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1. 发明公开

EP2894301A1 Stator heat shield segment 审中-公开
标题翻译：定子热屏蔽段
公开(公告)号：EP2894301A1
公开(公告)日：2015-07-15
申请号：EP14151020.6
申请日：2014-01-14
申请人： ALSTOM Technology Ltd
发明人： Kostege, Valery , Ivanov, Artem , Drozdov, Alexey , Chekanov, Alexander
IPC分类号： F01D11/24
CPC分类号： F01D9/06 , F01D11/08 , F01D11/12 , F01D11/122 , F01D25/14
摘要： The invention relates to a stator heat shield segment (10) for a gas turbine, comprising: an outside plate (20) facing a hot gas path of the gas turbine; an inside plate (30) facing away from the outside plate and exposed to cooling air; at least one serpentine cooling channel (100) disposed between the outside plate and the inside plate, the serpentine cooling channel comprises straight portions (104, 110, 112) extending parallelly with each other, bent portions (106, 108) connecting adjacent strait portions respectively, an inlet riser portion (102) for introducing coolant disposed perpendicularly to the serpentine cooling channel at one end of the serpentine channel; and an outlet portion (114) disposed at an opposite end of the serpentine channel.
摘要翻译：本发明涉及一种用于燃气轮机的定子热屏蔽段（10），包括：面向燃气轮机的热气路径的外板（20）内板（30），其远离外板并暴露于冷却空气; 至少一个设置在外板和内板之间的蛇形冷却通道（100），蜿蜒冷却通道包括彼此平行延伸的直线部分（104,110,112），连接相邻的直线部分的弯曲部分（106,108）一个入口立管部分（102），用于在蛇形通道的一端垂直于蛇形冷却通道引入冷却剂; 和设置在蛇形通道的相对端的出口部分（114）。

2. 发明公开

EP2458163A2 Gas turbine of the axial flow type 审中-公开
标题翻译：轴流式燃气轮机
公开(公告)号：EP2458163A2
公开(公告)日：2012-05-30
申请号：EP11190649.1
申请日：2011-11-24
申请人： Alstom Technology Ltd
发明人： Khanin, Alexander Anatolievich , Kostege, Valery
IPC分类号： F01D25/12
CPC分类号： F01D25/12 , F01D5/187 , F05D2240/126 , F05D2240/15 , 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 (36) and air-cooled rotor heat shields, and a stator with alternating rows of air-cooled vanes (33) and air-cooled stator heat shields (38) mounted on a vane carrier (31), whereby the stator coaxially surrounds the rotor to define a hot gas path (32) in between, such that the rows of blades (36) and stator heat shields (38), and the rows of vanes (33) and rotor heat shields are correlated with each other, respectively, and a row of vanes (33) and the next row of blades (36) in the downstream direction define a turbine stage (TS).
A substantial reduction of the consumption of cooling air is achieved by providing within a turbine stage (TS) means (39-44) to reuse the cooling air that has already been used to cool, especially the airfoils of, the vanes (33) of the turbine stage (TS), for cooling the stator heat shields (38) of said turbine stage (TS) downstream of the vanes (33).
摘要翻译：本发明涉及轴流式燃气轮机（30），其包括具有交替行空气冷却叶片（36）和空气冷却转子隔热屏的转子，以及具有交替排空气冷却叶片（ 33）和空气冷却定子热防护件（38）安装在叶片承载件（31），由此所述定子同轴地围绕所述转子之间，以限定热气体通路（32）上，使得叶片的行（36）和定子热防护件（38），以及叶片（33）和转子热防护件的行彼此分别相关，和叶片的排（33）和叶片在下游方向上的下一行（36）限定了涡轮级（TS）。通过在涡轮级（TS）装置（39-44）内提供以重新使用已经用于冷却叶片（33）的叶片（33）的冷却空气来冷却冷却空气消耗的实质性减少，涡轮级（TS），用于冷却叶片（33）下游的所述涡轮级（TS）的定子隔热罩（38）。

3. 发明公开

EP2458155A2 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：EP2458155A2
公开(公告)日：2012-05-30
申请号：EP11190895.0
申请日：2011-11-28
申请人： Alstom Technology Ltd
发明人： Khanin, Alexander Anatolievich , Kostege, Valery
IPC分类号： F01D9/00 , F01D5/20
CPC分类号： F01D9/00 , F01D11/08 , F02C7/18 , F05D2240/11 , F05D2260/20 , F05D2260/205
摘要： The invention relates to a gas turbine (35) of the axial flow type, comprising a rotor with alternating rows of air-cooled blades (40) and rotor heat shields, and a stator with alternating rows of air-cooled vanes (41) and stator heat shields (47) mounted on inner rings (46), whereby the stator coaxially surrounds the rotor to define a hot gas path (42) in between, such that the rows of blades (40) and stator heat shields (47), and the rows of vanes (41) and rotor heat shields are opposite to each other, respectively, and a row of vanes (41) and the next row of blades (40) in the downstream direction define a turbine stage (TS), and whereby the blades (40) of the turbine stage (TS) are each provided with a blade crown (32) at their tips and the vanes (41) of the turbine stage (TS) are each provided with an outer vane platform (38).
A reduction in cooling air mass flow and an improved cooling and effective thermal protection of critical parts within the turbine stages of the turbine is achieved by adapting the stator heat shields (47) and outer vane platforms (38) within the turbine stage (TS) to one another such that air (37) leaking through the joints between the outer vane platforms (38) and the adjacent stator heat shields (47) into the hot gas path (42) is directed onto the blade crown (32) of the blades (40).
摘要翻译：本发明涉及轴流式燃气轮机（35），其包括具有交替排空气冷却叶片（40）和转子隔热罩的转子，以及具有交替排空气冷却叶片（41）和定子隔热罩47安装在内环46上，由此定子同轴地包围转子以在其间限定热气通路42，使得成排的叶片40和定子隔热罩47，并且叶片排41和转子隔热罩分别彼此相对，并且沿着下游方向的一排叶片41和下一排叶片40限定涡轮级TS，并且由此涡轮机级（TS）的叶片（40）在它们的尖端处分别设置有叶片冠部（32），并且涡轮机级（TS）的叶片（41）各自设置有外部叶片平台（38）。通过使涡轮机级（TS）内的定子隔热罩（47）和外部叶片平台（38）适应，冷却空气质量流量的减少以及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使得通过外叶片平台（38）和相邻定子隔热罩（47）之间的接头泄漏到热气路径（42）中的空气（37）被引导到叶片的叶片冠部（32）上（40）。

4. 发明公开

EP2458163A3 Gas turbine of the axial flow type 审中-公开
标题翻译：轴流燃气涡轮
公开(公告)号：EP2458163A3
公开(公告)日：2014-11-26
申请号：EP11190649.1
申请日：2011-11-24
申请人： Alstom Technology Ltd
发明人： Khanin, Alexander Anatolievich , Kostege, Valery
IPC分类号： F01D25/12
CPC分类号： F01D25/12 , F01D5/187 , F05D2240/126 , F05D2240/15 , 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 (36) and air-cooled rotor heat shields, and a stator with alternating rows of air-cooled vanes (33) and air-cooled stator heat shields (38) mounted on a vane carrier (31), whereby the stator coaxially surrounds the rotor to define a hot gas path (32) in between, such that the rows of blades (36) and stator heat shields (38), and the rows of vanes (33) and rotor heat shields are correlated with each other, respectively, and a row of vanes (33) and the next row of blades (36) in the downstream direction define a turbine stage (TS).
A substantial reduction of the consumption of cooling air is achieved by providing within a turbine stage (TS) means (39-44) to reuse the cooling air that has already been used to cool, especially the airfoils of, the vanes (33) of the turbine stage (TS), for cooling the stator heat shields (38) of said turbine stage (TS) downstream of the vanes (33).

5. 发明公开

EP2458155A3 Gas turbine of the axial flow type 有权
标题翻译：轴流燃气涡轮
公开(公告)号：EP2458155A3
公开(公告)日：2013-07-10
申请号：EP11190895.0
申请日：2011-11-28
申请人： Alstom Technology Ltd
发明人： Khanin, Alexander Anatolievich , Kostege, Valery
IPC分类号： F01D9/00 , F01D5/20 , F01D11/08 , F02C7/18
CPC分类号： F01D9/00 , F01D11/08 , F02C7/18 , F05D2240/11 , F05D2260/20 , F05D2260/205
摘要： The invention relates to a gas turbine (35) of the axial flow type, comprising a rotor with alternating rows of air-cooled blades (40) and rotor heat shields, and a stator with alternating rows of air-cooled vanes (41) and stator heat shields (47) mounted on inner rings (46), whereby the stator coaxially surrounds the rotor to define a hot gas path (42) in between, such that the rows of blades (40) and stator heat shields (47), and the rows of vanes (41) and rotor heat shields are opposite to each other, respectively, and a row of vanes (41) and the next row of blades (40) in the downstream direction define a turbine stage (TS), and whereby the blades (40) of the turbine stage (TS) are each provided with a blade crown (32) at their tips and the vanes (41) of the turbine stage (TS) are each provided with an outer vane platform (38).
A reduction in cooling air mass flow and an improved cooling and effective thermal protection of critical parts within the turbine stages of the turbine is achieved by adapting the stator heat shields (47) and outer vane platforms (38) within the turbine stage (TS) to one another such that air (37) leaking through the joints between the outer vane platforms (38) and the adjacent stator heat shields (47) into the hot gas path (42) is directed onto the blade crown (32) of the blades (40).

6. 发明公开

EP2458147A3 Gas turbine of the axial flow type 审中-公开
公开(公告)号：EP2458147A3
公开(公告)日：2014-08-06
申请号：EP11190647.5
申请日：2011-11-24
申请人： Alstom Technology Ltd
发明人： Khanin, Alexander Anatolievich , Kostege, Valery , Sumin, Anton
IPC分类号： F01D5/08 , F01D25/12
CPC分类号： F01D5/084 , F01D5/081 , F01D25/12
摘要： The invention relates to a gas turbine (20) of the axial flow type, comprising a rotor (13) and a stator, which stator constitutes a casing surrounding the rotor (13), thereby providing a hot gas path, through which hot gas formed in a combustion chamber passes, whereby the rotor (13) comprises a rotor shaft (15) with axial slots, especially of the fir-tree type, for receiving a plurality of blades (B1-B3), which are arranged in a series of blade rows, with rotor heat shields (R1, R2) interposed between adjacent blade rows, thereby forming an inner outline of the hot gas path, and whereby the rotor shaft (15) is configured to conduct a main flow of cooling air (17) in axial direction along the rotor heat shields (R1, R2) and the lower parts of the blades (B1-B3), and whereby the rotor shaft (15) supplies the blades (B1-B3) with cooling air (18) entering the interior of the blades (B1-B3).
Stable and predictable cooling air parameters at any blade row inlet are secured by providing air-tight cooling channels (21), which extend axially through the rotor shaft (15) separate from the main flow of cooling air (17), and supply the blades (B1-B3) with cooling air (18).

7. 发明公开

EP2458147A2 Gas turbine of the axial flow type 审中-公开
标题翻译：轴流式燃气轮机
公开(公告)号：EP2458147A2
公开(公告)日：2012-05-30
申请号：EP11190647.5
申请日：2011-11-24
申请人： Alstom Technology Ltd
发明人： Khanin, Alexander Anatolievich , Kostege, Valery , Sumin, Anton
IPC分类号： F01D5/08 , F01D25/12
CPC分类号： F01D5/084 , F01D5/081 , F01D25/12
摘要： The invention relates to a gas turbine (20) of the axial flow type, comprising a rotor (13) and a stator, which stator constitutes a casing surrounding the rotor (13), thereby providing a hot gas path, through which hot gas formed in a combustion chamber passes, whereby the rotor (13) comprises a rotor shaft (15) with axial slots, especially of the fir-tree type, for receiving a plurality of blades (B1-B3), which are arranged in a series of blade rows, with rotor heat shields (R1, R2) interposed between adjacent blade rows, thereby forming an inner outline of the hot gas path, and whereby the rotor shaft (15) is configured to conduct a main flow of cooling air (17) in axial direction along the rotor heat shields (R1, R2) and the lower parts of the blades (B1-B3), and whereby the rotor shaft (15) supplies the blades (B1-B3) with cooling air (18) entering the interior of the blades (B1-B3).
Stable and predictable cooling air parameters at any blade row inlet are secured by providing air-tight cooling channels (21), which extend axially through the rotor shaft (15) separate from the main flow of cooling air (17), and supply the blades (B1-B3) with cooling air (18).
摘要翻译：本发明涉及一种轴流式燃气轮机（20），其包括转子（13）和定子，该定子构成围绕转子（13）的外壳，由此提供热气路径，热气体通过该热气路径形成在燃烧室中通过，由此转子（13）包括具有轴向槽（特别是枞树型）的转子轴（15），用于接收多个叶片（B1-B3），所述叶片布置成一系列（R1，R2）置于相邻的叶片列之间，从而形成热气路径的内轮廓，并且其中转子轴（15）构造成引导冷却空气（17）的主流，沿着转子隔热罩（R1，R2）和叶片（B1-B3）的下部沿轴向方向旋转，并且由此转子轴（15）向叶片（B1-B3）供应冷却空气（18）刀片内部（B1-B3）。通过提供气密冷却通道（21）来确保任何叶片排入口处的稳定且可预测的冷却空气参数，所述气密冷却通道轴向地穿过与主冷却空气流（17）分开的转子轴（15）延伸，（B1-B3）和冷却空气（18）。

8. 发明授权

EP2458159B1 Gas turbine of the axial flow type 有权
标题翻译：轴流燃气涡轮
公开(公告)号：EP2458159B1
公开(公告)日：2016-03-30
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

9. 发明授权

EP2458155B1 Gas turbine of the axial flow type 有权
标题翻译：轴流燃气涡轮
公开(公告)号：EP2458155B1
公开(公告)日：2015-06-24
申请号：EP11190895.0
申请日：2011-11-28
申请人： ALSTOM Technology Ltd
发明人： Khanin, Alexander Anatolievich , Kostege, Valery
IPC分类号： F01D9/00 , F01D5/20 , F01D11/08 , F02C7/18
CPC分类号： F01D9/00 , F01D11/08 , F02C7/18 , F05D2240/11 , F05D2260/20 , F05D2260/205

10. 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）。

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