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    GAS TURBINE ENGINE CONFIGURED TO SHAPE POWER OUTPUT
    1.
    发明申请
    GAS TURBINE ENGINE CONFIGURED TO SHAPE POWER OUTPUT 有权
    气体涡轮发动机配置形成电源输出

    公开(公告)号：US20130227954A1

    公开(公告)日：2013-09-05

    申请号：US13754936

    申请日：2013-01-31

    Applicant: Bonnie D. Marini ,  Brian J. Bohinsky

    Inventor： Bonnie D. Marini ,  Brian J. Bohinsky

    IPC: F02C9/20

    CPC classification number: F02C9/20 ,  F02C7/057 ,  F02C9/28 ,  F02C9/54 ,  F05D2270/05 ,  F05D2270/20

    Abstract: A gas turbine engine and method of controlling the gas turbine engine that may be utilized in a power grid having a plurality of additional power generation sources. The gas turbine engine is configured with a compressor having an enlarged mass flow volume. The gas turbine engine may be operated at a base load for supplying power to the power grid at a part load and optimum efficiency for the engine, and may be ramped up to a higher output to supply a peak load output to the power grid.

    Abstract translation: 一种燃气涡轮发动机和控制可用于具有多个附加发电源的电网中的燃气涡轮发动机的方法。 燃气涡轮发动机配置有具有扩大的质量流量的压缩机。 燃气涡轮发动机可以在基本负载下操作，以在部分负载处为发电机提供电力并且对于发动机提供最佳效率，并且可以升高到更高的输出以向电网提供峰值负载输出。

    EXHAUST DIFFUSER FOR A GAS TURBINE, AND METHOD THEREOF
    2.
    发明申请
    EXHAUST DIFFUSER FOR A GAS TURBINE, AND METHOD THEREOF 审中-公开
    用于气体涡轮的排气歧管及其方法

    公开(公告)号：US20130121806A1

    公开(公告)日：2013-05-16

    申请号：US13811943

    申请日：2011-07-18

    Applicant: Alexander R. Beeck ,  Bonnie D. Marini

    Inventor： Alexander R. Beeck ,  Bonnie D. Marini

    IPC: F01D25/30

    CPC classification number: F01D25/30 ,  F05D2220/32 ,  F05D2250/232 ,  F05D2270/17 ,  F05D2270/301

    Abstract: An exhaust diffuser assembly is provided, particularly for a stationary gas turbine. The exhaust diffuser assembly includes a longitudinal axis, a diffuser inlet for receiving a turbine mainflow gas, a diffuser outlet, and a diverging diffuser wall having an adjustable geometry and forming a conduit for flow of the gas therethrough from the diffuser inlet to the diffuser outlet. The diffuser wall has a divergence angle ‘α’ with respect to the longitudinal axis. The diffuser assembly also has a diffuser geometry control device for controlling a recovery of pressure from the gas between the diffuser inlet and the diffuser outlet by adjusting the divergence angle ‘α’ of the diffuser wall to cause a resultant flow field of the gas that is attached to the diffuser wall.

    Abstract translation: 提供排气扩散器组件，特别是用于固定式燃气轮机。 排气扩散器组件包括纵向轴线，用于接收涡轮机主流气体的扩散器入口，扩散器出口和具有可调节几何形状的发散扩散壁，并形成用于气体从扩散器入口到扩散器出口流动的导管 。 扩散壁相对于纵向轴线具有发散角α'。 扩散器组件还具有扩散器几何控制装置，用于通过调节扩散壁的发散角“α”来控制从扩散器入口和扩散器出口之间的气体的压力恢复，从而导致气体的合成流场 附着在扩散壁上。

    Vane shroud through-flow platform cover
    5.
    发明授权
    Vane shroud through-flow platform cover 失效
    叶片护罩通流平台盖

    公开(公告)号：US07604456B2

    公开(公告)日：2009-10-20

    申请号：US11401987

    申请日：2006-04-11

    Applicant: Anthony L. Schiavo, Jr. ,  Bonnie D. Marini

    Inventor： Anthony L. Schiavo, Jr. ,  Bonnie D. Marini

    IPC: F04D29/40 ,  F03B11/02

    CPC classification number: F01D5/225 ,  F01D11/008 ,  F05D2240/80

    Abstract: A turbine vane array (10) for a combustion assembly (8) in a combustion turbine engine. The vane array (10) includes a plurality of stationary vane assemblies (12), each vane assembly (12) including at least one airfoil (24) and inner and outer shroud segments (26, 28) attached to opposing ends of the airfoil (24). The inner and outer shroud segments (26, 28) each include an inner face (34, 36) facing toward a gas path (13) extending through the vane array (10). A removable cover structure may be provided on the inner faces (34, 36) of the inner and outer shroud segments (26, 28). The cover structure may include removably attached insert elements (72, 72′) that are positioned on the inner faces (34, 36) extending between upstream edges (44) and downstream edges (46) of the shroud segments (26, 28) and extending between adjacent airfoils (24).

    Abstract translation: 一种用于燃气涡轮发动机中的燃烧组件（8）的涡轮叶片阵列（10）。 叶片阵列（10）包括多个静止叶片组件（12），每个叶片组件（12）包括至少一个翼型件（24），以及附接到翼型件的相对端部的内部和外侧护罩段（26,28） 24）。 内部和外部护罩段（26,28）各自包括面向延伸穿过叶片阵列（10）的气体路径（13）的内表面（34,36）。 可拆卸的盖结构可以设置在内和外护罩段（26,28）的内表面（34,36）上。 盖结构可以包括可移除地附接的插入元件（72,72'），其位于在护罩段（26,28）的上游边缘（44）和下游边缘（46）之间延伸的内表面（34,36）上，以及 在相邻的翼型件（24）之间延伸。

    Turbine vane with removable platform inserts
    6.
    发明申请
    Turbine vane with removable platform inserts 失效
    涡轮叶片带有可移动平台插入件

    公开(公告)号：US20080025842A1

    公开(公告)日：2008-01-31

    申请号：US11494177

    申请日：2006-07-27

    Applicant: Bonnie D. Marini ,  Anthony L. Schiavo

    Inventor： Bonnie D. Marini ,  Anthony L. Schiavo

    IPC: F01D11/00

    CPC classification number: F01D5/147 ,  F01D5/18 ,  F01D25/12 ,  F05D2230/80 ,  F05D2230/90 ,  F05D2240/80 ,  F05D2240/81 ,  F05D2300/21 ,  F05D2300/603 ,  F05D2300/611

    Abstract: Aspects of the invention are related to a turbine vane assembly in which at least one of the platforms is equipped with one or more removable platform inserts. The inserts can be used in those areas of the platform where failures or damage has been known to occur, among other locations. If an insert becomes damaged or is destroyed during engine operation, the insert can be easily replaced, and the platform frames and the airfoil can be reused. As a result, the overall life of the vane can be extended. Further, the inserts can be made of materials that can reduce cooling requirements compared to known turbine vanes, thereby allowing cooling air to be used for other uses in the engine.

    Abstract translation: 本发明的方面涉及涡轮叶片组件，其中至少一个平台装备有一个或多个可移除的平台插入件。 这些插入件可用于已知发生故障或损坏的平台的其他位置的那些区域。 如果在发动机运行期间插入件损坏或损坏，则可以方便地更换插入件，并可以重新使用平台框架和翼型件。 结果，叶片的整体寿命可以延长。 此外，与已知的涡轮叶片相比，插入件可以由能够降低冷却要求的材料制成，从而允许将冷却空气用于发动机中的其它用途。

    Ring seal for a turbine engine
    8.
    发明授权
    Ring seal for a turbine engine 有权
    涡轮发动机的环形密封

    公开(公告)号：US07871244B2

    公开(公告)日：2011-01-18

    申请号：US11707193

    申请日：2007-02-15

    Applicant: Bonnie D. Marini ,  Douglas A. Keller

    Inventor： Bonnie D. Marini ,  Douglas A. Keller

    IPC: F01D11/12

    CPC classification number: F01D11/122 ,  F05D2230/31 ,  F05D2230/90 ,  F05D2240/11 ,  F05D2240/127 ,  F05D2250/70 ,  F05D2250/71 ,  F05D2250/711 ,  F05D2260/30 ,  F05D2300/21

    Abstract: A turbine engine ring seal for sealing gaps between turbine engine outer seal segments and turbine blade tips. The turbine engine ring segment may have an inner radial surface that defines a portion of a gap gas flow path where the inner radial surface may be formed of an abradable ceramic coating and includes a plurality of gas flow protrusions that are oriented transverse to the gap gas flow path. The gas flow protrusions may induce vortices in the gas flow in the gap gas flow path. Additionally, the gas flow protrusions may be series of peaks and depressions between two adjacent peaks, where the depressions have an approximate semicircular shape. The distance between two adjacent peaks may be equal or greater than a width of the depression and the height of a single peak may be six percent or greater than the distance between two adjacent peaks.

    Abstract translation: 涡轮发动机环密封件，用于密封涡轮发动机外密封段和涡轮叶片尖端之间的间隙。 涡轮发动机环段可以具有限定间隙气体流动路径的一部分的内部径向表面，其中内部径向表面可以由可磨损陶瓷涂层形成，并且包括多个气体流动突起，其横向于间隙气体 流路。 气流突起可以在间隙气体流动路径中的气流中引起涡流。 此外，气流突起可以是两个相邻峰之间的一系列峰和凹陷，其中凹陷具有近似的半圆形。 两个相邻峰之间的距离可以等于或大于凹陷的宽度，单个峰的高度可以是两个相邻峰之间的距离的6％或更大。

    Turbine vanes with airfoil-proximate cooling seam
    9.
    发明授权
    Turbine vanes with airfoil-proximate cooling seam 失效
    涡轮叶片与翼面靠近的冷却缝

    公开(公告)号：US07581924B2

    公开(公告)日：2009-09-01

    申请号：US11494178

    申请日：2006-07-27

    Applicant: Bonnie D. Marini ,  Anthony L. Schiavo

    Inventor： Bonnie D. Marini ,  Anthony L. Schiavo

    IPC: F01D9/02

    CPC classification number: F01D5/147 ,  F01D5/081 ,  F01D9/041 ,  F01D11/005 ,  F05D2240/81

    Abstract: Aspects of the invention relate to a turbine vane in which the inner and outer platforms are located substantially entirely on either the pressure side or the suction side of the airfoil. When a plurality of such vanes are installed in the turbine, a seam is formed by the circumferential end of the inner and outer platforms and a portion of the airfoil of a neighboring vane. During engine operation, a high pressure coolant is supplied to at least one of the platforms. The coolant can leak through the seam. Because the seam is located proximate the airfoil, the coolant leakage through the seam can be productively used to cool the transition region between the vane platforms and the airfoil. In addition to such cooling benefits, aspects of the invention can result in a potential increase in engine efficiency as well as component life.

    Abstract translation: 本发明的方面涉及一种涡轮叶片，其中内平台和外平台基本上完全位于翼型的压力侧或吸力侧上。 当多个这样的叶片安装在涡轮机中时，由内平台和外平台的周向端部和相邻叶片的翼型的一部分形成接缝。 在发动机操作期间，向至少一个平台供应高压冷却剂。 冷却液可能通过接缝泄漏。 因为接缝位于翼型附近，所以通过接缝的冷却剂泄漏可以有效地用于冷却叶片平台和翼型之间的过渡区域。 除了这样的冷却效果之外，本发明的方面可以导致发动机效率以及部件寿命的潜在增加。

    Turbine vane with divided turbine vane platform
    10.
    发明申请
    Turbine vane with divided turbine vane platform 审中-公开
    涡轮叶片带有涡轮叶片平台

    公开(公告)号：US20080298973A1

    公开(公告)日：2008-12-04

    申请号：US11807390

    申请日：2007-05-29

    Applicant: Bonnie D. Marini

    Inventor： Bonnie D. Marini

    IPC: F01D5/14

    CPC classification number: F01D5/147 ,  F01D9/02 ,  F05D2240/80 ,  F05D2260/36

    Abstract: A turbine vane with endwalls, wherein at least one endwall is formed from two or more sections configured such that the sections form releasable joints with a generally elongated airfoil of the turbine vane. The sections may be configured to both support the generally elongated airfoil and to establish cooling fluid flowpaths between the sections and the generally elongated airfoil to cool the aspects of the turbine vane proximate to the intersection of the endwalls and the generally elongated airfoil. In addition, the joints between the generally elongated airfoil and the sections may be formed from a connection system that enables forces to be transmitted from the generally elongated airfoil to the endwalls without creating stresses found in conventional turbine vane fillets at the intersection between the generally elongated airfoil and the endwalls.

    Abstract translation: 具有端壁的涡轮叶片，其中至少一个端壁由两个或更多个部分形成，所述两个或多个部分构造成使得所述部分形成具有涡轮叶片的大致细长的翼型的可释放接头。 这些部分可以被构造成两者支撑大致细长的翼型件并且在部分和大体上细长的翼型之间建立冷却流体流动路径，以冷却靠近端壁和大致细长的翼型件的相交处的涡轮叶片的方面。 此外，大体细长的翼型件和部分之间的接头可以由连接系统形成，该连接系统使得能够将力从大体上细长的翼型件传递到端壁，而不产生在常规涡轮机叶片中的压力， 翼型和端壁。

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