (19) on the side of a pressure surface (19c) of said movable nozzle blade (19) without contacting said movable nozzle blade (19) when it is located at a maximum opening position (A).
摘要翻译：一种可变排量的径向涡轮机，包括分别由轴体（20）围绕涡轮机叶轮（7）的外周分别旋转地设置在相对的两个侧壁表面（14,15）之间的多个可移动喷嘴叶片（19），以及延伸穿过两个侧壁表面（14,15）之间的间隙设定支撑销（124,124'），以便将两个侧壁表面（14,15）之间的距离保持在适当的值。支撑销（124,124'）设置在比可移动喷嘴叶片（19）的轴体（20）的位置更接近可动喷嘴叶片（19）之一的前缘（19a）的位置，所述可动喷嘴叶片（19）的压力表面（19c）的侧面在位于最大打开位置（A）时不接触所述可动喷嘴刀片（19）。

4. 发明公开

EP2873830A1 TURBOCHARGER, TURBINE NOZZLE, AND SHIP 审中-公开
标题翻译： TURBOLADER UND SCHIFF
公开(公告)号：EP2873830A1
公开(公告)日：2015-05-20
申请号：EP14825080.6
申请日：2014-08-21
申请人： Mitsubishi Heavy Industries
发明人： SHIRAISHI, Keiichi
IPC分类号： F02B39/00 , B63H21/14 , F01D9/02 , F01D17/00 , F02B37/22
CPC分类号： F02B37/22 , F01D5/146 , F01D9/02 , F01D9/041 , F01D9/045 , F01D17/18 , F05D2220/40 , Y02T10/144
摘要： An object of the present invention is to provide a turbocharger, a turbine nozzle, and a ship that can improve turbine efficiency, and can effectively change an inflow area of exhaust gas that flows into the turbine nozzle according to an engine load. In a turbine nozzle (25), a plurality of blade tip portions (44) are provided spaced apart from each other in a peripheral direction, the blade tip portions (44) being provided between an outer peripheral side member (25b) and a partition member (42), and a plurality of blade root portions (45) are provided spaced apart from each other in the peripheral direction, the blade root portions (45) being provided between an inner peripheral side member (25a) and the partition member (42). Additionally, a trailing edge (45b) of a downstream side in a flow direction of exhaust gas of the blade root portion (45) is formed so as to be located closer to an upstream side in the flow direction of the exhaust gas than a trailing edge (44b) of the blade tip portion (44). Consequently, a throat width (S1) between the blade root portions (45, 45) adjacent to each other in the peripheral direction of the turbine nozzle (25) is set to be larger than a throat width (S2) between the blade tip portions (44, 44) adjacent to each other in the peripheral direction.
摘要翻译：本发明的目的是提供一种能够提高涡轮机效率的涡轮增压器，涡轮喷嘴和船舶，能够根据发动机负荷有效地改变流入涡轮喷嘴的排气的流入面积。在涡轮喷嘴（25）中，多个叶片尖端部分（44）沿圆周方向彼此间隔设置，叶片尖端部分（44）设置在外周侧部件（25b）与分隔部构件（42）和多个叶片根部（45）沿圆周方向彼此间隔设置，叶片根部（45）设置在内周侧构件（25a）和分隔构件（ 42）。此外，叶片根部（45）的排气的流动方向的下游侧的后缘（45b）形成为比排气体的流动方向更靠近排气的流动方向的上游侧叶片顶端部分（44）的边缘（44b）。因此，在涡轮喷嘴（25）的圆周方向上彼此相邻的叶片根部（45,45）之间的喉部宽度（S1）被设定为大于叶片前端部（44,44）在周向方向上彼此相邻。

5. 发明公开

EP2716878A4 NOZZLE BLADE 有权
标题翻译： JETS铲
公开(公告)号：EP2716878A4
公开(公告)日：2015-03-25
申请号：EP12789256
申请日：2012-05-24
申请人： IHI CORP
发明人： MORITA ISAO
IPC分类号： F01D17/16 , F02B37/24
CPC分类号： F01D17/16 , F01D5/141 , F01D9/045 , F01D17/165 , F02B37/24 , F02C6/12 , F05D2220/40 , F05D2240/121 , Y02T10/144
摘要： This relates to a nozzle blade in which the leading edge shape has a curved-line shape that is formed by the distance from the rotation axis of the nozzle blade to the leading edge changing depending on the nozzle blade height position, and the trailing edge shape has a straight-line shape that is formed by the distance from the rotation axis of the nozzle blade to the trailing edge being constant irrespective of the nozzle blade height position.

6. 发明公开

EP2807949A1 RADIAL VANE AND METHOD OF MANUFACTURING SAME 有权
标题翻译： RADIALERFLÜGELUND HERSTELLUNGSVERFAHRENDAFÜR
公开(公告)号：EP2807949A1
公开(公告)日：2014-12-03
申请号：EP13740912.4
申请日：2013-01-25
申请人： STB Higuchi Co., Ltd.
发明人： HIGUCHI, Izumi , UEBA, Yasushi , NISHIMURA, Hideaki , HIGUCHI, Masaki
IPC分类号： A46D3/04 , A46B9/04
CPC分类号： F01D9/045 , A46B3/04 , A46B13/001 , A46D3/04 , Y10T29/49336
摘要： Provided is a radial vane with which manufacturing is possible with superior economy, without incurring a cut loss associated with vane separation in a weld part of a thread bundle. With a longitudinal intermediate part of a contiguous bundle of threads being a fold-over part, both end parts of the fold-over part of the thread bundle are opened into radial shapes and superpositioned, leaving a space in the center part of the fold-over part, a ring-shaped fold-over part (12) is formed within the circumference of the space in the center part thereof. The outer part of the ring-shaped fold-over part (12) is welded in a ring shape, forming a ring-shaped core part (13). A through hole (11) is formed in the inner side of the fold-over part (12), and radial vane parts (14) are formed in which a plurality of thread materials (21) extend outward from the core part (13) toward the outer circumference side from all regions of the circumference direction. The ring-shaped fold-over part (12) is either an un-welded part or an incompletely welded part which protrudes in a dome shape in both surfaces and protrudes in an arch shape into the center, and is also efficacious as a boss part for gap adjustment when a plurality of radial vanes (10) are fixed in an axle, forming a brush head, as well as functioning simultaneously as a slide part which makes fixing easy, and as a grip part which anchors the fixed vanes.
摘要翻译：提供一种径向叶片，其可以以优越的经济性进行制造，而不会在螺纹束的焊接部分中产生与叶片分离相关的切口损失。由于连续的一束螺纹的纵向中间部分是折叠部分，所以螺纹束的折叠部分的两个端部部分被打开成径向形状并且叠加，在折叠部分的中心部分留下一个空间，在其中心部分的空间的圆周内形成环形折叠部分（12）。环形折叠部分（12）的外部部分被焊接成环形，形成环形芯部分（13）。在折叠部分（12）的内侧形成通孔（11），并且形成多个螺纹材料（21）从芯部（13）向外延伸的径向叶片部分（14）从圆周方向的所有区域朝向外周侧。环形折叠部分（12）是在两个表面中以圆顶形状突出并且以拱形突出到中心的未焊接部分或不完全焊接部分，并且也作为凸起部分有效用于在多个径向叶片（10）固定在轴上时形成刷头，同时作为使得固定的滑动部件同时起作用的间隙调节，以及锚定固定叶片的把手部分。

7. 发明公开

EP2805027A1 ABGASTURBOLADER 审中-公开
标题翻译：涡轮增压器
公开(公告)号：EP2805027A1
公开(公告)日：2014-11-26
申请号：EP13700611.0
申请日：2013-01-08
申请人： IHI Charging Systems International GmbH
发明人： IHLI, Thomas , DE SANTIS, Roberto
IPC分类号： F01D17/16
CPC分类号： F02B47/08 , F01D9/045 , F01D11/005 , F01D17/165 , F02C6/12 , F05D2220/40
摘要： The invention relates to an exhaust gas turbocharger, comprising at least one housing part (12), on which a guiding device (16) that is separate from the housing part (12) is at least partially arranged, said guiding device comprising two insert elements (18, 20) that are arranged at a distance from each other in an axial direction, a flow channel (22) thus being formed between the insert elements (18, 20), wherein guide blades of the guiding device (16), by means of which guide blades exhaust gas flowing through the flow channel (22) can be led away, are movably supported relative to the insert elements (18, 20) on at least one of the insert elements (18, 20) and wherein at least one first insert element (18) of the insert elements has at least one first wall area (30) extending at least substantially in a radial direction and at least one second wall area (32) connected thereto and extending at least substantially in the axial direction, which wall areas form a corner area (28) of the first insert element (18), wherein at least one recess (24, 26) is provided in the first wall area (30) and/or in the corner area (28) on a side (27) facing the housing part (12).

8. 发明公开

EP2707575A2 VARIABLE TURBINEN-/VERDICHTERGEOMETRIE 有权
标题翻译：可变涡轮/压缩机几何
公开(公告)号：EP2707575A2
公开(公告)日：2014-03-19
申请号：EP12707550.5
申请日：2012-03-02
申请人： Bosch Mahle Turbo Systems GmbH & Co. KG
发明人： LAUBENDER, Jochen , KRETH, Jens
IPC分类号： F01D5/12 , F01D5/14 , F01D5/18 , F01D17/16 , F02C6/12
CPC分类号： F02B37/24 , F01D5/147 , F01D9/045 , F01D17/165 , F05D2220/40 , F05D2230/21 , F05D2230/22 , F05D2240/12 , F05D2240/121 , F05D2240/125 , F05D2260/60 , Y02T10/144
摘要： The present invention relates to a variable turbine/compressor geometry (1), in particular for an exhaust-gas turbocharger of an internal combustion engine, preferably of a motor vehicle, having a blade bearing ring (2) and guide blades (3) which are mounted rotatably therein, and having a cover disc (4) which is arranged on the front side of the guide blades (3). It is essential to the invention that at least one guide blade (3) is penetrated by at least one gas-conducting channel (6, 6') which has at least one inlet opening (8, 8') in the region of a profile lug (7) and has an outlet opening (10, 10', 10'') on the front side (5) which is directed towards the cover disc (4) and/or on the underside (9) which is directed towards the blade bearing ring (2), and, as a result, generates an air cushion which reduces friction on the front side (5) and/or on the underside (9) during operation. As a result, hysteresis behaviour and the service life can be influenced positively.

9. 发明公开

EP1882821A1 Ensemble diffuseur-redresseur pour une turbomachine 有权转让
标题翻译： Diffusor-Gleichrichter-AnordnungfüreineStrömungsmaschine
公开(公告)号：EP1882821A1
公开(公告)日：2008-01-30
申请号：EP07290804.9
申请日：2007-06-28
申请人： SNECMA
发明人： Daguenet, Luc Henri Claude , Gandelot, Sandrine , Vieillefond, Guy
IPC分类号： F01D9/04 , F04D29/44
CPC分类号： F01D9/044 , F01D9/045 , F04D29/441 , F04D29/444 , F05D2230/237 , F05D2240/128 , F05D2250/52 , Y02T50/671
摘要： Ensemble diffuseur-redresseur (10) pour turboréacteur ou turbopropulseur d'avion, le diffuseur (12) comprenant des flasques annulaires (22, 24) reliés par des aubes (26) et le redresseur (14) comprenant des viroles cylindriques (28, 30) reliées par des aubes (32), les flasques annulaires et les viroles cylindriques étant formés de tôles auxquelles les aubes (26, 32) sont assemblées par brasure.
摘要翻译：组件（10）具有径向环形扩散器（12），其上游和下游环形凸缘（22,24）围绕环形燃烧室（20）的旋转轴线以螺旋方向由叶片（26）连接。环形圆柱形同步环（14）布置在扩散器的出口处，并且包括通过径向叶片（32）连接的外部和内部圆柱形圆柱体（28,30）。法兰和圆柱体由片材制成，刀片通过钎焊固定到其上。这些片材具有被结合并钎焊到刀片的端部并且通过激光预切形成的孔。

10. 发明公开

EP4417791A1 TURBOMACHINE WITH COMPRESSOR DIFFUSER BLEED FOR UNIFORM EXIT FLOW 审中-公开
公开(公告)号：EP4417791A1
公开(公告)日：2024-08-21
申请号：EP24153455.1
申请日：2024-01-23
申请人： Honeywell International Inc.
发明人： NASIR, Shakeel , MCCLINTIC, John , KRISE, Jeffrey
IPC分类号： F01D9/04 , F04D29/54 , F02C9/18
CPC分类号： F02C9/18 , F04D29/542 , F01D9/045 , F05D2260/60620130101 , F04D29/444 , F04D27/023 , F02C6/08 , F02C3/08
摘要： A turbomachine 20 includes a compressor 44, a combustor 56 disposed to receive the compressed air from the compressor through a flow path, and a diffuser 38 disposed in the flow path between the compressor and the combustor. A number of bleed holes 101 are disposed downstream in the flow path from the diffuser 38 and are configured to direct bleed air compressed by the compressor away from the combustor. The number of bleed holes 101 have a plural number of sizes configured to provide uniform compressor exit flow distribution around a circumference of the diffuser 38.

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