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91. 发明授权

EP1205634B1 Turbine blade and use thereof 有权
标题翻译：涡轮叶片及其使用
公开(公告)号：EP1205634B1
公开(公告)日：2013-01-23
申请号：EP01309235.8
申请日：2001-10-31
申请人： GENERAL ELECTRIC COMPANY
发明人： Demers, Daniel Edward , Acquaviva, Paul Joseph , Manning, Robert Francis
IPC分类号： F01D5/08 , F01D5/18
CPC分类号： F01D11/04 , F01D5/081 , F01D5/187 , F05D2240/81 , F05D2260/202 , F05D2260/22141 , Y02T50/676

92. 发明公开

EP2534340A1 TURBINE VANE HOLLOW INNER RAIL 有权
标题翻译：一个涡轮机叶片的中空内指导
公开(公告)号：EP2534340A1
公开(公告)日：2012-12-19
申请号：EP11711875.2
申请日：2011-03-30
申请人： Siemens Aktiengesellschaft
发明人： JONES, Richard , PACEY, Andy
IPC分类号： F01D5/18 , F01D9/02 , F01D9/04 , F01D9/06 , F01D11/00 , F01D25/12
CPC分类号： F01D25/12 , B23P15/04 , F01D5/189 , F01D9/02 , F01D9/042 , F01D9/047 , F01D9/06 , F01D11/001 , F01D11/005 , F05D2240/12 , F05D2240/81 , F05D2240/91 , F05D2260/201 , Y10T29/49316
摘要： The present invention relates to a guide vane device (100) for a turbine. The guide vane device (100) comprises an inner platform (101) with a through hole (301) forming a fluid channel for a cooling fluid, wherein the inner platform (101) extends in a circumferential direction (109) around a shaft (304) of the turbine. The guide vane device (100) further comprises a hollow aerofoil (102) with a cooling opening for exchanging the cooling fluid passing the through hole (301) into or from the hollow aerofoil (102), wherein the hollow aerofoil (102) is fixed to a first surface (201) of the inner platform (101). The guide vane device (100) further comprises a rail (103) comprising a recess (104) with a cooling fluid passage (105) forming a passage for the cooling fluid to the through hole (301), wherein the rail (103) is fixed to a second surface (106) of the inner platform (101) and the rail (103) extends along the second surface (106) in the circumferential direction (109) around the shaft (304). The cooling fluid passage (105) comprises in the circumferential direction (109) at least the dimension of the through hole (301).

93. 发明授权

EP1132574B1 Gas turbine cooled stationary blade 有权
标题翻译：用于燃气涡轮机冷却的定子
公开(公告)号：EP1132574B1
公开(公告)日：2012-12-19
申请号：EP01104054.0
申请日：2001-02-20
申请人： MITSUBISHI HEAVY INDUSTRIES, LTD.
发明人： Kuwabara, Masamitsu, Takasago Machinery Works , Tomita, Yasuoki, Takasago Machinery Works , Shirota, Akihiko, Takasago Machinery Works , Ito, Eisaku, Takasago Research & Development Cent.
IPC分类号： F01D5/18 , F01D9/04
CPC分类号： F01D5/187 , F05D2240/81 , F05D2260/22141

94. 发明公开

EP2063118A3 Method and system to facilitate cooling turbine engines 审中-公开
标题翻译：方法和系统用于简化涡轮发动机的冷却
公开(公告)号：EP2063118A3
公开(公告)日：2012-12-12
申请号：EP07117321.5
申请日：2007-09-27
申请人： GENERAL ELECTRIC COMPANY
发明人： Lee, Ching-Pang , Estill, Eric Alan , Laflen, James Harvey , Vitt, Paul Hadley , Wymore, Michael Elliot
IPC分类号： F03D9/00
CPC分类号： F01D25/12 , F01D9/04 , F01D11/08 , F01D11/24 , F01D25/246 , F05D2240/11 , F05D2240/81 , F05D2250/314 , Y02T50/671 , Y02T50/676 , Y10T29/49236
摘要： An engine assembly including a nozzle assembly. The nozzle assembly includes an inner band, an outer band (183) including an aft flange (504) and a radial inner surface (522), the aft flange including a plurality of cooling holes (508) configured to direct cooling fluid (526) therefrom at an oblique discharge angle (α), and at least one airfoil vane (510) extending between the inner band and the outer band.

95. 发明公开

EP1882814A3 Turbine vanes with airfoil-proximate cooling seam 审中-公开
标题翻译：涡轮机叶片与型材靠近冷却缝
公开(公告)号：EP1882814A3
公开(公告)日：2012-09-12
申请号：EP07013301.2
申请日：2007-07-06
申请人： Siemens Energy, Inc.
发明人： Marini, Bonnie D. , Schiavo, Anthony L.
IPC分类号： F01D5/08 , F01D5/14 , F01D9/04 , F01D11/00
CPC分类号： F01D5/147 , F01D5/081 , F01D9/041 , F01D11/005 , F05D2240/81
摘要： Aspects of the invention relate to a turbine vane (30) in which the inner and outer platforms (52, 54) are located substantially entirely on either the pressure side (36) or the suction side (38) of the airfoil (32). When a plurality of such vanes (30) are installed in the turbine, a seam (78) is formed by the circumferential end (56) of the inner and outer platforms (52, 54) and a portion of the airfoil (32) of a neighboring vane (30). During engine operation, a high pressure coolant (82) is supplied to at least one of the platforms (52, 54). The coolant (82) can leak through the seam (78). Because the seam (78) is located proximate the airfoil (32), the coolant leakage through the seam (78) can be productively used to cool the transition region (86) between the vane platforms (52, 54) and the airfoil (32). In addition to such cooling benefits, aspects of the invention can result in a potential increase in engine efficiency as well as component life.

96. 发明公开

EP1826360A3 Turbine bucket platform cooling circuit and method 审中-公开
标题翻译：装置和方法用于冷却燃气涡轮叶片平台
公开(公告)号：EP1826360A3
公开(公告)日：2012-06-13
申请号：EP07102391.5
申请日：2007-02-14
申请人： GENERAL ELECTRIC COMPANY
发明人： VELTRE, Louis , MACARIAN, Christopher Arda
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/81 , F05D2250/185 , F05D2260/202 , F05D2260/205
摘要： In a turbine bucket having an airfoil portion (212) and a root portion with a platform (216) at an interface between the airfoil portion and the root portion, a platform cooling arrangement including: a cooling passage (224,226) defined in the platform (216) to extend along at least a portion of a concave, pressure side (228) of the airfoil portion (212), at least one cooling medium inlet to said cooling passage extending from an airfoil cooling medium cavity (230,244) in a vicinity of an axial center of the airfoil portion, and at least one outlet opening (242,248) for expelling cooling medium from said cooling passage.

97. 发明公开

EP2458159A1 Gas turbine of the axial flow type 有权
标题翻译：轴流式燃气轮机
公开(公告)号：EP2458159A1
公开(公告)日：2012-05-30
申请号：EP11190892.7
申请日：2011-11-28
申请人： Alstom Technology Ltd
发明人： Khanin, Alexander Anatolievich , Kostege, Valery
IPC分类号： F01D11/10
CPC分类号： F01D11/10 , F05D2240/11 , F05D2240/81 , F05D2260/201 , F05D2260/205
摘要： The invention relates to a gas turbine (30) of the axial flow type, comprising a rotor with alternating rows of air-cooled blades (32) and rotor heat shields, and a stator with alternating rows of air-cooled vanes (31) and stator heat shields (36) mounted on a vane carrier (40), whereby the stator coaxially surrounds the rotor to define a hot gas path (39) in between, such that the rows of blades (32) and stator heat shields (36), and the rows of vanes (31) and rotor heat shields are opposite to each other, respectively, and a row of vanes (31) and the next row of blades (32) in the downstream direction define a turbine stage (TS), and whereby the blades (32) are provided with outer blade platforms (34) at their tips.
A reduction in cooling air mass flow and leakage in combination with an improved cooling and effective thermal protection of critical parts within the turbine stages of the turbine is achieved by providing within a turbine stage (TS) means (43-48) to direct cooling air that has already been used to cool, especially the airfoils of the vanes (31) of the turbine stage (TS), into a first cavity (41) located between the outer blade platforms (34) and the opposed stator heat shields (36) for protecting the stator heat shields (36) against the hot gas and for cooling the outer blade platforms (34).
摘要翻译：本发明涉及一种轴流式燃气轮机（30），其包括具有交替排空气冷却叶片（32）和转子隔热罩的转子，以及具有交替行空气冷却叶片（31）和（40）上的定子隔热罩（36），其中定子同轴地围绕转子以在其间限定热气体路径（39），使得成排的叶片（32）和定子隔热罩（36），并且叶片排（31）和转子隔热罩分别彼此相对，并且在下游方向上的一排叶片（31）和下一排叶片（32）限定涡轮机级（TS），其中，并且由此叶片（32）在其尖端处设置有外叶片平台（34）。通过在涡轮机级（TS）装置（43-48）内提供冷却空气质量流量和泄漏的减少以及对涡轮机的涡轮机级内的关键部件的改进的冷却和有效的热保护，已经用于冷却尤其是涡轮机级（TS）的叶片（31）的翼型件进入位于外叶片平台（34）和相对的定子隔热罩（36）之间的第一腔室（41）用于保护定子隔热罩（36）抵抗热气体并用于冷却外部叶片平台（34）。

98. 发明公开

EP2458152A2 Gas turbine of the axial flow type 有权
标题翻译：轴流式燃气轮机
公开(公告)号：EP2458152A2
公开(公告)日：2012-05-30
申请号：EP11190902.4
申请日：2011-11-28
申请人： Alstom Technology Ltd
发明人： Khanin, Alexander Anatolievich
IPC分类号： F01D5/20 , F01D11/10 , F01D25/24
CPC分类号： F01D5/225 , F01D11/10 , F01D11/12 , F01D25/246 , F05D2240/11 , F05D2240/81 , F05D2260/205 , F05D2300/5021
摘要： A gas turbine (30) of the axial flow type comprises a rotor with alternating rows of air-cooled blades (20) and rotor heat shields, and a stator with alternating rows of air-cooled vanes (21) and stator heat shields (27) mounted on inner rings (26), whereby the stator coaxially surrounds the rotor to define a hot gas path (22) in between, such that the rows of blades (20) and stator heat shields (27), and the rows of vanes (21) and rotor heat shields are opposite to each other, respectively, and a row of vanes (21) and the next row of blades (20) in the downstream direction define a turbine stage (TS), and whereby the blades (20) are provided with outer blade platforms (45) at their tips.
An efficient cooling and long life-time is achieved by providing outer blade platforms (45), which comprise on their outside a plurality of teeth (46a-c) running parallel to each other in the circumferential direction and being arranged one after the other in the direction of the hot gas flow, whereby said teeth (46a-c) are divided into first and second teeth (46a; 46b-c), the second teeth (46b-c) being located downstream of the first teeth (46a), the first teeth (46a) are opposite to a downstream projection (33) of the adjacent vanes (21) of the turbine stage (TS), and the second teeth (46b-c) are opposite to the respective stator heat shields (27).
摘要翻译：轴流类型的燃气轮机（30）包括具有交替排空气冷却叶片（20）和转子隔热罩的转子，以及具有交替排空气冷却叶片（21）和定子隔热罩（27）的定子）安装在内环（26）上，由此定子同轴地围绕转子以在其之间限定热气体路径（22），使得叶片排（20）和定子隔热罩（27）以及叶片排（21）和转子隔热罩分别彼此相对，并且在下游方向上的一排叶片（21）和下一排叶片（20）限定涡轮机级（TS），并且其中叶片（20））在它们的尖端处设有外部叶片平台（45）。通过提供外叶片平台（45）来实现有效的冷却和长的使用寿命，所述外叶片平台（45）在其外侧上包括多个在圆周方向上彼此平行延伸的齿（46a-c）并且一个接一个地依次布置（46a-c）被分成第一和第二齿（46a; 46b-c），第二齿（46b-c）位于第一齿（46a）的下游，第一齿46a与涡轮机级TS的相邻叶片21的下游突出部33相对，并且第二齿46b-c与相应的定子隔热罩27相对，。

99. 发明授权

EP2256297B1 Gas turbine vane with improved cooling 有权转让
标题翻译：燃气涡轮叶片具有改进的冷却
公开(公告)号：EP2256297B1
公开(公告)日：2012-05-30
申请号：EP09160581.6
申请日：2009-05-19
申请人： Alstom Technology Ltd
发明人： McFeat, Jose Anguisola , Kreiselmaier, Erich , Nagler, Christoph , Riazantsev, Sergei
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/188 , F01D9/02 , F05D2240/81 , F05D2260/201

100. 发明公开

EP2110513A3 Reduced weight blade for a gas turbine engine 审中-公开
标题翻译：具有减小的重量的叶片
公开(公告)号：EP2110513A3
公开(公告)日：2012-05-09
申请号：EP09250721.9
申请日：2009-03-13
申请人： United Technologies Corporation
发明人： Spangler, Brandon W.
IPC分类号： F01D5/14
CPC分类号： F01D5/147 , F01D5/187 , F05D2220/321 , F05D2240/81 , F05D2250/291 , F05D2260/202 , F05D2260/941
摘要： A rotor blade (34) for a gas turbine engine having an edge buttress (56T) having an aperture (72). A method of reducing rotor blade weight includes removing material from within a truss area bounded by a platform section (52), an internal airfoil cooling passage (64), and an underplatform fillet (66T).

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