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1. 发明申请

US20100269481A1 SYSTEMS AND METHODS FOR PROVIDING SURGE PROTECTION TO A TURBINE COMPONENT 有权
标题翻译：用于向涡轮机组件提供防护的系统和方法
公开(公告)号：US20100269481A1
公开(公告)日：2010-10-28
申请号：US12428769
申请日：2009-04-23
申请人： David August Snider , Harold Lamar Jordan, JR. , Timothy Andrew Healy , John David Stampfli
发明人： David August Snider , Harold Lamar Jordan, JR. , Timothy Andrew Healy , John David Stampfli
IPC分类号： F02C9/00
CPC分类号： F02C9/00 , F05D2260/80 , F05D2270/101
摘要： Systems and methods for providing surge protection to turbine components are provided. A surge protection limit may be determined for the turbine component. One or more measurements associated with operation of the turbine component may be received and provided to a cycle model executed to predict an operating condition of the turbine component. The predicted operating condition of the turbine component may be adjusted based at least in part on the received one or more measurements. The surge protection limit may be adjusted based on the adjusted predicted operating condition of the turbine component.
摘要翻译：提供了用于向涡轮机部件提供喘振保护的系统和方法。可以为涡轮机部件确定浪涌保护极限。可以接收与涡轮机部件的操作相关联的一个或多个测量，并且将其提供给执行以预测涡轮机部件的操作状态的循环模型。可以至少部分地基于所接收的一个或多个测量来调整涡轮机部件的预测操作状态。浪涌保护极限可以根据调整后的涡轮机部件的运行状况进行调整。

2. 发明授权

US08322145B2 Systems and methods for providing surge protection to a turbine component 有权
标题翻译：为涡轮机部件提供喘振保护的系统和方法
公开(公告)号：US08322145B2
公开(公告)日：2012-12-04
申请号：US12428769
申请日：2009-04-23
申请人： David August Snider , Harold Lamar Jordan, Jr. , Timothy Andrew Healy , John David Stampfli
发明人： David August Snider , Harold Lamar Jordan, Jr. , Timothy Andrew Healy , John David Stampfli
IPC分类号： F02C7/00
CPC分类号： F02C9/00 , F05D2260/80 , F05D2270/101
摘要： Systems and methods for providing surge protection to turbine components are provided. A surge protection limit may be determined for the turbine component. One or more measurements associated with operation of the turbine component may be received and provided to a cycle model executed to predict an operating condition of the turbine component. The predicted operating condition of the turbine component may be adjusted based at least in part on the received one or more measurements. The surge protection limit may be adjusted based on the adjusted predicted operating condition of the turbine component.
摘要翻译：提供了用于向涡轮机部件提供喘振保护的系统和方法。可以为涡轮机部件确定浪涌保护极限。可以接收与涡轮机部件的操作相关联的一个或多个测量，并且将其提供给执行以预测涡轮机部件的操作状态的循环模型。可以至少部分地基于所接收的一个或多个测量来调整涡轮机部件的预测操作状态。浪涌保护极限可以根据调整后的涡轮机部件的运行状况进行调整。

3. 发明授权

US08510013B2 Gas turbine shutdown 有权
标题翻译：燃气轮机停机
公开(公告)号：US08510013B2
公开(公告)日：2013-08-13
申请号：US12434755
申请日：2009-05-04
申请人： Harold Lamar Jordan, Jr. , David August Snider
发明人： Harold Lamar Jordan, Jr. , David August Snider
IPC分类号： F02C9/00 , F02C9/26 , F02C9/48 , F02C7/057
CPC分类号： F02C9/48 , F01D21/00 , F05D2270/304 , Y02T50/671
摘要： A gas turbine includes a rotor, and a controller for controlling a shutdown of the gas turbine based on a target fuel-to-air ratio profile and/or controlling a rotor speed according to a target speed schedule to attain a specified duration for the shutdown. The controller controls the rotor speed by engaging the starting system to turn the rotor.
摘要翻译：燃气轮机包括转子和控制器，用于根据目标速度调度来控制燃气轮机的目标燃料空气比分布和/或控制转子速度以达到停机的指定持续时间。控制器通过接合启动系统来转动转子来控制转子速度。

4. 发明申请

US20130103323A1 TURBINE RADIAL SENSOR MEASUREMENT 审中-公开
标题翻译：涡轮径向传感器测量
公开(公告)号：US20130103323A1
公开(公告)日：2013-04-25
申请号：US13280565
申请日：2011-10-25
申请人： David August Snider , Harold Lamar Jordan, JR. , Christopher Ryan Holsonback
发明人： David August Snider , Harold Lamar Jordan, JR. , Christopher Ryan Holsonback
IPC分类号： G06F19/00 , G01L7/00 , G06F17/18
CPC分类号： F01D17/08 , F01D21/003 , F05D2200/00
摘要： A method of measuring parameters of a gas turbine flow path is described. The method includes installing along one or more existing struts in the gas turbine flow path a first plurality of sensors for measuring a first parameter at one or more radial positions along the one or more struts and a second plurality of sensors for measuring a second parameter at one or more radial positions along the one or more struts. The method further includes producing an actual profile of the gas turbine flow path first parameter and second parameter.
摘要翻译：描述了一种测量燃气轮机流路参数的方法。该方法包括沿燃气涡轮机流路中的一个或多个现有支柱安装第一多个传感器，用于测量沿着一个或多个支柱的一个或多个径向位置处的第一参数和用于测量第二参数的第二多个传感器沿着一个或多个支柱的一个或多个径向位置。该方法还包括产生燃气轮机流路第一参数和第二参数的实际轮廓。

5. 发明申请

US20100280733A1 GAS TURBINE SHUTDOWN 有权
标题翻译：燃气轮机关闭
公开(公告)号：US20100280733A1
公开(公告)日：2010-11-04
申请号：US12434755
申请日：2009-05-04
申请人： Harold Lamar Jordan, JR. , David August Snider
发明人： Harold Lamar Jordan, JR. , David August Snider
IPC分类号： F02C9/00
CPC分类号： F02C9/48 , F01D21/00 , F05D2270/304 , Y02T50/671
摘要： A gas turbine includes a rotor, and a controller for controlling a shutdown of the gas turbine based on a target fuel-to-air ratio profile and/or controlling a rotor speed according to a target speed schedule to attain a specified duration for the shutdown. The controller controls the rotor speed by engaging the starting system to turn the rotor.
摘要翻译：燃气轮机包括转子和控制器，用于根据目标速度调度控制燃气轮机的目标燃料空气比分布和/或控制转子速度，以达到关闭的指定持续时间。控制器通过接合启动系统来转动转子来控制转子速度。

6. 发明申请

US20110185743A1 Methods For Operating Gas Turbine Engines 有权
标题翻译：操作燃气轮机发动机的方法
公开(公告)号：US20110185743A1
公开(公告)日：2011-08-04
申请号：US13085769
申请日：2011-04-13
申请人： David August Snider , Willy Steve Ziminsky
发明人： David August Snider , Willy Steve Ziminsky
IPC分类号： F02C7/22
CPC分类号： F02C7/222 , F02C7/228 , F05D2270/30 , F05D2270/54
摘要： Fuel is delivered in a gas turbine engine including a can annular combustor array that includes at least one combustor level subset within the array supplied by an independent fuel delivery system. Fuel is supplied only to one or more subsets during a first mode of operation. Fuel is supplied to the entire array of combustors during a second mode of operation.
摘要翻译：燃料在包括罐环形燃烧器阵列的燃气涡轮发动机中输送，所述罐环形燃烧器阵列包括由独立燃料输送系统提供的阵列内的至少一个燃烧器级子集。在第一操作模式期间，燃料仅供应给一个或多个子集。在第二种操作模式期间，燃料供应给整个燃烧器阵列。

7. 发明申请

US20100280731A1 SYSTEMS AND METHODS FOR CONTROLLING FUEL FLOW TO A TURBINE COMPONENT 有权
标题翻译：用于控制燃油流向涡轮机组件的系统和方法
公开(公告)号：US20100280731A1
公开(公告)日：2010-11-04
申请号：US12432867
申请日：2009-04-30
申请人： David August Snider
发明人： David August Snider
IPC分类号： F02C9/26 , F02C7/22
CPC分类号： F02C9/28 , F02C9/26 , F02C9/32 , F02C9/40 , F05D2260/81
摘要： Systems and methods for controlling fuel flow to a turbine component are provided. One or more parameters associated with a fuel flow to a turbine component may be monitored. The fuel flow may be modeled based at least in part on the one or more monitored parameters. The fuel flow may be adjusted to a target flow based at least in part on the modeling of the fuel flow.
摘要翻译：提供了用于控制到涡轮机部件的燃料流的系统和方法。可以监测与到涡轮机部件的燃料流相关联的一个或多个参数。燃料流可以至少部分地基于一个或多个监测的参数来建模。燃料流可以至少部分地基于燃料流的建模来调整到目标流。

8. 发明授权

US08965728B2 Exhaust strut radial temperature measurement 有权
标题翻译：排气支柱径向温度测量
公开(公告)号：US08965728B2
公开(公告)日：2015-02-24
申请号：US13104250
申请日：2011-05-10
申请人： David August Snider , Harold Jordan , Christopher Holsonback
发明人： David August Snider , Harold Jordan , Christopher Holsonback
IPC分类号： F01D21/00 , F01D25/30 , F01D21/12
CPC分类号： F01D21/003 , F01D25/30 , F05D2270/303
摘要： A method is disclosed for providing a real time, radial exhaust temperature distribution in a gas turbine to improve the understanding of exhaust gas temperature in a manner similar to installing production rakes. The thermocouples are installed along the exhaust frame strut skins at a number of radial positions. The data from the thermocouples along each of the struts is used to produce a normalized radial profile of the turbine exhaust temperature. The existing turbine station instrumentation is then used to expand the normalized profile into an actual profile of the turbine exhaust temperature. The calculations/transfer functions for temperatures are obtained from data collected during performance testing with full rakes. This profile is integrated to determine a bulk Tx to improve gas turbine controls including model-based controls or corrected parameter controls (MBC/CPC) controls, or specific radial temperatures are used, to provide protective action for bucket platforms, or other turbine components.
摘要翻译：公开了一种用于在燃气轮机中提供实时，径向排气温度分布的方法，以类似于安装生产耙子的方式提高对排气温度的理解。热电偶沿着排气框架支柱表面安装在多个径向位置。沿着每个支柱的热电偶的数据用于产生涡轮排气温度的归一化径向轮廓。然后使用现有的涡轮机站仪器将归一化轮廓扩展为涡轮排气温度的实际轮廓。温度的计算/传递函数是从完整耙子的性能测试期间收集的数据获得的。该配置文件集成以确定批量Tx，以改进燃气轮机控制，包括基于模型的控制或校正的参数控制（MBC / CPC）控制或使用特定径向温度，为铲斗平台或其他涡轮机部件提供保护作用。

9. 发明申请

US20100287944A1 AVAILABILITY IMPROVEMENTS TO HEAVY FUEL FIRED GAS TURBINES 审中-公开
标题翻译：重型燃油燃气涡轮机的可用性改进
公开(公告)号：US20100287944A1
公开(公告)日：2010-11-18
申请号：US12767134
申请日：2010-04-26
申请人： Sam David Draper , David August Snider , Robert Thomas Thatcher
发明人： Sam David Draper , David August Snider , Robert Thomas Thatcher
IPC分类号： F02C9/00
CPC分类号： F02C9/00 , F01D21/00 , F05D2260/80 , F05D2260/85 , F05D2260/94 , F05D2260/941
摘要： Maintenance operations for a hot gas path of a gas turbine require shutdown and cooled down conditions. When a gas turbine is shut down, thermal gradients in the rotor cause stresses that limit the life of the major components. As the cooling rate is increased to reduce the time, the stresses are increased, reducing rotor life. A method and equipment are provided to reduce the overall cycle time for the maintenance, yet mitigate the life penalties, thereby providing greater power production while maintaining (or potentially extending) rotor life. The method includes small hold times during the turbine shutdown and startup and slower turbine ramp rates during cooldown and startup, which more than offset thermal stresses from a forced cooldown, considerably shortening the overall operation.
摘要翻译：燃气轮机的热气路的维护操作需要关闭和冷却条件。当燃气轮机关闭时，转子中的热梯度会引起限制主要部件寿命的应力。随着冷却速度的增加，减少时间，应力增加，减少转子寿命。提供了一种方法和设备，以减少维护的整个周期时间，同时减轻寿命，从而在保持（或潜在地延长）转子寿命的同时提供更大的功率生产。该方法在涡轮机关闭和启动期间具有小的保持时间，并且在冷却和启动期间较慢的涡轮增压速率，其超过抵消强制冷却时的热应力，显着缩短了整个操作。

10. 发明申请

US20100275608A1 Systems and Methods for Rapid Turbine Deceleration 审中-公开
标题翻译：快速涡轮减速系统与方法
公开(公告)号：US20100275608A1
公开(公告)日：2010-11-04
申请号：US12826733
申请日：2010-06-30
申请人： David August Snider , John David Memmer
发明人： David August Snider , John David Memmer
IPC分类号： F02C7/268 , F02C7/26 , F02C7/00
CPC分类号： F01D21/00 , F01D21/14 , F02C7/268 , F02C9/48 , F02C9/56 , F05D2220/76 , F05D2260/85 , F05D2260/903 , F05D2270/304
摘要： The present application provides for a gas turbine engine system for turbine deceleration during shutdown procedures. The gas turbine engine system may include a rotor extending through a turbine, a generator engaged with the rotor, and a starting system in communication with the rotor. The starting system may reverse the operation of the generator so as to apply torque to the rotor during the shutdown procedures.
摘要翻译：本申请提供了一种用于在关闭过程期间涡轮减速的燃气涡轮发动机系统。燃气涡轮发动机系统可以包括延伸穿过涡轮机的转子，与转子接合的发电机以及与转子连通的启动系统。启动系统可以使发电机的操作反转，以便在关机过程中向转子施加扭矩。

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