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1. 发明授权

US06438961B2 Swozzle based burner tube premixer including inlet air conditioner for low emissions combustion 有权
标题翻译：基于喷嘴的燃烧器管预混合器，包括用于低排放燃烧的入口空调
公开(公告)号：US06438961B2
公开(公告)日：2002-08-27
申请号：US09811764
申请日：2001-03-20
申请人： Richard Sterling Tuthill , William Theodore Bechtel, II , Jeffrey Arthur Benoit , Stephen Hugh Black , Robert James Bland , Guy Wayne DeLeonardo , Stefan Martin Meyer , Joseph Charles Taura , John Luigi Battaglioli
发明人： Richard Sterling Tuthill , William Theodore Bechtel, II , Jeffrey Arthur Benoit , Stephen Hugh Black , Robert James Bland , Guy Wayne DeLeonardo , Stefan Martin Meyer , Joseph Charles Taura , John Luigi Battaglioli
IPC分类号： F23R314
CPC分类号： F23C7/004 , F23C2900/07001 , F23D14/02 , F23D2206/10 , F23D2900/14021 , F23M9/02
摘要： A burner for use in a combustion system of a heavy-duty industrial gas turbine includes a fuel/air premixer having an air inlet, a fuel inlet, and an annular mixing passage. The fuel/air premixer mixes fuel and air into a uniform mixture for injection into a combustor reaction zone. The burner also includes an inlet flow conditioner disposed at the air inlet of the fuel/air premixer for controlling a radial and circumferential distribution of incoming air. The pattern of perforations in the inlet flow conditioner is designed such that a uniform air flow distribution is produced at the swirler inlet annulus in both the radial and circumference directions. The premixer includes a swozzle assembly having a series of preferably air foil shaped turning vanes that impart swirl to the airflow entering via the inlet flow conditioner. Each air foil contains internal fuel flow passages that introduce natural gas fuel into the air stream via fuel metering holes that pass through the walls of the air foil shaped turning vanes. By injecting fuel in this manner, an aerodynamically clean flow field is maintained throughout the premixer. By injecting fuel via two separate passages, the fuel/air mixture strength distribution can be controlled in the radial direction to obtain optimum radial concentration profiles for control of emissions, lean blow outs, and combustion driven dynamic pressure activity as machine and combustor load are varied.
摘要翻译：用于重型工业燃气轮机的燃烧系统的燃烧器包括具有空气入口，燃料入口和环形混合通道的燃料/空气预混合器。燃料/空气预混合器将燃料和空气混合成均匀的混合物，用于注入燃烧器反应区。燃烧器还包括设置在燃料/空气预混合器的空气入口处的入口流动调节器，用于控制进入空气的径向和周向分布。入口流动调节器中的穿孔图案被设计成使得在径向和圆周方向上的旋流器入口环上产生均匀的气流分布。预混合器包括具有一系列优选为空气箔形的转动叶片的喷嘴组件，该旋转叶片赋予经由入口流动调节器进入的气流涡流。每个空气箔包含内部燃料流动通道，其通过燃烧计量孔将天然气燃料引入空气流中，所述燃料计量孔穿过所述翼状叶片的转动叶片的壁。通过以这种方式喷射燃料，在整个预混合器中保持空气动力学清洁的流场。通过经由两个独立的通道喷射燃料，燃料/空气混合物的强度分布可以在径向方向上被控制，以获得最佳径向浓度分布，用于控制排放，稀薄吹出和燃烧驱动的动态压力活动，因为机器和燃烧器负荷变化。

2. 发明授权

US06363724B1 Gas only nozzle fuel tip 失效
标题翻译：气体仅喷嘴燃油头
公开(公告)号：US06363724B1
公开(公告)日：2002-04-02
申请号：US09652176
申请日：2000-08-31
申请人： William Theodore Bechtel , David Orus Fitts , Guy Wayne DeLeonardo
发明人： William Theodore Bechtel , David Orus Fitts , Guy Wayne DeLeonardo
IPC分类号： F02C100
CPC分类号： F23D14/78 , F23D14/22 , F23D2211/00 , F23R2900/00001
摘要： A diffusion flame nozzle gas tip is provided to convert a dual fuel nozzle to a gas only nozzle. The nozzle tip diverts compressor discharge air from the passage feeding the diffusion nozzle air swirl vanes to a region vacated by removal of the dual fuel components, so that the diverted compressor discharge air can flow to and through effusion holes in the end cap plate of the nozzle tip. In a preferred embodiment, the nozzle gas tip defines a cavity for receiving the compressor discharge air from a peripheral passage of the nozzle for flow through the effusion openings defined in the end cap plate.
摘要翻译：设置扩散火焰喷嘴气体尖端以将双燃料喷嘴转换成仅气体喷嘴。喷嘴尖端将压缩机排出空气从通过供给扩散喷嘴空气旋流叶片的通道转移到通过去除双重燃料部件而腾出的区域，使得转向的压缩机排出的空气可以流过并通过端盖板中的渗出孔喷嘴尖端在优选实施例中，喷嘴气体尖端限定用于从喷嘴的周边通道接收压缩机排放空气的空腔，用于流过限定在端盖板中的渗出开口。

3. 发明授权

US07874156B2 Methods and apparatus for heating a fluid 失效
标题翻译：用于加热流体的方法和装置
公开(公告)号：US07874156B2
公开(公告)日：2011-01-25
申请号：US11693488
申请日：2007-03-29
申请人： Yu Wang , George Hanna Ghanime , Chi Tang , Guy Wayne DeLeonardo
发明人： Yu Wang , George Hanna Ghanime , Chi Tang , Guy Wayne DeLeonardo
IPC分类号： F02C7/08
CPC分类号： F02C7/224 , F02C6/18 , F28D7/0033
摘要： A method for heating a fluid in a turbine engine is provided. The method includes channeling an exhaust flow through an exhaust duct of the turbine engine and coupling a panel to the exhaust duct. The panel includes a first wall and an opposite second wall that is spaced a distance from the first wall such that at least one passageway is defined within the panel. The fluid is supplied to the at least one passageway through an inlet defined at a first end of the passageway, such that heat is transferred from the exhaust flow to the fluid flowing through the panel. The fluid is injected into the turbine engine.
摘要翻译：提供了一种用于加热涡轮发动机中的流体的方法。该方法包括将排气流引导通过涡轮发动机的排气管道并将面板连接到排气管道。面板包括第一壁和与第一壁隔开一定距离的相对的第二壁，使得至少一个通道限定在面板内。通过限定在通道的第一端处的入口将流体供应到至少一个通道，使得热量从排气流传递到流过面板的流体。流体被注入涡轮发动机。

4. 发明授权

US07153090B2 System and method for passive load attenuation in a wind turbine 有权
标题翻译：风力发电机中被动负载衰减的系统和方法
公开(公告)号：US07153090B2
公开(公告)日：2006-12-26
申请号：US11015259
申请日：2004-12-17
申请人： Guy Wayne DeLeonardo , Scott Roger Finn , Peter Michael Finnigan , Donald Joseph Kasperski
发明人： Guy Wayne DeLeonardo , Scott Roger Finn , Peter Michael Finnigan , Donald Joseph Kasperski
IPC分类号： F03B15/06
CPC分类号： F03D1/0675 , F05B2240/30 , F05B2240/301 , Y02E10/721
摘要： In accordance with certain embodiments, a wind turbine blade includes an outer skin and an internal support structure. The skin has a closed airfoil shape and includes an outer surface, an inner surface, and opposite sides along a length of the blade. The internal support structure is disposed within the closed airfoil shape. The internal support structure includes at least one shear load bearing member disposed across the opposite sides and oriented lengthwise along the length of the blade. The internal support structure further includes a plurality of bending load bearing members disposed along the inner surface in a lengthwise direction along the length of the blade. The internal support structure is configured to position a shear center and a center of aerodynamic pressure loading of the blade at different locations relative to one another.
摘要翻译：根据某些实施例，风力涡轮机叶片包括外部皮肤和内部支撑结构。皮肤具有封闭的翼型形状并且包括外表面，内表面和沿刀片的长度的相对侧。内部支撑结构设置在封闭的翼型形状内。内部支撑结构包括横跨相对侧设置并沿着叶片的长度沿纵向定向的至少一个剪切载荷承载构件。内部支撑结构还包括多个沿刀片的长度方向沿长度方向沿内表面设置的弯曲载荷承载部件。内部支撑结构构造成将叶片的剪切中心和空气动力学压力的中心相对于彼此定位在不同的位置。

5. 发明授权

US07079957B2 Method and system for active tip clearance control in turbines 失效
标题翻译：涡轮机主动顶盖间隙控制方法及系统
公开(公告)号：US07079957B2
公开(公告)日：2006-07-18
申请号：US10748812
申请日：2003-12-30
申请人： Peter Michael Finnigan , Mullahalli Venkataramaniah Srinivas , Robert Joseph Albers , Guy Wayne DeLeonardo
发明人： Peter Michael Finnigan , Mullahalli Venkataramaniah Srinivas , Robert Joseph Albers , Guy Wayne DeLeonardo
IPC分类号： G01R3/00 , F01D11/08 , F01D11/12
CPC分类号： F01D11/025 , F01D11/22 , F01D11/24 , F05D2270/62 , F05D2270/66
摘要： A system for controlling blade tip clearance in a turbine. The system includes a stator including a shroud having a plurality of shroud segments and a rotor including a blade rotatable within the shroud. An actuator assembly is positioned radially around the shroud and includes a plurality of actuators. A sensor senses a turbine parameter and generates a sensor signal representative of the turbine parameter. A modeling module generates a tip clearance prediction in response to turbine cycle parameters. A controller receives the sensor signal and the tip clearance prediction and generates at least one command signal. The actuators include at least one actuator receiving the command signal and adjusts a position of at least one of the shroud segments in response to the command signal.
摘要翻译：一种用于控制涡轮机叶片顶端间隙的系统。该系统包括定子，其包括具有多个护罩段的护罩和包括可在护罩内旋转的刀片的转子。致动器组件围绕护罩径向定位，并且包括多个致动器。传感器感测涡轮参数并产生代表涡轮机参数的传感器信号。建模模块响应于涡轮循环参数产生尖端间隙预测。控制器接收传感器信号和尖端间隙预测，并产生至少一个命令信号。致动器包括响应于命令信号接收命令信号并调节至少一个护罩段的位置的至少一个致动器。

6. 发明申请

US20080236800A1 METHODS AND APPARATUS FOR HEATING A FLUID 失效
标题翻译：用于加热流体的方法和装置
公开(公告)号：US20080236800A1
公开(公告)日：2008-10-02
申请号：US11693488
申请日：2007-03-29
申请人： Yu Wang , George Hanna Ghanime , Chi Tang , Guy Wayne DeLeonardo
发明人： Yu Wang , George Hanna Ghanime , Chi Tang , Guy Wayne DeLeonardo
IPC分类号： F28F99/00
CPC分类号： F02C7/224 , F02C6/18 , F28D7/0033
摘要： A method for heating a fluid in a turbine engine is provided. The method includes channeling an exhaust flow through an exhaust duct of the turbine engine and coupling a panel to the exhaust duct. The panel includes a first wall and an opposite second wall that is spaced a distance from the first wall such that at least one passageway is defined within the panel. The fluid is supplied to the at least one passageway through an inlet defined at a first end of the passageway, such that heat is transferred from the exhaust flow to the fluid flowing through the panel. The fluid is injected into the turbine engine.
摘要翻译：提供了一种用于加热涡轮发动机中的流体的方法。该方法包括将排气流引导通过涡轮发动机的排气管道并将面板连接到排气管道。面板包括第一壁和与第一壁隔开一定距离的相对的第二壁，使得至少一个通道限定在面板内。通过限定在通道的第一端处的入口将流体供应到至少一个通道，使得热量从排气流传递到流过面板的流体。流体被注入涡轮发动机。

7. 发明授权

US06460326B2 Gas only nozzle 失效
标题翻译：气体喷嘴
公开(公告)号：US06460326B2
公开(公告)日：2002-10-08
申请号：US09994830
申请日：2001-11-28
申请人： William Theodore Bechtel , David Orus Fitts , Guy Wayne DeLeonardo
发明人： William Theodore Bechtel , David Orus Fitts , Guy Wayne DeLeonardo
IPC分类号： F02C322
CPC分类号： F23D14/78 , F23D14/22 , F23D2211/00 , F23R2900/00001
摘要： A diffusion flame nozzle gas tip is provided to convert a dual fuel nozzle to a gas only nozzle. The nozzle tip diverts compressor discharge air from the passage feeding the diffusion nozzle air swirl vanes to a region vacated by removal of the dual fuel components, so that the diverted compressor discharge air can flow to and through effusion holes in the end cap plate of the nozzle tip. In a preferred embodiment, the nozzle gas tip defines a cavity for receiving the compressor discharge air from a peripheral passage of the nozzle for flow through the effusion openings defined in the end cap plate.
摘要翻译：设置扩散火焰喷嘴气体尖端以将双燃料喷嘴转换成仅气体喷嘴。喷嘴尖端将压缩机排出空气从通过供给扩散喷嘴空气旋流叶片的通道转移到通过去除双重燃料部件而腾出的区域，使得转向的压缩机排出的空气可以流过并通过端盖板中的渗出孔喷嘴尖端在优选实施例中，喷嘴气体尖端限定用于从喷嘴的周边通道接收压缩机排出空气的空腔，用于流过限定在端盖板中的积液开口。

8. 发明授权

US06453673B1 Method of cooling gas only nozzle fuel tip 失效
标题翻译：冷却气体喷嘴燃料端的方法
公开(公告)号：US06453673B1
公开(公告)日：2002-09-24
申请号：US09994831
申请日：2001-11-28
申请人： William Theodore Bechtel , David Orus Fitts , Guy Wayne DeLeonardo
发明人： William Theodore Bechtel , David Orus Fitts , Guy Wayne DeLeonardo
IPC分类号： F02C726
CPC分类号： F23D14/78 , F23D14/22 , F23D2211/00 , F23R2900/00001
摘要： A diffusion flame nozzle gas tip is provided to convert a dual fuel nozzle to a gas only nozzle. The nozle tip diverts compressor discharge air from the passage feeding the diffusion nozzle air swirl vanes to a region vacated by removal of the dual fuel components, so that the diverted compressor discharge air can flow to and through effusion holes in the end cap plate of the nozzle tip. In a preferred embodiment, the nozzle gas tip defines a cavity for receiving the compressor discharge air from a peripheral passage of the nozzle for flow through the effusion openings defined in the end cap plate.
摘要翻译：设置扩散火焰喷嘴气体尖端以将双燃料喷嘴转换成仅气体喷嘴。尖顶部将压缩机排放空气从通过供给扩散喷嘴空气旋流叶片的通道转移到通过去除双燃料部件而腾出的区域，使得转向的压缩机排出的空气可以流过并通过端盖板中的排出孔喷嘴尖端在优选实施例中，喷嘴气体尖端限定用于从喷嘴的周边通道接收压缩机排出空气的空腔，用于流过限定在端盖板中的积液开口。

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