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1. 发明授权

EP2900925B1 GAS TURBINE ENGINE COMBUSTOR WITH INTEGRATED COMBUSTOR VANE 有权转让
公开(公告)号：EP2900925B1
公开(公告)日：2018-07-18
申请号：EP13864570.0
申请日：2013-09-25
申请人： United Technologies Corporation
发明人： CUNHA, Frank, J. , ERBAS-SEN, Nurhak
IPC分类号： F23R3/06 , F23R3/16 , F23R3/26
CPC分类号： F23R3/16 , F23R3/06 , F23R3/26 , F23R2900/00018 , F23R2900/03041 , F23R2900/03042 , F23R2900/03045 , Y02T50/675
摘要： A combustor section for a gas turbine engine includes a combustor vane which extends at least partially into a combustion chamber.

2. 发明授权

EP1286031B2 Gas turbine control apparatus and gas turbine system using the same 有权
公开(公告)号：EP1286031B2
公开(公告)日：2018-07-04
申请号：EP02018282.0
申请日：2002-08-22
申请人： MITSUBISHI HEAVY INDUSTRIES, LTD.
发明人： Nomura, Masumi, Mitsubishi Heavy Industries, Ltd. , Kozo, Toyama, Mitsubishi Heavy Industries, Ltd.
IPC分类号： F02C9/50
CPC分类号： F02C7/228 , F01D17/162 , F02C9/18 , F02C9/22 , F02C9/263 , F02C9/28 , F02C9/50 , F02C9/52 , F05D2260/96 , F05D2270/083 , F05D2270/14 , F23N5/16 , F23N2041/20 , F23R3/26 , F23R2900/00013 , F23R2900/00014
摘要： In a gas turbine control apparatus, a frequency analyzing section (12) analyzes the frequency of at least one pressure oscillation in combustors of a gas turbine and the acceleration oscillation of each of the combustors and outputs a first frequency analysis result as the result of frequency analysis for a plurality of predetermined frequency bands. A control unit (11,21,24,27,30,33,34) controls at least one of a first fuel flow rate of fuel and a first air flow rate of air based on the first frequency analysis result for the plurality of frequency bands. The fuel and the air are supplied to the gas turbine.

3. 发明公开

EP3301278A1 GAS TURBINE ARRANGEMENT WITH CONTROLLED BLEED AIR INJECTION INTO COMBUSTOR, AND METHOD OF OPERATION 审中-公开
标题翻译：可控气体喷射进入燃烧室的燃气轮机布置及操作方法
公开(公告)号：EP3301278A1
公开(公告)日：2018-04-04
申请号：EP16191803.2
申请日：2016-09-30
申请人： Siemens Aktiengesellschaft
发明人： Jaerling, Patrik , Larsson, Anders
IPC分类号： F02C7/22 , F02C9/18 , F02C9/52 , F23N5/24 , F23R3/26 , F02C6/08 , F02C9/00
CPC分类号： F23N5/242 , F02C3/22 , F02C6/08 , F02C7/222 , F02C9/40 , F05D2220/75 , F23R3/26
摘要： The invention is related to gas turbine arrangement for at least dual fuel operation, comprising a compressor (11), at least one combustor (12), a plurality of fuel manifolds (21,22,23), each connected to each of the at least one combustor (12) and a control system (17). A first manifold (21) these fuel manifolds is configured to deliver either a, preferably gaseous, first fuel or a compressor bleed fluid (31), the first manifold (21) being connectable to a bleed port (30) of the compressor (11) via a bleed valve (32,32') for delivering the compressor bleed fluid (31), wherein the first manifold (21) is connected to at least one first passage (41) of the at least one combustor (12) for ejecting the first fuel or the compressor bleed fluid (31) into a combustor space (50). A second manifold (22) of these fuel manifolds (21,22,23) is configured to deliver at least a, preferably gaseous, second fuel, wherein the second manifold (22) is connected to at least one second passage (42) of the at least one combustor (12) for ejecting the second fuel into the combustor space (50). The control system (17), when the combustor (12) is operated solely with the second fuel, is configured to provide the second fuel to the second manifold (22) and to continuously open the bleed valve (32,32') to provide compressor bleed fluid (31) into the first manifold (21) such that the first fuel in the first manifold (21) is replaced by the compressor bleed fluid (31), to monitor a flame behaviour and/or fuel distribution in the combustor space (50), and to modify the flame behaviour and/or fuel distribution by controlling of the bleed valve (32,32') and/or further valves (43',43",43"',43"").
摘要翻译：本发明涉及用于至少双燃料操作的燃气涡轮机装置，其包括压缩机（11），至少一个燃烧器（12），多个燃料歧管（21,22,23），每个燃料歧管连接到至少一个燃烧器（12）和控制系统（17）。这些燃料歧管的第一歧管（21）构造成输送优选为气态的第一燃料或压缩机排出流体（31），第一歧管（21）可连接至压缩机（11）的排出口（30））经由用于输送压缩机排出流体（31）的排出阀（32,32'），其中第一歧管（21）连接到至少一个燃烧器（12）的至少一个第一通道（41）以用于排出第一燃料或压缩机将流体（31）引入燃烧室空间（50）。这些燃料歧管（21,22,23）中的第二歧管（22）构造成输送至少一种优选气态的第二燃料，其中第二歧管（22）连接到至少一个第二通道（42），该第二通道所述至少一个燃烧器（12）用于将所述第二燃料喷射到所述燃烧室空间（50）中。当燃烧器（12）仅用第二燃料操作时，控制系统（17）构造成向第二歧管（22）提供第二燃料并连续打开泄放阀（32,32'）以提供压缩机排出流体（31）进入第一歧管（21），使得第一歧管（21）中的第一燃料被压缩机排出流体（31）代替，以监测燃烧室空间中的火焰行为和/或燃料分布（50），并且通过控制排放阀（32,32'）和/或另外的阀（43'，43“，43”'，43“”）来改变火焰行为和/或燃料分配。

4. 发明授权

EP3027867B1 SYSTEM AND METHOD OF CONTROLLING COMBUSTION AND EMISSIONS IN GAS TURBINE ENGINE WITH EXHAUST GAS RECIRCULATION 有权
标题翻译：燃气涡轮发动机排气再循环燃烧和排放的控制系统和方法
公开(公告)号：EP3027867B1
公开(公告)日：2017-10-04
申请号：EP14750915.2
申请日：2014-07-29
申请人： ExxonMobil Upstream Research Company
发明人： SLOBODYANSKIY, Ilya Aleksandrovich , DAVIS JR., Lewis Berkley , MINTO, Karl Dean
IPC分类号： F23N1/02 , F23R3/16 , F23R3/26
CPC分类号： F23N1/02 , F02C1/005 , F02C3/34 , F05D2260/61 , F05D2270/08 , F05D2270/083 , F23C9/00 , F23C9/08 , F23C2202/20 , F23C2202/30 , F23N2021/12 , F23N2041/20 , F23R3/002 , F23R3/16 , F23R3/26 , F23R3/40 , Y02E20/16 , Y02T50/677
摘要： In one embodiment, a system includes a turbine combustor having a combustor liner disposed about a combustion chamber, a head end upstream of the combustion chamber relative to a downstream direction of a flow of combustion gases through the combustion chamber, a flow sleeve disposed at an offset about the combustor liner to define a passage, and a barrier within the passage. The head end is configured to direct an oxidant flow and a first fuel flow toward the combustion chamber. The passage is configured to direct a gas flow toward the head end and to direct a portion of the oxidant flow toward a turbine end of the turbine combustor. The gas flow includes a substantially inert gas. The barrier is configured to block the portion of the oxidant flow toward the turbine end and to block the gas flow toward the head end within the passage.
摘要翻译：在一个实施例中，一种系统包括涡轮燃烧器，该涡轮燃烧器具有布置在燃烧室周围的燃烧器衬套，相对于通过燃烧室的燃烧气体流的下游方向的燃烧室上游的头端，布置在燃烧室在燃烧器衬套周围偏移以限定通道，以及通道内的屏障。头端构造成将氧化剂流和第一燃料流引向燃烧室。该通道被构造成将气流引向头端并且将一部分氧化剂流引向涡轮机燃烧器的涡轮机端。气流包括基本上惰性的气体。屏障被配置为阻挡氧化剂流向涡轮机端部的一部分并阻止气体流向通道内的头端。

5. 发明公开

EP2204617A3 Methods and systems for controlling a combustor in turbine engines 审中-公开
标题翻译：用于控制涡轮发动机中的燃烧器的方法和系统
公开(公告)号：EP2204617A3
公开(公告)日：2017-05-10
申请号：EP09179181.4
申请日：2009-12-15
申请人： General Electric Company
发明人： Myers, Geoffrey David , Davis, Jr., Lewis Berkley , Healy, Timothy Andrew , Citeno, Joseph
IPC分类号： F23R3/26 , F23N5/00
CPC分类号： F23R3/26 , F23N5/00 , F23N2041/20 , F23R2900/00013
摘要： Embodiments of methods and systems for controlling a combustor (104) for a turbine engine (100) are provided. According to one example embodiment, a system includes an air control assembly (406) associated with at least one air path of a combustor (104) for a turbine engine (100). Additionally, the system also includes at least one sensor (402) for sensing at least one operating parameter of the turbine engine (100). Further, the system also includes a controller (404) operable to receive at least one operating parameter sensed by the at least one sensor (402), and further operable to selectively control an air control assembly (406) based at least in part on the at least one operating parameter sensed by the at least one sensor (402).
摘要翻译：提供了用于控制涡轮发动机（100）的燃烧器（104）的方法和系统的实施例。根据一个示例性实施例，一种系统包括与用于涡轮发动机（100）的燃烧器（104）的至少一个空气路径相关联的空气控制组件（406）。另外，该系统还包括用于感测涡轮发动机（100）的至少一个运行参数的至少一个传感器（402）。此外，所述系统还包括控制器（404），所述控制器可操作以接收由所述至少一个传感器（402）感测的至少一个操作参数，并且还可操作以至少部分地基于所述空气控制组件由所述至少一个传感器（402）感测的至少一个操作参数。

6. 发明公开

EP2599981A3 Systems and Methods for Changing a Speed of a Compressor Boost Stage in a Gas Turbine 有权
标题翻译：一种用于在燃气涡轮机改变压缩器增益级的速度的系统和方法
公开(公告)号：EP2599981A3
公开(公告)日：2017-03-01
申请号：EP12182402.3
申请日：2012-08-30
申请人： PRATT & WHITNEY CANADA CORP.
发明人： MacFarlane, Ian A.
IPC分类号： F02C7/36
CPC分类号： F02C7/36 , F05D2260/4023 , F05D2260/4031 , F05D2260/902 , F23R3/26
摘要： A system for changing a speed ratio between a compressor boost stage (12) and at least one power turbine (16) of a gas turbine engine (10) comprises a coupling device (20) configured to selectively transmit energy from the at least one power turbine (16) to the boost stage (12) according to at least a first speed ratio and a second speed ratio. The system also comprises an auxiliary power device (22, 26) configured to cause a rotational speed of the boost stage (12) to change from a first speed corresponding substantially to the first speed ratio to a second speed corresponding substantially to the second speed ratio when the boost stage (12) is decoupled from the at least one power turbine (16).
摘要翻译：一种用于改变压缩机升压级（12）和燃气涡轮发动机的至少一个动力涡轮（16）之间的速度比的系统（10）包括构造成选择性地从所述至少一个功率发射能量的耦合装置（20）涡轮机（16）升压级（12）雅丁到至少一个第一速度比和一个第二速度比。因此，系统包括配置成使所述升压级（12）的旋转速度从第一速度基本对应于第一速度比第二速度基本上对应于所述第二速度比改变辅助电源装置（22，26）的当升压级（12）由所述至少一个动力涡轮机（16）脱开。

7. 发明公开

EP3132131A1 COMBUSTION CYCLE PROCESS 无效
标题翻译： VERBRENNUNGSZYKLUSVERFAHREN
公开(公告)号：EP3132131A1
公开(公告)日：2017-02-22
申请号：EP15721117.8
申请日：2015-04-17
申请人： Hoos, Frank
发明人： Hoos, Frank
IPC分类号： F02G5/02 , F02C7/08
CPC分类号： F23R3/26 , F02C1/05 , F02C6/16 , F02C7/08 , F02G5/02 , F23R3/28 , Y02E60/15 , Y02T10/166 , Y02T50/671
摘要： An aspect of the present disclosure is a process for generating work, in particular via a combustion cycle. The process comprises the steps of compressing an oxidator, e.g. air. The process further comprises mixing the oxidator with a reductor, in particular a fuel, e.g. hydrocarbons such as petrol, kerosene, and diesel and causing the mixture to ignite, e.g. by means of a spark or (compression) heat. The process further comprises allowing the ignited mixture to expand, generating work, exchanging heat between the expanded and combusted mixture and the compressed oxidator, and exhausting the expanded and combusted mixture.
摘要翻译：本公开的一个方面是特别是经由燃烧循环产生作业的过程。该方法包括以下步骤：将氧化剂空气。该方法进一步包括将氧化剂与还原剂，特别是燃料混合。烃类如汽油，煤油和柴油，并使混合物点燃，例如通过火花或（压缩）热。该方法还包括允许点燃的混合物膨胀，产生工作，在膨胀和燃烧的混合物与压缩的氧化剂之间进行热交换，以及排出膨胀和燃烧的混合物。

8. 发明公开

EP3067626A1 AIR SHIELD FOR A FUEL INJECTOR OF A COMBUSTOR 审中-公开
标题翻译：欧洲克莱斯特·芬克斯EINER BRENNKAMMER
公开(公告)号：EP3067626A1
公开(公告)日：2016-09-14
申请号：EP16158421.4
申请日：2016-03-03
申请人： General Electric Company
发明人： BHAGAT, Reena , CAI, Jun
IPC分类号： F23R3/34 , F23R3/00
CPC分类号： F23R3/346 , F23R3/002 , F23R3/26
摘要： An air shield (100) for an injector (32) of a combustor (20) includes a first section (102) that extends axially from a first end (101) to a second end (103). The first section includes at least one side wall and a top wall. The at least one side wall and the top wall at least partially define a channel (112) configured to distribute a channel airflow to the injector. The air shield also includes at least one first inlet defined through the at least one side wall and at least one second inlet defined through the top wall. The at least one first inlet and the at least one second inlet are configured to receive a portion of a surrounding airflow to at least partially form the channel airflow.
摘要翻译：用于燃烧器（20）的喷射器（32）的空气屏蔽（100）包括从第一端（101）轴向延伸到第二端（103）的第一部分（102）。第一部分包括至少一个侧壁和顶壁。所述至少一个侧壁和所述顶壁至少部分地限定了构造成将通道气流分配到所述喷射器的通道（112）。空气屏蔽还包括通过至少一个侧壁限定的至少一个第一入口和通过顶壁限定的至少一个第二入口。所述至少一个第一入口和所述至少一个第二入口构造成接收周围气流的一部分以至少部分地形成所述通道气流。

9. 发明公开

EP3039340A4 VENA CONTRACTA SWIRLING DILUTION PASSAGES FOR GAS TURBINE ENGINE COMBUSTOR 有权转让
标题翻译：弗吉尼亚州
公开(公告)号：EP3039340A4
公开(公告)日：2016-08-24
申请号：EP14848461
申请日：2014-06-30
申请人： UNITED TECHNOLOGIES CORP
发明人： DRAKE CHRISTOPHER , CUNHA FRANK J , KOSTKA JR STANISLAV , JAUSE JONATHAN M , HANSON RUSSELL B
IPC分类号： F23M5/08 , F02C7/18 , F23R3/04 , F23R3/42
CPC分类号： F23R3/06 , F02C7/18 , F23R3/002 , F23R3/005 , F23R3/04 , F23R3/045 , F23R3/26 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044 , Y02T50/675
摘要： A liner panel for use in a combustor of a gas turbine engine includes a nozzle includes an inner periphery along an axis. The inner periphery includes a flow guide around the axis. A wall assembly for use in a combustor of a gas turbine engine includes a support shell with a first inner periphery along an axis. The wall assembly also includes a liner panel with a second inner periphery along the axis, the second inner periphery including a spiral flow guide around the axis. A method of reducing recirculation into a dilution passage in a combustor liner panel of a gas turbine engine includes contouring a dilution passage to match a natural vena contracta of a fluid flowing therethrough.
摘要翻译：用于燃气涡轮发动机的燃烧器的衬板包括：喷嘴，包括沿轴线的内周边。内周边包括围绕轴的流动引导件。用于燃气涡轮发动机的燃烧器的壁组件包括具有沿轴线的第一内周边的支撑壳体。壁组件还包括具有沿着轴线的第二内周边的衬板，第二内周包括绕轴线的螺旋形流动引导件。减少燃气涡轮发动机的燃烧器衬板中的稀释通道的再循环的方法包括对稀释通道进行轮廓化，以匹配流过其中的流体的天然收缩膜。

10. 发明公开

EP3054219A1 AIR SHROUDS WITH AIR WIPES 有权
标题翻译： LUFTUMMANTELENEN MITLUFTTÜCHERN
公开(公告)号：EP3054219A1
公开(公告)日：2016-08-10
申请号：EP16154547.0
申请日：2016-02-05
申请人： Delavan, Inc.
发明人： DONOVAN, Matthew , BRETZ, David H. , BUELOW, Philip E.O.
IPC分类号： F23R3/26 , F23R3/14
CPC分类号： F23R3/28 , F23R3/14 , F23R3/26 , F23R2900/00004
摘要： An air shroud (100) for a nozzle includes an air shroud body (101) defining an inlet and an outlet (103) in fluid communication with one another to allow an outer airflow to issue therefrom. The air shroud (100) also includes an air wipe (107) disposed outboard of the air shroud body (101) including a web (109) defining a plurality of air wipe outlets (111) in fluid communication with a downstream surface (105) of the air shroud body (101) such that air can flow through the air wipe outlets (111) and wipe the downstream surface (105) of the air shroud body (101). The air wipe (107) can be integral with the air shroud body (101).
摘要翻译：用于喷嘴的空气罩（100）包括限定入口的空气罩体（101）和彼此流体连通的出口（103），以允许从其中发出外部气流。空气罩（100）还包括布置在空气护罩主体（101）外侧的空气擦拭物（107），其包括限定与下游表面（105）流体连通的多个空气擦拭出口（111）的腹板（109）使得空气罩体（101）的空气能够流过空气擦拭出口（111）并擦拭空气罩体（101）的下游表面（105）。空气擦拭物（107）可以与空气罩体（101）成一体。

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