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1. 发明申请

WO2014070436A2 TEMPERATURE CONTROL WITHIN A CAVITY OF A TURBINE ENGINE 审中-公开
标题翻译：在涡轮发动机的空气中的温度控制
公开(公告)号：WO2014070436A2
公开(公告)日：2014-05-08
申请号：PCT/US2013/064903
申请日：2013-10-15
申请人： SIEMENS AKTIENGESELLSCHAFT , RODRIGUEZ, Jose L. , LITTLE, David A. , ZHANG, Jiping , CHEHAB, Abdullatif M.
发明人： RODRIGUEZ, Jose L. , LITTLE, David A. , ZHANG, Jiping , CHEHAB, Abdullatif M.
IPC分类号： F01D9/06 , F01D25/16 , F02C7/18
CPC分类号： F01D9/065 , F01D25/162 , F02C7/18 , F05D2260/601
摘要： A turbine engine including an intermediate space defined between outer and inner portions of the turbine engine. A flow energizer is provided including a flow body located within the intermediate space and including an inlet port, an outlet port and a flow passage extending within the flow body between the inlet and outlet ports. The inlet port receives a flow of a first medium located within the intermediate space and the flow body injects an energizing flow of a second medium to a portion of the first medium within the flow body to create an energized flow of a mixed medium from the outlet portion, the energized flow of mixed medium creates a flow of the first medium adjacent to the flow body within the intermediate space.
摘要翻译：一种涡轮发动机，包括在涡轮发动机的外部和内部之间限定的中间空间。提供了一种流动增压器，其包括位于中间空间内的流动体，并且包括入口端口，出口端口和在入口和出口之间的流体内延伸的流动通道。入口端口接收位于中间空间内的第一介质流，并且流体将第二介质的通电流注入流体内的第一介质的一部分，以从出口产生混合介质的通电流混合介质的通电流在中间空间内产生与流体相邻的第一介质的流动。

2. 发明申请

WO2013126126A3 AXIAL FLOW COMPRESSOR TIP CLEARANCE CONTROL BY AXIAL SHIFT OF ROTOR 审中-公开
公开(公告)号：WO2013126126A3
公开(公告)日：2013-08-29
申请号：PCT/US2012/068466
申请日：2012-12-07
申请人： SIEMENS ENERGY, INC. , LITTLE, David A. , PU, Zhengxiang
发明人： LITTLE, David A. , PU, Zhengxiang
IPC分类号： F01D11/22 , F04D29/16
摘要： In a turbine engine, an axial compressor is equipped with a system that moves the rotor axially in order to influence the tip clearances of cantilevered airfoils during operation. Axial movement of the rotor can reduce the tip clearances of both one cantilevered rotor blade and one cantilevered stator vane. The radially inwards flowpath boundary of the compressor is shaped in such a way that its radius increases in streamwise direction over a portion of its axial extend, at least over the 40% downstream part of its axial extend.

3. 发明申请

WO2011097121A3 COOLING OF TURBINE COMPONENTS USING COMBUSTOR SHELL AIR 审中-公开
标题翻译：使用COMBUSTOR SHELL空气冷却涡轮机组件
公开(公告)号：WO2011097121A3
公开(公告)日：2011-10-27
申请号：PCT/US2011022819
申请日：2011-01-28
申请人： SIEMENS ENERGY INC , FOUST ADAM M , NORDLUND RAYMOND S , CHHABRA NITIN , LITTLE DAVID A
发明人： FOUST ADAM M , NORDLUND RAYMOND S , CHHABRA NITIN , LITTLE DAVID A
IPC分类号： F02C9/18 , F01D9/02 , F02C3/13 , F02C6/08 , F02C7/12 , F02C7/18
CPC分类号： F01D9/023 , F02C3/13 , F02C6/08 , F02C7/12 , F02C7/185 , F02C9/18 , F05D2260/20 , F05D2270/08
摘要： A turbine engine assembly for a generator including a turbine engine having a compressor section (12), a combustor section (30) and a turbine section (14). An air bleed line is in communication with the combustor section for receiving combustor shell air from the combustor section and conveying the combustor shell air as bleed air to a plurality of stages of the turbine section. Bleed air is controlled to flow through the air bleed line when an operating load of the turbine engine assembly is less than a base load of the engine to bypass air exiting the compressor section around a combustor in the combustor section and effect a flow of high pressure combustor shell air to the stages of the turbine section.
摘要翻译：一种用于发电机的涡轮发动机组件，包括具有压缩机部分（12），燃烧器部分（30）和涡轮部分（14）的涡轮发动机。排气管路与燃烧器部分连通，用于从燃烧器部分接收燃烧器壳体空气，并将燃烧器壳体空气作为排气输送到涡轮部分的多个级。当涡轮发动机组件的操作负载小于发动机的基本负载以排出围绕燃烧器部分中的燃烧器排出的压缩机部分的空气时，排出的空气被控制流过排气管，并且产生高压燃烧器壳体空气到涡轮部分的阶段。

4. 发明申请

WO2005057197A1 A DEPOSITION SENSOR BASED ON DIFFERENTIAL HEAT FLUX MEASUREMENT 审中-公开
标题翻译：基于差分热通量测量的沉积传感器
公开(公告)号：WO2005057197A1
公开(公告)日：2005-06-23
申请号：PCT/US2004/033854
申请日：2004-10-15
申请人： GENERAL ELECTRIC COMPANY , XIAO, Caibin , LITTLE, David, A. , BOYETTE, Scott, M.
发明人： XIAO, Caibin , LITTLE, David, A. , BOYETTE, Scott, M.
IPC分类号： G01N25/18
CPC分类号： G01N17/008 , G01N25/18
摘要： An apparatus and method for the monitoring and measurement of chemical and/or biological deposition in heat exchangers and other fluid processing vessels. The new and original sensing system includes at least two hollow fluid vessels conductively mounted across a constant heat transfer path. Thin film heat flux sensors are attached to a heat transfer surface of the vessels in order to measure changes in differential heat flux that occur when deposition begins to accumulate in the vessel. In this way, it is shown that differential heat flux measurements can be used to detect and measure the early onset of chemical and/or biological deposition.
摘要翻译：用于监测和测量热交换器和其它流体处理容器中的化学和/或生物沉积的装置和方法。新的和原始的感测系统包括至少两个导电地安装在恒定传热路径上的中空流体容器。薄膜热通量传感器连接到容器的传热表面，以便测量当沉积开始在容器中积聚时发生的差热通量的变化。以这种方式，可以看出差示热通量测量可用于检测和测量化学和/或生物沉积的早期发生。

5. 发明申请

WO2014070436A3 TEMPERATURE CONTROL WITHIN A CAVITY OF A TURBINE ENGINE 审中-公开
标题翻译：在涡轮发动机的空气中的温度控制
公开(公告)号：WO2014070436A3
公开(公告)日：2014-07-24
申请号：PCT/US2013064903
申请日：2013-10-15
申请人： SIEMENS AG , RODRIGUEZ JOSE L , LITTLE DAVID A , ZHANG JIPING , CHEHAB ABDULLATIF M
发明人： RODRIGUEZ JOSE L , LITTLE DAVID A , ZHANG JIPING , CHEHAB ABDULLATIF M
IPC分类号： F01D9/06 , F01D25/16 , F02C7/18
CPC分类号： F01D9/065 , F01D25/162 , F02C7/18 , F05D2260/601
摘要： A turbine engine including an intermediate space defined between outer and inner portions of the turbine engine. A flow energizer (64) is provided including a flow body located within the intermediate space and including an inlet port (68), an outlet port and a flow passage extending within the flow body between the inlet and outlet ports. The inlet port receives a flow of a first medium located within the intermediate space and the flow body injects an energizing flow of a second medium (82) to a portion of the first medium within the flow body to create an energized flow of a mixed medium from the outlet portion, the energized flow of mixed medium creates a flow of the first medium adjacent to the flow body within the intermediate space.
摘要翻译：一种涡轮发动机，包括在涡轮发动机的外部和内部之间限定的中间空间。提供流动增压器（64），其包括位于中间空间内的流动体，并且包括入口端口（68），出口端口和在入口端口和出口之间的流体内延伸的流动通道。入口端口接收位于中间空间内的第一介质的流动，流体将第二介质（82）的通电流注入流体内的第一介质的一部分以产生混合介质的通电流从出口部分，混合介质的通电流在中间空间内产生与流体相邻的第一介质的流动。

6. 发明申请

WO2011097121A2 COOLING OF TURBINE COMPONENTS USING COMBUSTOR SHELL AIR 审中-公开
标题翻译：使用COMBUSTOR SHELL空气冷却涡轮机组件
公开(公告)号：WO2011097121A2
公开(公告)日：2011-08-11
申请号：PCT/US2011/022819
申请日：2011-01-28
申请人： SIEMENS ENERGY, INC. , FOUST, Adam, M. , NORDLUND, Raymond, S. , CHHABRA, Nitin , LITTLE, David, A.
发明人： FOUST, Adam, M. , NORDLUND, Raymond, S. , CHHABRA, Nitin , LITTLE, David, A.
IPC分类号： F02C9/18
CPC分类号： F01D9/023 , F02C3/13 , F02C6/08 , F02C7/12 , F02C7/185 , F02C9/18 , F05D2260/20 , F05D2270/08
摘要： A turbine engine assembly for a generator including a turbine engine having a compressor section, a combustor section and a turbine section. An air bleed line is in communication with the combustor section for receiving combustor shell air from the combustor section and conveying the combustor shell air as bleed air to a plurality of stages of the turbine section. Bleed air is controlled to flow through the air bleed line when an operating load of the turbine engine assembly is less than a base load of the engine to bypass air exiting the compressor section around a combustor in the combustor section and effect a flow of high pressure combustor shell air to the stages of the turbine section.
摘要翻译：一种用于发电机的涡轮发动机组件，其包括具有压缩机部分，燃烧器部分和涡轮部分的涡轮发动机。排气管路与燃烧器部分连通，用于从燃烧器部分接收燃烧器壳体空气，并将燃烧器壳体空气作为排气输送到涡轮部分的多个级。当涡轮发动机组件的操作负载小于发动机的基本负载以排出围绕燃烧器部分中的燃烧器排出的压缩机部分的空气时，排出的空气被控制流过排气管，并且产生高压燃烧器壳体空气到涡轮部分的阶段。

7. 发明申请

WO2008123904A2 ENGINE BRAKE FOR PART LOAD CO REDUCTION 审中-公开
标题翻译：发动机制动器减少部分负荷
公开(公告)号：WO2008123904A2
公开(公告)日：2008-10-16
申请号：PCT/US2008/001858
申请日：2008-02-13
申请人： SIEMENS POWER GENERATION, INC. , MYERS, Gerald, A. , LITTLE, David, A.
发明人： MYERS, Gerald, A. , LITTLE, David, A.
CPC分类号： F01K13/02 , F02C9/18 , F02C9/20 , F05D2270/08
摘要： Aspects of the invention relate to a system and method for operating a turbine engine assembly. The turbine engine assembly has a turbine engine (10) having a compressor section (14), a combustor section (16) and a turbine section (18). The combustor section (16) has a lower T_PZ limit and the turbine engine (10) has a design load. The assembly further includes at least one air bleed line (80) from the compressor (14) and at least one valve (84) for controlling air flow through the bleed line (80). Control structure (88) is provided for opening the valve (84) to allow bleed air to flow through the bleed line (80) when an operating load is less than the design load. The flow rate through the bleed line (80) is increased as the operating load is decreased, reducing the power delivered by the turbine assembly while maintaining the T_PZ above a lower T_PZ limit. A method for operating a turbine engine assembly is also disclosed.
摘要翻译：本发明的方面涉及用于操作涡轮发动机组件的系统和方法。涡轮发动机组件具有涡轮发动机（10），其具有压缩机部分（14），燃烧器部分（16）和涡轮部分（18）。燃烧器部分（16）具有较低的T_PZ限制，并且涡轮发动机（10）具有设计负载。组件还包括来自压缩机（14）的至少一个排气管线（80）和用于控制通过排放管线（80）的空气流的至少一个阀门（84）。提供控制结构（88），用于当操作负载小于设计负荷时，打开阀（84）以允许排放空气流过排放管线（80）。通过泄放管线（80）的流量随着操作负载的降低而增加，从而降低涡轮机组件输送的功率，同时将T_PZ保持在较低的T_PZ极限以下。还公开了一种用于操作涡轮发动机组件的方法。

8. 发明申请

WO2013126126A2 COMPRESSOR AIRFOIL TIP CLEARANCE OPTIMIZATION SYSTEM 审中-公开
标题翻译：压缩机空气净化器间隙优化系统
公开(公告)号：WO2013126126A2
公开(公告)日：2013-08-29
申请号：PCT/US2012068466
申请日：2012-12-07
申请人： SIEMENS ENERGY INC , LITTLE DAVID A , PU ZHENGXIANG
发明人： LITTLE DAVID A , PU ZHENGXIANG
IPC分类号： F04D29/16
CPC分类号： F04D29/164 , F01D11/22 , F04D19/028 , F04D29/052 , F04D29/522
摘要： A compressor airfoil tip clearance optimization system for reducing a gap between a tip of a compressor airfoil and a radially adjacent component of a turbine engine is disclosed. The turbine engine may include ID and OD flowpath boundaries configured to minimize compressor airfoil tip clearances during turbine engine operation in cooperation with one or more clearance reduction systems that are configured to move the rotor assembly axially to reduce tip clearance. The configurations of the ID and OD flowpath boundaries enhance the effectiveness of the axial movement of the rotor assembly, which includes movement of the ID flowpath boundary. During operation of the turbine engine, the rotor assembly may be moved axially to increase the efficiency of the turbine engine.
摘要翻译：公开了一种用于减小压缩机叶片的尖端与涡轮发动机的径向相邻部件之间的间隙的压缩机翼型顶端间隙优化系统。涡轮发动机可以包括ID和OD流动路径边界，其被配置为在涡轮发动机运行期间最小化压缩机翼型顶端间隙，与一个或多个间隙减小系统配合，其被配置成轴向地移动转子组件以减小顶端间隙。 ID和OD流路边界的结构增强了转子组件的轴向运动的有效性，其包括ID流路边界的移动。在涡轮发动机的操作期间，转子组件可以轴向移动以提高涡轮发动机的效率。

9. 发明申请

WO2011156078A1 COOLED CONDUIT FOR CONVEYING COMBUSTION GASES IN A GAS TURBINE ENGINE 审中-公开
标题翻译：用于在气体涡轮发动机中输送燃烧气体的冷却管道
公开(公告)号：WO2011156078A1
公开(公告)日：2011-12-15
申请号：PCT/US2011/036058
申请日：2011-05-11
申请人： SIEMENS ENERGY, INC. , LEE, Ching-Pang , PRAKASH, Chander , SCHILP, Reinhard , LITTLE, David A.
发明人： LEE, Ching-Pang , PRAKASH, Chander , SCHILP, Reinhard , LITTLE, David A.
IPC分类号： F01D9/02 , F02K1/82 , F23R3/00
CPC分类号： F01D9/023 , F02K1/822 , F05D2250/13 , F05D2250/324 , F05D2260/202 , F23M20/005 , F23R3/002 , F23R3/06 , F23R2900/00014 , F23R2900/03042 , Y02T50/675
摘要： A conduit through which hot combustion gases pass in a gas turbine engine. The conduit includes a wall structure having a central axis and defining an inner volume of the conduit for permitting hot combustion gases to pass through the conduit. The wall structure includes a forward end, an aft end axially spaced from the forward end, the aft end defining a combustion gas outlet for the hot combustion gases passing through the conduit, and a plurality of generally radially outwardly extending protuberances formed in the wall structure. The protuberances each include at least one cooling fluid passage formed therethrough for permitting cooling fluid to enter the inner volume. At least one of the protuberances is shaped so as to cause cooling fluid passing through it to diverge in a circumferential direction as it enters into the inner volume.
摘要翻译：热燃气通过燃气涡轮发动机的导管。导管包括具有中心轴线并且限定导管的内部容积以允许热燃气体通过导管的壁结构。壁结构包括前端，与前端轴向间隔的后端，后端限定用于通过导管的热燃烧气体的燃烧气体出口，以及形成在壁结构中的多个大致径向向外延伸的突起。突起各自包括至少一个通过其形成的冷却流体通道，用于允许冷却流体进入内部容积。突起中的至少一个被成形为使得冷却流体通过它，当它进入内部体积时沿圆周方向发散。

10. 发明申请

WO2008123904A3 GAS TURBINE ENGINE ASSEMBLY 审中-公开
标题翻译：气体涡轮发动机总成
公开(公告)号：WO2008123904A3
公开(公告)日：2013-04-25
申请号：PCT/US2008001858
申请日：2008-02-13
申请人： SIEMENS ENERGY INC , MYERS GERALD A , LITTLE DAVID A
发明人： MYERS GERALD A , LITTLE DAVID A
IPC分类号： F02C9/20 , F01K13/02 , F02C9/18
CPC分类号： F01K13/02 , F02C9/18 , F02C9/20 , F05D2270/08
摘要： Aspects of the invention relate to a system and method for operating a turbine engine assembly. The turbine engine assembly has a turbine engine (10) having a compressor section (14), a combustor section (16) and a turbine section (18). The combustor section (16) has a lower primary zone temperature (T_PZ) limit and the turbine engine (10) has a design load. The assembly further includes at least one air bleed line (80) from the compressor (14) and at least one valve (84) for controlling air flow through the bleed line (80). Control structure (88) is provided for opening the valve (84) to allow bleed air to flow through the bleed line (80) when an operating load is less than the design load. The flow rate through the bleed line (80) is increased as the operating load is decreased, reducing the power delivered by the turbine assembly while maintaining the primary zone temperature (T_PZ) above a lower primary zone temperature (T_PZ) limit.
摘要翻译：本发明的方面涉及用于操作涡轮发动机组件的系统和方法。涡轮发动机组件具有涡轮发动机（10），其具有压缩机部分（14），燃烧器部分（16）和涡轮部分（18）。燃烧器部分（16）具有较低的主区温度（T_PZ）极限，并且涡轮发动机（10）具有设计负载。组件还包括来自压缩机（14）的至少一个排气管线（80）和用于控制通过排放管线（80）的空气流的至少一个阀门（84）。提供控制结构（88），用于当操作负载小于设计负荷时，打开阀（84）以允许排放空气流过排放管线（80）。通过泄放管线（80）的流量随着操作负荷的降低而增加，从而降低涡轮机组件输送的功率，同时保持初级区域温度（T_PZ）高于较低的初级区域温度（T_PZ）极限。

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