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1. 发明公开

EP3412891A1 IMPELLER, TURBOCHARGER, AND METHOD FOR FORMING FLOW FIELD FOR GAS IN IMPELLER AND TURBOCHARGER 有权
公开(公告)号：EP3412891A1
公开(公告)日：2018-12-12
申请号：EP16896982.2
申请日：2016-03-31
申请人： Mitsubishi Heavy Industries Engine & Turbocharger, Ltd.
发明人： YOSHIDA, Toyotaka , HOSHI, Toru , DAMMOTO, Yosuke , AKIYAMA, Yoji
IPC分类号： F02B39/00
CPC分类号： F01D5/048 , F01D17/165 , F02B37/24 , F02B39/00 , F02C6/12 , F05D2220/40 , F05D2250/712
摘要： A turbine wheel (12) is provided with: a disc (22) provided so as to be capable of rotating about a center axis (C); and a plurality of blades (23) provided to a disc surface (22f) at intervals in a circumferential direction, the blades (23) causing a gas guided in from radially outward leading edges (23f) to be expelled from trailing edges (23r) disposed on one side of each of the blades along the direction of the center axis (C). In each of the blades (23), in an area on one side along the direction of the center axis (C) including the trailing edge (23r), there is provided a concave surface (27) in which a positive-pressure surface (23p) on the rear side in a rotational direction (R) is recessed forward in the rotational direction (R), causing the gas to be dispersed entirely in the radial direction of the blade (23).

2. 发明授权

EP2549117B1 FAN AND FLUID DELIVERY DEVICE 有权
公开(公告)号：EP2549117B1
公开(公告)日：2018-12-12
申请号：EP11756114.2
申请日：2011-03-07
申请人： Sharp Kabushiki Kaisha
发明人： SHIRAICHI, Yukishige , OHTSUKA, Masaki
IPC分类号： F04D29/28 , F04D29/30 , F04D29/66 , F04D17/04
CPC分类号： F04D29/281 , B29C45/26 , B29L2031/08 , F04D17/04 , F04D17/08 , F04D17/10 , F04D25/02 , F04D29/26 , F04D29/282 , F04D29/283 , F04D29/30 , F04D29/384 , F04D29/4226 , F04D29/666 , F05D2240/301 , F05D2240/303 , F05D2240/304 , F05D2240/305 , F05D2240/306 , F05D2250/711 , F05D2250/712 , F05D2250/713 , Y02T50/673
摘要： A centrifugal fan includes a plurality of fan blades (21) arranged spaced apart from each other in a circumferential direction. The fan blade (21) has an inner edge portion (26) disposed on an inner peripheral side and an outer edge portion (27) disposed on an outer peripheral side. The fan blade (21) has a blade surface including a pressure surface and a suction surface. When cut along a plane orthogonal to a rotation axis of the fan, the fan blade (21) has a blade cross section having concave portions formed at the pressure surface and the suction surface. A plurality of fan blades (21) include fan blades (21A to 21E) having blade cross sections of different shapes. With such a configuration, the fan has an excellent air-blowing capacity while preventing noise. A molding die for use in production of the fan and a fluid feeder including the fan are also provided.

3. 发明授权

EP3032109B1 CENTRIFUGAL COMPRESSOR AND SUPERCHARGER 有权
公开(公告)号：EP3032109B1
公开(公告)日：2018-06-13
申请号：EP14834821.2
申请日：2014-07-30
申请人： IHI Corporation
发明人： BESSHO, Yasutaka
IPC分类号： F04D29/44 , F04D17/10 , F04D29/68 , F02B33/40
CPC分类号： F04D29/441 , F02B33/40 , F04D17/10 , F04D29/284 , F04D29/4233 , F04D29/681 , F05D2250/294 , F05D2250/712
摘要： An annular diffuser (27) is formed on an outlet side of a wheel (13) in a housing (5). A spiral scroll (31) is formed on an outlet side of the diffuser (27) in the housing (5). An annular concave part (37) is formed to be depressed to an inside in a radial direction in a boundary (35) between a shroud-side wall surface (27s) of the diffuser (27) and a wall surface (31w) of the scroll (31).

4. 发明公开

EP3194115A4 HIGH SPEED SPINDLE 审中-公开
公开(公告)号：EP3194115A4
公开(公告)日：2018-05-09
申请号：EP14902174
申请日：2014-09-17
申请人： GAL WAY METAL CUTTING TECH LTD
发明人： MILLER ZVI
IPC分类号： B23Q5/06 , B23Q5/04 , B23Q5/26
CPC分类号： B23Q5/06 , B23Q5/048 , B23Q11/1015 , F01D5/141 , F01D15/06 , F05D2220/30 , F05D2240/14 , F05D2240/30 , F05D2240/60 , F05D2250/712 , F16C19/184 , F16C2322/39
摘要： A spindle assembly configured to be assembled in a machining device. A front cover of the spindle assembly includes passages to allow high pressure fluid to flow towards the blades of the turbine and rotate the turbine; openings located at the front end of the front cover may allow low pressure fluid to flow out of the spindle assembly; passages extending from behind the turbine to the front end of the front cover may allow collection of low pressure fluids that flow towards the rear end of the spindle after hitting the blades of the turbine and to direct these fluids towards the front end of the front cover and out of the spindle assembly. The housing of the spindle assembly may include a rear section configured to be assembled onto the machining device.

5. 发明公开

EP3255249A1 GAS TURBINE ENGINE BLADE INCLUDING SQUEALER TIP POCKET 审中-实审转让
标题翻译：燃气轮机发动机叶片包括冷却器尖端口袋
公开(公告)号：EP3255249A1
公开(公告)日：2017-12-13
申请号：EP17174721.5
申请日：2017-06-07
申请人： United Technologies Corporation
发明人： COUTURE, Patrick D. , LEWIS, Scott D. , LANA, Kyle C.
IPC分类号： F01D5/20
CPC分类号： F01D5/18 , F01D5/20 , F02C3/04 , F05D2220/32 , F05D2230/21 , F05D2240/303 , F05D2240/304 , F05D2240/307 , F05D2250/711 , F05D2250/712
摘要： A gas turbine engine blade (100) includes a blade portion (110) having a leading edge (202) and a trailing edge (204). A first surface (206) connects the leading edge (202) to the trailing edge (204) and a second surface (208) connects the leading edge (202) to the trailing edge (204). A tip section (200) is located at a first end of the blade portion (110) and includes a pocket (232) protruding into the tip section (200) from an outermost end of the tip section (200). The pocket (232) has a first side wall (236) adjacent the first surface (206) and a second side wall (238) adjacent the second surface (208). At least one of the first side wall (236) and the second side wall (238) have a curve distinct from a curve of the corresponding adjacent surface.
摘要翻译：燃气涡轮发动机叶片（100）包括具有前缘（202）和后缘（204）的叶片部分（110）。第一表面（206）将前缘（202）连接到后缘（204），并且第二表面（208）将前缘（202）连接到后缘（204）。尖端部分（200）位于叶片部分（110）的第一端并且包括从尖端部分（200）的最外端伸入尖端部分（200）中的凹穴（232）。袋（232）具有与第一表面（206）相邻的第一侧壁（236）和与第二表面（208）相邻的第二侧壁（238）。第一侧壁（236）和第二侧壁（238）中的至少一个具有与相应的相邻表面的曲线不同的曲线。

6. 发明授权

EP2435662B1 TURBINE BASSE-PRESSION 有权转让
标题翻译：涡轮压缩机
公开(公告)号：EP2435662B1
公开(公告)日：2017-08-16
申请号：EP10728803.7
申请日：2010-05-21
申请人： Snecma
发明人： BELMONTE, Olivier , GILLANT, Grégory, Nicolas, Gérald
IPC分类号： F01D5/02 , F01D5/06
CPC分类号： F01D5/066 , F05D2250/712 , Y02T50/671

7. 发明公开

EP3199762A1 GAS TURBINE ENGINE COMPONENT 有权转让
标题翻译：燃气轮机发动机组件
公开(公告)号：EP3199762A1
公开(公告)日：2017-08-02
申请号：EP17153157.7
申请日：2017-01-25
申请人： United Technologies Corporation
发明人： LEWIS, Scott D. , ZELESKY, Mark F. , MONGILLO, Dominic J.
IPC分类号： F01D5/18 , F01D9/06 , F23R3/00
CPC分类号： F01D5/186 , F01D9/065 , F05D2240/11 , F05D2240/81 , F05D2250/711 , F05D2250/712 , F05D2250/75 , F05D2260/202 , F23R2900/03042 , Y02T50/676
摘要： A gas turbine engine component having a cooling hole (60;106) includes a first wall having a cooling hole inlet (110), a second wall generally opposite the first wall and having a cooling hole outlet (116), a metering section (112) extending downstream from the inlet (110) and having a hydraulic diameter ( d h ), and a diffusing section (114) extending from the metering section (112) to the outlet (116). The metering section (112) includes a substantially convex first surface (134) extending from a first end (140) to a second end (142), a substantially concave second surface (136) extending from a third end (144) to a fourth end (146), and first and second curved portions (152,154) connecting the ends (140,142,144,146) of the first and second surfaces (134,136).
摘要翻译：具有冷却孔（60; 106）的燃气涡轮发动机部件包括具有冷却孔入口（110）的第一壁，与第一壁大致相对且具有冷却孔出口（116）的第二壁，计量部分（112 ）从入口（110）向下游延伸并且具有水力直径（dh），以及从计量部分（112）延伸到出口（116）的扩散部分（114）。计量部分（112）包括从第一端（140）延伸到第二端（142）的基本上凸的第一表面（134），从第三端（144）延伸到第四端（146）以及连接第一和第二表面（134,136）的端部（140,142,144,146）的第一和第二弯曲部分（152,154）。

8. 发明授权

EP1903183B1 Tip ramp turbine blade 有权
标题翻译：尖端斜面涡轮叶片
公开(公告)号：EP1903183B1
公开(公告)日：2017-07-19
申请号：EP07114605.4
申请日：2007-08-20
申请人： GENERAL ELECTRIC COMPANY
发明人： Klasing, Kevin Samuel , Lee, Ching-Pang , Vitt, Paul Hadley , Keith, Brian David
IPC分类号： F01D5/20 , F01D5/18
CPC分类号： F01D5/20 , F05D2240/307 , F05D2250/292 , F05D2250/70 , F05D2250/711 , F05D2250/712 , F05D2260/20 , Y02T50/673 , Y02T50/676

9. 发明公开

EP3187712A1 NACELLE SHORT INLET 有权转让
标题翻译： NACELLE短进口
公开(公告)号：EP3187712A1
公开(公告)日：2017-07-05
申请号：EP16206722.7
申请日：2016-12-23
申请人： United Technologies Corporation
发明人： QIU, Yuan J. , MALECKI, Robert E. , LORD, Wesley K.
IPC分类号： F02C7/04 , B64D33/02
CPC分类号： F04D29/547 , B64D33/02 , B64D2033/0286 , F02C7/04 , F02K3/06 , F04D29/325 , F05D2220/323 , F05D2240/14 , F05D2240/30 , F05D2250/711 , F05D2250/712
摘要： A fan assembly for a gas turbine engine (20) includes a fan (42) including a plurality of fan blades (92). Each fan blade extends radially outwardly from a fan hub to a blade tip (94). The plurality of blade tips define a fan diameter (D). A nacelle (80) surrounds the fan (42) and defines a fan inlet upstream of the fan (42), relative to an airflow direction into the fan (42). The nacelle (80) has a forwardmost edge defining an inlet length from the forwardmost edge to a leading edge of a fan blade of the plurality of fan blades (92). A ratio of inlet length to fan diameter (D) is between 0.20 and 0.45. A nacelle (80) inner surface defines a nacelle flowpath. The nacelle flowpath has a convex throat portion (122) and a concave diffusion portion (126) between the throat portion and the leading edge of the fan blade at a bottommost portion of the nacelle (80).
摘要翻译：用于燃气涡轮发动机（20）的风扇组件包括包括多个风扇叶片（92）的风扇（42）。每个风扇叶片从风扇轮毂径向向外延伸到叶片尖端（94）。多个叶片尖端限定了风扇直径（D）。相对于进入风扇（42）的气流方向，机舱（80）围绕风扇（42）并在风扇（42）的上游限定风扇入口。机舱（80）具有最前边缘，该前边缘限定从多个风扇叶片（92）的风扇叶片的最前边缘到前缘的入口长度。入口长度与风扇直径之比（D）在0.20和0.45之间。发动机舱（80）内表面限定机舱流动路径。机舱流道在机舱（80）的最底部处具有位于风扇叶片的喉部和前缘之间的凸形喉部部分（122）和凹形扩散部（126）。

10. 发明公开

EP3187690A1 SYSTEM FOR AN INLET GUIDE VANE SHROUD AND BAFFLE ASSEMBLY 审中-公开
标题翻译：进口导向叶片和挡板组件的系统
公开(公告)号：EP3187690A1
公开(公告)日：2017-07-05
申请号：EP16196832.6
申请日：2016-11-02
申请人： General Electric Company
发明人： LOBOCKI, Marcin Jacek , WARDECKI, Wiktor Karol , KULESA, Joseph Charles , STASZEWSKI, Maciej
IPC分类号： F01D9/04 , F01D11/00 , F01D11/08
CPC分类号： F04D29/542 , F01D9/04 , F01D11/00 , F01D11/08 , F02C3/04 , F02C7/04 , F04D29/083 , F04D29/325 , F05D2220/32 , F05D2240/126 , F05D2240/35 , F05D2250/712 , F05D2260/201
摘要： A system for an inlet guide vane shroud and baffle assembly 300 includes a shroud 216. The shroud includes a first end 304 configured to couple to an annular support member 302 of the gas turbine engine 100, and a second end 324. The shroud also includes a distal end 310 including an axially aft extending lip 311, and a seal assembly configured to form a seal with an annular set of rotating teeth 309 on a rotor 208 of the gas turbine engine. The shroud further includes an arcuate shroud body 322 extending between the distal end and the second end. The shroud and baffle assembly also includes a baffle 306 coupled to an aft side 347a of the shroud. The baffle includes a radially outward end 354 coupled to the aft side, a radially inward end 362 coupled to the axially aft extending lip, and an arcuate baffle body 358, 360, 363 extending there between. Both the shroud and the baffle extend circumferentially about a central axis.
摘要翻译：用于入口导向叶片护罩和挡板组件300的系统包括护罩216.护罩包括构造成联接到燃气涡轮发动机100的环形支撑构件302的第一端部304和第二端部324.护罩还包括包括轴向向后延伸唇缘311的远端310以及构造成与燃气涡轮发动机的转子208上的环形成组的旋转齿309形成密封的密封组件。护罩还包括在远端和第二端之间延伸的弧形护罩主体322。护罩和挡板组件还包括联接到护罩的后侧347a的挡板306。挡板包括联接到后侧的径向向外端部354，联接到轴向向后延伸唇部的径向向内端部362和在其间延伸的弓形挡板主体358,360,363。护罩和挡板都围绕中心轴线周向延伸。

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