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21. 发明公开

EP3045677A1 TURBOCHARGER WITH AN ANNULAR ROTARY BYPASS VALVE 有权转让
标题翻译： TURBOLADER MITRINGFÖRMIGEMDREHUMLEITUNGSVENTIL
公开(公告)号：EP3045677A1
公开(公告)日：2016-07-20
申请号：EP16155499.3
申请日：2015-03-04
申请人： Honeywell International Inc.
发明人： LOMBARD, Alain , BRIBANT, Valerie , COSTEUX, Antoine
IPC分类号： F01D17/10 , F02B37/18
CPC分类号： F02B37/183 , F01D17/105 , F02C6/12 , F05D2210/12 , F05D2220/40 , F05D2250/411 , F05D2270/05 , Y02T10/144
摘要： A turbocharger includes an annular bypass passage with an annular bypass valve (70) disposed therein. The bypass valve (70) includes a fixed annular valve seat (72) and a rotary annular valve member (74) disposed against the valve seat (72). The valve member (74) is rotatable about the axis for varying a degree of alignment between orifices (73, 75) in the valve seat (72) and valve member (74) so as to form flow passages having a flow area A for exhaust gas. The orifices are shaped to provide a first phase of evolution of the flow area A from zero up to a value A 1 and then a second phase of evolution from the value A 1 up to a value A 2 , and such that the first and second phases have distinctly different slopes on a curve of flow area versus rotational position of the valve member, with a distinct break point in the curve between the first and second phases.
摘要翻译：涡轮增压器包括环形旁路通道，其中设置有环形旁通阀（70）。旁通阀（70）包括固定环形阀座（72）和抵靠阀座（72）设置的旋转环形阀构件（74）。阀构件（74）可围绕轴线旋转以改变阀座（72）和阀构件（74）中的孔（73,75）之间的对准程度，以形成具有用于排气的流动面积A的流动通道加油站。孔被成形为提供流动区域A的从零到达值A 1的演化的第一阶段，然后是从值A 1到值A 2的第二阶段演化，并且使得第一和第二阶段在相对于阀构件的旋转位置的流动面积曲线上的相位具有明显不同的斜率，在第一和第二相之间的曲线中具有明显的断点。

22. 发明公开

EP2998519A1 TURBINE ENGINE DIFFUSER ASSEMBLY WITH AIRFLOW MIXER 有权转让
标题翻译： TURBINENMOTORDIFFUSORANORDNUNG MIT LUFTKANALMISCHER
公开(公告)号：EP2998519A1
公开(公告)日：2016-03-23
申请号：EP15185959.2
申请日：2015-09-18
申请人： United Technologies Corporation
发明人： CUNHA, Frank J. , KOSTKA, Stanislav
IPC分类号： F01D9/06 , F02C6/06 , F23R3/02
CPC分类号： F23R3/04 , F01D9/02 , F01D9/065 , F02C6/06 , F02C7/04 , F02C9/16 , F05D2210/12 , F05D2210/13 , F05D2220/30 , F05D2240/35 , F23R3/005 , F23R3/02
摘要： A diffuser assembly is provided for a turbine engine. This diffuser assembly includes a diffuser module 50 with a combustor plenum 48 and a mixing chamber 70. The diffuser module 50 is configured to receive first and second airflows into the mixing chamber 70 and direct a mixed airflow out of the mixing chamber 70. The diffuser module 50 includes a mixer 102 configured to mix the first and the second airflows together within the mixing chamber 70 to provide the mixed airflow.
摘要翻译：为涡轮发动机提供扩散器组件。该扩散器组件包括具有燃烧器增压室48和混合室70的扩散器模块50.扩散器模块50构造成将第一和第二气流接收到混合室70中并将混合气流引导出混合室70。模块50包括配置成将混合室70内的第一和第二气流混合在一起以提供混合气流的混合器102。

23. 发明公开

EP2994627A2 DIFFUSER CASE STRUT FOR A TURBINE ENGINE 有权转让
标题翻译：扩压器壳体追求涡轮发动机
公开(公告)号：EP2994627A2
公开(公告)日：2016-03-16
申请号：EP14832432.0
申请日：2014-05-08
申请人： United Technologies Corporation
发明人： LYONS, Christopher B.
IPC分类号： F02C7/00 , F02C7/12 , F01D25/08
CPC分类号： F02C7/18 , F01D5/02 , F01D9/02 , F01D9/065 , F01D25/08 , F01D25/12 , F01D25/162 , F01D25/24 , F02C3/06 , F02C7/04 , F02C7/12 , F05D2210/12 , F05D2220/32 , F05D2220/3219 , F05D2240/12 , F05D2240/35 , F05D2260/211 , F05D2260/213 , Y02T50/676
摘要： An inner diffuser case for a turbine engine includes a fore gas path edge and an aft gas path edge defining a strut, wherein each of the fore gas path edge and the aft gas path edge include a gas path opening, a support cone structure extending radially outward from the strut, wherein the support cone structure is operable to structurally connect the strut to a turbine engine case, a diffuser case skirt structure extending radially inward from the strut, wherein the diffuser case skirt structure is operable to structurally connect the diffuser case strut to an inner support structure of the turbine engine, and at least one direct feed air passage passing radially through the strut including a radially outward upper mixing chamber opening and a radially inward direct air feed opening, the direct air feed opening is connected to a direct air feed.

24. 发明公开

EP2984300A1 ASYMMETRIC DOUBLE-ENTRY TURBINE 有权转让
标题翻译：非对称双进TURBINE
公开(公告)号：EP2984300A1
公开(公告)日：2016-02-17
申请号：EP14718696.9
申请日：2014-03-14
申请人： Imperial Innovations Limited
发明人： MARTINEZ-BOTAS, Ricardo , SAKAI, Masakazu
IPC分类号： F01D17/16 , F02B37/007 , F02B37/02 , F02B37/24 , F02C6/12 , F02M26/00
CPC分类号： F02M26/04 , F01D5/02 , F01D9/026 , F01D17/165 , F01D25/24 , F02B33/40 , F02B37/007 , F02B37/025 , F02B37/24 , F02C6/12 , F02M26/02 , F05D2210/12 , F05D2220/40 , F05D2240/24 , Y02T10/144
摘要： An asymmetric double-entry turbine is provided with a turbine housing that includes a first volute, a second volute and a turbine receiving bore. The first volute has a first exhaust gas inlet and a first exhaust gas outlet. The second volute has a second exhaust gas inlet and a second exhaust gas outlet. The turbine receiving bore is in fluid communication with the first exhaust gas outlet and the second exhaust gas outlet for conducting a flow of exhaust gas from the first exhaust gas outlet and the second exhaust gas outlet out in an axial direction. The first exhaust gas outlet has an angular opening amount of more than 180 degrees around the turbine receiving bore. The second exhaust gas outlet has an angular opening amount of less than 180 degrees around the turbine receiving bore.

25. 发明公开

EP2980384A1 INTAKE AIR COOLING DEVICE 有权转让
标题翻译： EINLASSLUFT-KÜHLVORRICHTUNG
公开(公告)号：EP2980384A1
公开(公告)日：2016-02-03
申请号：EP14775523.5
申请日：2014-01-28
申请人： Mitsubishi Hitachi Power Systems, Ltd.
发明人： KANEBAKO, Atsuhiko
IPC分类号： F02C3/30 , F02C7/143 , F04B49/06
CPC分类号： F02C7/1435 , F01D9/041 , F01D25/12 , F02C3/30 , F02C7/04 , F02C9/16 , F04B17/03 , F04B49/06 , F04B2201/1201 , F04B2203/0209 , F04B2205/09 , F05D2210/12 , F05D2220/32 , F05D2260/212 , F05D2270/311
摘要： An intake air cooling device (100) is configured so as to uniformly spray water into intake air even during partial operation. The intake air cooling device (100) is provided on the rear-stage side of a pre-filter (24) provided on the intake air inlet side of an air intake duct (12) for conducting intake air taken in from an intake air inlet (22) to a compressor (14), and cools the intake air by spraying the water thereinto. The intake air cooling device is provided with: nozzles (102) which spray the water into the intake air; water conduit pipes (104) having the nozzles arranged thereon in the axial direction thereof; and supply pumps (106) which supplies the water to the water conduit pipes, respectively. The water conduit pipes are endless bodies having different peripheral lengths.
摘要翻译：进气冷却装置（100）被构造成即使在部分操作期间也将水均匀地喷射到进气中。进气冷却装置（100）设置在设置在进气管（12）的进气入口侧的预过滤器（24）的后段侧，用于将从吸入空气入口（22）连接到压缩机（14），并且通过喷射水来冷却进气。进气冷却装置设置有：将水喷入吸入空气的喷嘴（102）在其轴向上具有喷嘴的水管道（104）; 以及将水分别供给到水管道的供水泵（106）。水管是具有不同周长的环形体。

26. 发明公开

EP2921653A1 TURBOCHARGER WITH AN ANNULAR ROTARY BYPASS VALVE 有权转让
标题翻译： TURBOLADER MITRINGFÖRMIGEMDREHUMLEITUNGSVENTIL
公开(公告)号：EP2921653A1
公开(公告)日：2015-09-23
申请号：EP15157651.9
申请日：2015-03-04
申请人： Honeywell International Inc.
发明人： Lombard, Alain , Bribant, Valerie , Costeux, Antoine
IPC分类号： F01D17/10 , F02B37/18
CPC分类号： F02B37/183 , F01D17/105 , F02C6/12 , F05D2210/12 , F05D2220/40 , F05D2250/411 , F05D2270/05 , Y02T10/144
摘要： A turbocharger includes an annular bypass passage with an annular bypass valve (70) disposed therein. The bypass valve includes a fixed annular valve seat (72) and a rotary annular valve member (74) disposed against the valve seat. The valve member (74) is rotatable about the axis for varying a degree of alignment between orifices (75) in the valve seat (72) and valve member (74) so as to form flow passages having a flow area A for exhaust gas. The orifices (75) are shaped to provide a first phase of evolution of the flow area A from zero up to a value A 1 and then a second phase of evolution from the value A 1 up to a value A 2 , and such that the first and second phases have distinctly different slopes on a curve of flow area versus rotational position of the valve member (74), with a distinct break point in the curve between the first and second phases.
摘要翻译：涡轮增压器包括环形旁路通道，其中设置有环形旁通阀（70）。旁通阀包括固定环形阀座（72）和抵靠阀座设置的旋转环形阀构件（74）。阀构件（74）能够围绕轴线旋转以改变阀座（72）和阀构件（74）中的孔口（75）之间的对准程度，从而形成具有排气流动面积A的流动通道。孔75被成形为提供流动区域A的从第一到第二进化阶段的第一阶段，然后是从值A 1到值A 2的演化的第二阶段，并且使得第一和第二相在流动面积对阀构件（74）的旋转位置的曲线上具有明显不同的斜率，在第一和第二相之间的曲线中具有明显的断点。

27. 发明公开

EP2744995A4 AIR INLET ARRANGEMENT AND METHOD OF MAKING THE SAME 有权
标题翻译：进气设备及其制造方法
公开(公告)号：EP2744995A4
公开(公告)日：2015-04-29
申请号：EP12825921
申请日：2012-08-17
申请人： GULFSTREAM AEROSPACE CORP
发明人： CONNERS TIMOTHY R , HENNE PRESTON A , HOWE DONALD C
IPC分类号： F02C7/04 , B64D33/02 , F02K1/04 , F02K1/46 , F02K3/02
CPC分类号： F02K1/46 , B64D33/02 , B64D2033/026 , B64D2033/0273 , B64D2033/0286 , F02C7/00 , F02C7/04 , F02C7/045 , F02K1/04 , F02K1/34 , F02K3/02 , F02K7/00 , F02K7/10 , F02K7/16 , F02K7/20 , F05D2210/12 , F05D2220/323 , F05D2220/80 , F05D2230/60 , F05D2250/70 , F05D2260/96 , Y10T29/49346 , Y10T137/0536
摘要： An inlet arrangement is disclosed herein for use with a supersonic jet engine configured to consume air at a predetermined mass flow rate when the supersonic jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed. The air inlet arrangement includes, but is not limited to, a cowl having a cowl lip and a center body coaxially aligned with the cowl. A protruding portion of the center body extends upstream of the cowl lip for a length greater than a conventional spike length. The protruding portion is configured to divert air flowing over the protruding portion out of a pathway of an inlet to the supersonic jet engine such that a remaining airflow approaching and entering the inlet matches the predetermined mass flow rate.

28. 发明授权

EP2191116B1 MULTI-STAGE TURBOCHARGER SYSTEM 有权
标题翻译：多级涡轮增压系统
公开(公告)号：EP2191116B1
公开(公告)日：2012-11-07
申请号：EP08806204.7
申请日：2008-09-04
申请人： Cummins Turbo Technologies Limited
发明人： GARRETT, Steven , RYDER, Owen, Alistair , ROBINSON, Lee, J. , MCEWAN, James, A.
IPC分类号： F02B37/013 , F02B37/16 , F02B37/18
CPC分类号： F02B37/004 , F02B37/001 , F02B37/002 , F02B37/007 , F02B37/013 , F02B37/16 , F02B37/18 , F02B37/183 , F02B39/00 , F02D9/06 , F05D2210/12 , F05D2220/40 , F05D2240/40 , F05D2270/3013 , Y02T10/144
摘要： A turbocharger system comprises a first relatively small turbocharger and a second relatively large turbocharger connected in series and an exhaust gas flow control valve. The exhaust control valve has an inlet port communicating with the exhaust gas flow upstream of the first turbine a first outlet port communicating with the exhaust flow downstream of said first turbine but upstream of said second turbine, and a second outlet port communicating with the exhaust flow downstream of said second turbine. The valve is operable to selectively permit or block flow through the first and second outlet ports.

29. 发明授权

EP1219800B1 Gasturbinenzyklus 有权
标题翻译：燃气轮机循环
公开(公告)号：EP1219800B1
公开(公告)日：2009-10-07
申请号：EP01128785.1
申请日：2001-12-04
申请人： Alstom Technology Ltd
发明人： Frutschi, Hans Ulrich, Dr.
IPC分类号： F02C3/34 , F02C3/04
CPC分类号： F02C3/30 , F01K25/103 , F02C1/10 , F02C3/20 , F02C3/34 , F02C7/08 , F02C7/143 , F05D2210/12

30. 发明公开

EP1748156A3 Sealing of a shaft of a geothermal steam turbine 审中-公开
标题翻译：轴密封件在地热汽轮机
公开(公告)号：EP1748156A3
公开(公告)日：2007-10-10
申请号：EP06117896.8
申请日：2006-07-26
申请人： ANSALDO ENERGIA S.P.A.
发明人： BRUZZONE, Marco
IPC分类号： F01D11/00 , F03G7/04
CPC分类号： F01D11/003 , F02C1/05 , F05D2210/12 , F05D2240/56 , F05D2240/57 , F16J15/3292 , F16J15/442
摘要： A geothermal steam turbine (11) has a casing (17) housing a succession of stages (15) and having a sleeve (26) through which projects an end portion (25) of a rotary shaft; and a sealing device (28) is provided between the sleeve (26) of the casing (17) and the end portion (25) of the shaft to prevent outside air from entering the turbine by means of a zero-clearance seal (29, 35, 38).

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