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1. 发明专利

JP2014190195A Gas turbine plant and gas turbine plant operation method 有权
标题翻译：气体涡轮机和气体涡轮机运行方法
公开(公告)号：JP2014190195A
公开(公告)日：2014-10-06
申请号：JP2013064715
申请日：2013-03-26
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： UECHI HIDEYUKI , SUGISHITA HIDEAKI , TOMIKAWA KUNIHIRO , ITO EISAKU , NAKAMOTO YUKIMASA , SAITO NAOHITO
IPC分类号： F01K23/10 , F02C6/18 , F02C7/08 , F02C7/22 , F02C7/224 , F02C9/16 , F22B1/18
摘要： PROBLEM TO BE SOLVED: To improve efficiency of a gas turbine plant.SOLUTION: A gas turbine plant includes: a combustor 21 combusting fuel F and generating combustion gas; a gas turbine 10 having a turbine 31 driven by the combustion gas; an exhaust heat collection boiler 110 generating steam using heat of exhaust gas EG from the gas turbine 10; a combustion-assisting combustor 141 injecting the fuel F into a part of the exhaust gas EG most upstream of the exhaust gas EG of the exhaust heat collection boiler 110; and a combustion-assisting heat exchanger 142 installed downstream of the combustion-assisting combustor 141. A part of the exhaust gas EG passing through the combustion-assisting combustor 141 merges with the remainder of the exhaust gas EG that does not pass through the combustion-assisting combustor 141 within the exhaust heat collection boiler 110.
摘要翻译：要解决的问题：提高燃气轮机厂的效率。解决方案：燃气轮机设备包括：燃烧燃料F并产生燃烧气体的燃烧器21; 具有由燃烧气体驱动的涡轮31的燃气轮机10; 排气收集锅炉110，其利用来自燃气轮机10的废气EG的热量产生蒸汽; 燃烧辅助燃烧器141将燃料F喷射到废气收集锅炉110的废气EG的最上游的废气EG的一部分; 和辅助燃烧器141的下游的助燃热交换器142.通过燃烧辅助燃烧器141的排气EG的一部分与不通过燃烧辅助燃烧器141的废气EG的其余部分合并，在排气收集锅炉110内辅助燃烧器141。

2. 发明专利

JP2014009606A Cooling system of turbine blade and gas turbine 有权
标题翻译：涡轮叶片和气体涡轮冷却系统
公开(公告)号：JP2014009606A
公开(公告)日：2014-01-20
申请号：JP2012145637
申请日：2012-06-28
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： UECHI HIDEYUKI
IPC分类号： F02C7/18 , F01D9/02 , F01K23/04 , F02C6/08 , F02C6/18 , F02C7/143 , F02C7/224
CPC分类号： Y02E20/16
摘要： PROBLEM TO BE SOLVED: To provide a cooling system of a turbine blade and a gas turbine which can reduce power of a compressor and can cool properly the turbine blade.SOLUTION: A cooling system of a turbine blade includes: a cooling device 51 which cools low-pressure compressed air extracted by being caused to pass through a compressed air extraction passage 56 from an extraction chamber 25 of a compressor 11; an auxiliary compressor 52 as a booster which boosts low-pressure cooled compressed air cooled by the cooling device 51; and a cooled gas supply device 53 which supplies high-pressure cooled compressed air compressed by the auxiliary compressor 52 to the interior of a turbine blade arranged on a position where the pressure is higher than the low-pressure gas on a combustion gas passage 40.
摘要翻译：要解决的问题：提供一种涡轮叶片和燃气轮机的冷却系统，其可以降低压缩机的功率并且可以适当地冷却涡轮叶片。涡轮叶片的冷却系统包括：冷却装置51，其冷却通过压缩机11的提取室25从压缩空气抽出通道56抽出的低压压缩空气; 作为增压器的辅助压缩机52，其对由冷却装置51冷却的低压冷却压缩空气进行升压; 以及冷却气体供给装置53，其将由辅助压缩机52压缩的高压冷却压缩空气供给到设置在燃烧气体通路40上的压力高于低压气体的位置的涡轮叶片的内部。

3. 发明专利

JP2012225211A Gas turbine moving blade and method of manufacturing the same 有权
标题翻译：气动涡轮叶片及其制造方法
公开(公告)号：JP2012225211A
公开(公告)日：2012-11-15
申请号：JP2011091984
申请日：2011-04-18
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： ISHIGURO TATSUO , UECHI HIDEYUKI , HANEDA SATORU
IPC分类号： F01D5/18 , B23H9/10 , B23H9/14 , F02C7/00
CPC分类号： F01D5/225 , F01D5/187 , F05D2240/81 , F05D2260/202 , F05D2260/205 , F05D2260/2212
摘要： PROBLEM TO BE SOLVED: To improve an output and/or energy efficiency of a gas turbine with a gas turbine moving blade configured to cool a tip shroud by cooling air.SOLUTION: The gas turbine moving blade 1 includes an airfoil section 3, an inner peripheral surface 4b joined to the tip of the airfoil section 3, and the tip shroud 4 with an outer peripheral surface 4c. The airfoil section 3 is configured to supply the cooling air to the tip shroud 4. The tip shroud 4 is configured to discharge the cooling air 7 supplied via the internal space thereof to the outside. The tip shroud 4 is configured to discharge the cooling air with a flow rate of more than 50% of the total flow rate of the supplied cooling air 7 so as to have a velocity component in a direction opposite to the rotational direction of the gas turbine moving blade.
摘要翻译：要解决的问题：为了提高燃气轮机的输出和/或能量效率，其中燃气轮机动叶片构造成通过冷却空气来冷却尖端罩。解决方案：燃气轮机动叶片1包括翼型部分3，连接到翼型部分3的尖端的内周表面4b和具有外周表面4c的尖端护罩4。翼型部3构成为向顶部护罩4供给冷却空气。顶端罩4构成为将从其内部空间供给的冷却风7排出到外部。尖端护罩4被构造成以大于供给的冷却空气7的总流量的50％的流量的方式排出冷却空气，从而具有与燃气轮机的旋转方向相反的方向的速度分量动叶片版权所有（C）2013，JPO＆INPIT

4. 发明专利

JP2012225207A Gas turbine moving blade and method of manufacturing the same 有权
标题翻译：气动涡轮叶片及其制造方法
公开(公告)号：JP2012225207A
公开(公告)日：2012-11-15
申请号：JP2011091789
申请日：2011-04-18
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： ISHIGURO TATSUO , UECHI HIDEYUKI , HANEDA SATORU
IPC分类号： F01D5/18 , F01D11/08 , F02C7/18 , F02C7/28 , F16J15/447
CPC分类号： F01D5/225 , F05D2240/81
摘要： PROBLEM TO BE SOLVED: To improve an output and/or energy efficiency of a gas turbine with a gas turbine moving blade configured to cool a tip shroud by cooling air.SOLUTION: The gas turbine moving blade 1 includes an airfoil section 3, a tip shroud 4 joined to the tip of the airfoil section 3, and a fin 5 arranged on its outer peripheral surface. The airfoil section 3 is configured to supply the cooling air to the tip shroud 4. The tip shroud 4 is configured to discharge the cooling air supplied via the internal space thereof. The tip shroud 4 is configured so that a flow rate of the cooling air discharged from the tip shroud 4 to a high pressure side area which is on the upstream side of a flow of hot gas with respect to the fin is higher than a flow rate of the cooling air discharged from the tip shroud to a low pressure side area which is downstream with respect to the fin 5.
摘要翻译：要解决的问题：为了提高燃气轮机的输出和/或能量效率，其中燃气轮机动叶片构造成通过冷却空气来冷却尖端罩。解决方案：燃气轮机动叶片1包括翼型部分3，接合到翼型部分3的尖端的尖端护罩4和布置在其外周表面上的翅片5。翼型部3被配置为将冷却空气供给到顶部护罩4.末端护罩4构成为排出经由内部空间供给的冷却空气。尖端护罩4构成为从尖端护罩4排出的冷却空气的流量相对于翅片的热气流的上游侧的高压侧区域的流量高于流量从尖端护罩排出的冷却空气相对于翅片5是下游的低压侧区域。（C）2013，JPO＆INPIT

5. 发明专利

JP2011047365A Intake air temperature control device for gas turbine, gas turbine and gas turbine combined cycle power generation plant equipped with the same 有权
标题翻译：采用气体涡轮机，气体涡轮机和气体涡轮机组合循环发电厂配备空气温度控制装置
公开(公告)号：JP2011047365A
公开(公告)日：2011-03-10
申请号：JP2009198383
申请日：2009-08-28
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： KAWAGUCHI NATSUKI , ITO EISAKU , TERASAKI MASAO , UECHI HIDEYUKI
IPC分类号： F02C7/143 , F02C6/08 , F02C6/10 , F02C6/18 , F02C7/08 , F02C9/00 , F02C9/18
CPC分类号： Y02E20/16
摘要： PROBLEM TO BE SOLVED: To obtain sufficient output for desired output and prevent damage of component devices and component parts of a gas turbine facility by proper output.
SOLUTION: An intake air temperature control device for a gas turbine is used in the gas turbine facility including a compressor, a combustor and the turbine and includes: a heat exchange means capable of exchanging heat with intake air taken in the compressor from the outside; and an intake air temperature control section causing the temperature of the intake air to be adjusted by the heat exchange means according to requested output of the gas turbine facility. The intake air temperature control section performs control so that compressor inlet temperature T
IN of the intake air at a compressor inlet is below a rated temperature T
PN according to rated output W
PN of the gas turbine facility and is not lower than the minimum temperature T
MIN according to the maximum allowable output W
MAX of the gas turbine facility.
COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：要解决的问题：为了获得足够的输出以期望的输出，并通过适当的输出来防止燃气轮机设备的部件装置和部件的损坏。解决方案：在包括压缩机，燃烧器和涡轮机的燃气轮机设备中使用用于燃气轮机的进气温度控制装置，包括：能够与从压缩机中吸入的进气相交换热量的热交换装置外; 以及进气温度控制部，其根据燃气轮机设备的要求输出，通过热交换装置来调节进气的温度。进气温度控制部进行控制，使得压缩机入口处的进气的压缩机入口温度T IN 根据额定输出W < SB> PN ，并且根据燃气轮机设备的最大允许输出W MAX 不低于最低温度T MIN 。版权所有（C）2011，JPO＆INPIT

6. 发明专利

JP2011038442A Intake air cooling system for gas turbine, gas turbine and gas turbine combined cycle power generation plant having the same and output increase method 有权
标题翻译：采用气体涡轮机，气体涡轮机和气体涡轮机组合循环发电厂及其输出增加方法的空气冷却系统
公开(公告)号：JP2011038442A
公开(公告)日：2011-02-24
申请号：JP2009184942
申请日：2009-08-07
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： YOSHINO RYO , ITO EISAKU , TERASAKI MASAO , UECHI HIDEYUKI
IPC分类号： F02C7/143 , F01K23/10 , F02C6/18 , F28D7/16 , F28F1/40
CPC分类号： F28D7/1615 , F28D7/082 , F28F1/24 , F28F1/36 , F28F13/08 , F28F13/185 , Y02E20/16
摘要： PROBLEM TO BE SOLVED: To provide an intake air cooling system for a gas turbine, restraining the gas turbine from sucking mist, without adding a separate device to a flow passage of cooled suction air. SOLUTION: This intake air cooling system 2 for the gas turbine is used for the gas turbine having a compressor, a combustor and a turbine, and includes a heat exchanger 21 cooling the suction air A sucked in the compressor from an external part. The heat exchanger 21 is characterized in that it has: a plurality of heat transfer tubes 32 extending over the upper side and the lower side in the gravitational direction and crossing with the air current direction of the suction air A; and a cooling medium C1 flowing inside the plurality of heat transfer tubes 32, and that the plurality of heat transfer tubes 32 are arranged so that the cooling effect becomes larger in the heat transfer tube 32 positioned on the air current upstream side than the heat transfer tube 32 positioned on the air current downstream side. COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：要解决的问题：为了提供一种用于燃气轮机的进气冷却系统，在不向冷却的吸入空气的流动通道添加单独的装置的同时，限制燃气轮机吸入雾气。解决方案：用于燃气轮机的进气冷却系统2用于具有压缩机，燃烧器和涡轮机的燃气轮机，并且包括热交换器21，其从外部部分冷却从压缩机吸入的吸入空气A 。热交换器21的特征在于：具有：在重力方向的上侧和下侧延伸并与吸入空气A的气流方向交叉的多个传热管32; 以及在多个传热管32内部流动的冷却介质C1，并且配置多个传热管32，使得位于比传热的上游侧的气流侧的传热管32的冷却效果变大管32位于气流下游侧。版权所有（C）2011，JPO＆INPIT

7. 发明专利

JP2004060478A Binary fluid gas turbine, its operation method, and repowering method for gas turbine 审中-公开
公开(公告)号：JP2004060478A
公开(公告)日：2004-02-26
申请号：JP2002217385
申请日：2002-07-26
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： UECHI HIDEYUKI
IPC分类号： F02C3/30 , F02C3/113 , F02C6/02 , F02C9/28 , F02C9/56 , F23R3/00
CPC分类号： Y02E20/14
摘要： PROBLEM TO BE SOLVED: To provide a binary fluid gas turbine capable of preventing the occurrence of surging and effectively attaining the increase of output and the improvement of thermal efficiency with simple constitution.
SOLUTION: This binary fluid gas turbine having a compressor for compressing air, a combustor for supplying fuel to the air compressed by the compressor, for combustion, and a turbine driven by combustion gas from the combustor, is constituted to charge steam or water in either one of a line extending from a compressor outlet to the combustor, the combustor and a line extending from the combustor to the turbine. In this constitution, a plurality of turbines are provided in parallel.
COPYRIGHT: (C)2004,JPO

8. 发明专利

JP2013083272A High temperature member for gas turbine 有权
标题翻译：用于气体涡轮机的高温部件
公开(公告)号：JP2013083272A
公开(公告)日：2013-05-09
申请号：JP2013019763
申请日：2013-02-04
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： UECHI HIDEYUKI , KAWADA YUTAKA , MATSUURA MASAAKI , SUENAGA KIYOSHI , SUGISHITA HIDEAKI , YAMAMOTO HIROYUKI , HANEDA SATORU
IPC分类号： F01D5/18 , F01D9/02 , F02C7/18
CPC分类号： F01D5/186 , F01D9/065 , F05D2240/11 , F05D2240/81 , F05D2250/711 , F05D2250/712 , F05D2250/713 , F05D2250/75 , F05D2260/202 , F05D2260/204 , F23R3/002 , F23R2900/03042
摘要： PROBLEM TO BE SOLVED: To eliminate nonuniformity of film cooling, by uniformizing a thickness of a film of a cooling medium formed on a surface of a high temperature member for a gas turbine in its width direction.SOLUTION: This high temperature member 180 for the gas turbine restrains the heat transmission from high temperature gas, by forming the film of the cooling medium on the surface 10a by the cooling medium blown off from a plurality of film cooling holes 184. One flow passage in an inflow part 185 of the film cooling hole 184 is arranged, an angle formed by the axis of the flow passage and the axis of a flow passage in an outflow part 186 of the film cooling hole 184 becomes an obtuse angle, and an angle formed by the axis of the flow passage in the outflow part 186 of the film cooling hole 184 and the surface 10a becomes an acute angle. On a wall surface 186b which forms the flow passage in the outflow part 186 and is opposed to an outlet end of the flow passage in the inflow part 185, a projection part is formed toward the outlet end.
摘要翻译：要解决的问题：为了消除膜冷却的不均匀性，通过使形成在用于燃气轮机的高温部件的表面上的冷却介质的膜的宽度方向的厚度均匀化。解决方案：这种用于燃气轮机的高温部件180通过从多个膜冷却孔184吹出的冷却介质在表面10a上形成冷却介质的膜来限制来自高温气体的热传递。在薄膜冷却孔184的流入部分185中设置一个流动通道，由流道的轴线和薄膜冷却孔184的流出部分186中的流动通道的轴线形成的角度变为钝角，并且由薄膜冷却孔184的流出部186和表面10a的流路的轴线形成的角度成为锐角。在流出部分186中形成流动通道并与流入部分185中的流动通道的出口端相对的壁表面186b上，朝向出口端形成突出部分。版权所有（C）2013，JPO＆INPIT

9. 发明专利

JP2012132461A Gas turbine 有权
标题翻译：燃气轮机
公开(公告)号：JP2012132461A
公开(公告)日：2012-07-12
申请号：JP2012015764
申请日：2012-01-27
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： UECHI HIDEYUKI , SUGISHITA HIDEAKI
IPC分类号： F02C7/18 , F01D9/02
摘要： PROBLEM TO BE SOLVED: To provide a technique for effectively preventing a gap part between a tail tube of a combustor and a stator vane shroud from burning out which is caused by pressure nonuniformity of a combustion gas in the circumferential direction of a stator vane row.SOLUTION: A gas turbine includes the combustor ejecting the combustion gas 3a from the tail tube 4, and a turbine to which the combustion gas 3a is supplied from the tail tube 4. The turbine is positioned on the downstream side of stator vanes 5 and the tail tube 4 and includes the stator vane shroud 6 supporting the stator vane 5. An opening for ejecting a cooling air 13 toward an end on the upstream side of the stator vane shroud 6 is arranged in an end on the downstream side of the tail tube 4. The opening is formed as a slit long in the direction the stator vanes 5 are arranged.
摘要翻译：要解决的问题：提供一种技术，用于有效地防止燃烧器的尾管与定子叶片护罩之间的间隙部分燃烧，这是由定子的周向上的燃烧气体的压力不均匀性引起的叶片排。解决方案：燃气轮机包括从尾管4喷射燃烧气体3a的燃烧器和从尾管4供给燃烧气体3a的涡轮机。涡轮机位于定子叶片的下游侧 5和尾管4，并且包括支撑定子叶片5的定子叶片护罩6.用于朝向定子叶片护罩6的上游侧的端部喷射冷却空气13的开口设置在尾管4.开口形成为沿定子叶片5布置的方向长的狭缝。版权所有（C）2012，JPO＆INPIT

10. 发明专利

JP2012112387A gas turbine 有权
标题翻译：燃气轮机
公开(公告)号：JP2012112387A
公开(公告)日：2012-06-14
申请号：JP2012015765
申请日：2012-01-27
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： UECHI HIDEYUKI , SUGISHITA HIDEAKI
IPC分类号： F01D9/02 , F02C7/18
摘要： PROBLEM TO BE SOLVED: To provide a technology effectively preventing a gap between a tail pipe and stationary blade shrouds of a combustor from being damaged by burn when the pressure of combustion gas in the circumference direction of a stationary blade row is uneven.SOLUTION: This gas turbine includes the combustor which ejects combustion gas 3a from the tail pipe 4, and a turbine to which the combustion gas 3a is supplied from the tail pipe 4. The turbine includes stationary blades 5 and the stationary blade shrouds 6 which are positioned on the downstream side of the tail pipe 4 and support the stationary blades 5. Openings 4c for jetting cooling air toward the upstream side ends of the stationary blade shrouds 6 are provided at the downstream side end of the tail pipe 4. Cooling air passages 4b-4 which are provided on the upstream sides of the stagnation points at the leading edges of the stationary blades for supplying cooling air to the openings 4c, and cooling air passages 4b-3 which are provided in the middle of the stagnation points for supplying cooling air to the openings 4c, are formed in the tail pipe 4. A turbulent flow generating means which generates turbulent flow in the cooling air is formed in the cooling air passage 4b-3.
摘要翻译：要解决的问题：当固定叶片排的圆周方向上的燃烧气体的压力不均匀时，提供有效地防止燃烧器的尾管和固定叶片护罩之间的间隙被燃烧损坏的技术。解决方案：该燃气轮机包括从尾管4喷射燃烧气体3a的燃烧器和从尾管4供给燃烧气体3a的涡轮机。涡轮机包括固定叶片5和固定叶片罩 6位于尾管4的下游侧并支撑固定叶片5.在尾管4的下游侧设置有用于向固定叶片护罩6的上游侧端部喷射冷却空气的开口4c。设置在静止叶片前缘上的停滞点的上游侧的冷却空气通道4b-4，用于向开口4c供应冷却空气，冷却空气通道4b-3设置在停滞中间在尾管4中形成有用于向开口4c供给冷却空气的点。在冷却风通道4b-3中形成有产生冷却空气中的湍流的湍流产生装置。版权所有（C）2012，JPO＆INPIT

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