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公开(公告)号：US20100251727A1
公开(公告)日：2010-10-07
申请号：US11784150
申请日：2007-04-05
申请人： Gerald A. Myers , David A. Little
发明人： Gerald A. Myers , David A. Little
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 having a compressor section, a combustor section and a turbine section. The combustor section has a lower T_PZ limit and the turbine engine has a design load. The assembly further includes at least one air bleed line from the compressor and at least one valve for controlling air flow through the bleed line. Control structure is provided for opening the valve to allow bleed air to flow through the bleed line when an operating load is less than the design load. The flow rate through the bleed line 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，其具有压缩机部分，燃烧器部分和涡轮部分。 燃烧器部分具有较低的T_PZ限制，并且涡轮发动机具有设计负载。 组件还包括来自压缩机的至少一个排气管线和用于控制通过排放管线的空气流的至少一个阀门。 提供控制结构用于打开阀门，以便当操作负载小于设计负载时允许排放空气流过排放管线。 通过泄放管线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。
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公开(公告)号：US08015826B2
公开(公告)日：2011-09-13
申请号：US11784150
申请日：2007-04-05
申请人： Gerald A. Myers , David A. Little
发明人： Gerald A. Myers , David A. Little
IPC分类号： F02C6/04
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 having a compressor section, a combustor section and a turbine section. The combustor section has a lower T_PZ limit and the turbine engine has a design load. The assembly further includes at least one air bleed line from the compressor and at least one valve for controlling air flow through the bleed line. Control structure is provided for opening the valve to allow bleed air to flow through the bleed line when an operating load is less than the design load. The flow rate through the bleed line 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，其具有压缩机部分，燃烧器部分和涡轮部分。 燃烧器部分具有较低的T_PZ限制，并且涡轮发动机具有设计负载。 组件还包括来自压缩机的至少一个排气管线和用于控制通过排放管线的空气流的至少一个阀门。 提供控制结构用于打开阀门，以便当操作负载小于设计负载时允许排放空气流过排放管线。 通过泄放管线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。
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3.发明授权Mid-section of a can-annular gas turbine engine with a radial air flow discharged from the compressor section 有权具有从压缩机部分排放的径向气流的罐环式燃气涡轮发动机的中部公开(公告)号：US09476355B2
公开(公告)日：2016-10-25
申请号：US13408147
申请日：2012-02-29
CPC分类号： F02C3/14
摘要： A midframe portion (213) of a gas turbine engine (210) is presented, and includes a compressor section (212) configured to discharge an air flow (211) directed in a radial direction from an outlet of the compressor section (212). Additionally, the midframe portion (213) includes a manifold (214) to directly couple the air flow (211) from the compressor section (212) outlet to an inlet of a respective combustor head (218) of the midframe portion (213).
摘要翻译： 呈现燃气涡轮发动机（210）的中架部分（213），并且包括被配置为从压缩机部分（212）的出口排出径向指向的空气流（211）的压缩机部分（212）。 另外，中框部分（213）包括将空气流（211）从压缩机部分（212）出口直接联接到中架部分（213）的相应燃烧器头部（218）的入口的歧管（214）。
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4.发明授权Mid-section of a can-annular gas turbine engine with an improved rotation of air flow from the compressor to the turbine 有权具有改进的从压缩机到涡轮机的空气流的旋转的罐环式燃气涡轮发动机的中部公开(公告)号：US09291063B2
公开(公告)日：2016-03-22
申请号：US13408287
申请日：2012-02-29
摘要： A midframe portion (313) of a gas turbine engine (310) is presented and includes a compressor section with a last stage blade to orient an air flow (311) at a first angle (372). The midframe portion (313) further includes a turbine section with a first stage blade to receive the air flow (311) oriented at a second angle (374). The midframe portion (313) further includes a manifold (314) to directly couple the air flow (311) from the compressor section to a combustor head (318) upstream of the turbine section. The combustor head (318) introduces an offset angle in the air flow (311) from the first angle (372) to the second angle (374) to discharge the air flow (311) from the combustor head (318) at the second angle (374). While introducing the offset angle, the combustor head (318) at least maintains or augments the first angle (372).
摘要翻译： 呈现燃气涡轮发动机（310）的中架部分（313）并且包括具有最后级叶片的压缩机部分，以使空气流（311）以第一角度（372）定向。 中间部分（313）还包括具有第一级叶片的涡轮机部分，以接收以第二角度（374）定向的空气流（311）。 中间部分（313）还包括歧管（314），用于将空气流（311）从压缩机部分直接耦合到涡轮部分上游的燃烧器头部（318）。 燃烧器头部（318）将空气流（311）中的偏移角从第一角度（372）引入第二角度（374），以使空气流（311）以第二角度从燃烧器头部（318）排出 （374）。 在引入偏移角的同时，燃烧器头（318）至少保持或增加第一角度（372）。
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公开(公告)号：US20140321981A1
公开(公告)日：2014-10-30
申请号：US13871080
申请日：2013-04-26
IPC分类号： F01D11/24
摘要： A turbine engine shutdown temperature control system configured to foster consistent air temperature within cavities surrounding compressor and turbine blade assemblies to eliminate turbine and compressor blade tip rub during warm restarts of gas turbine engines is disclosed. The turbine engine shutdown temperature control system may include one or more air amplifiers positioned in a turbine case. An exhaust outlet of the air amplifier may extend into a cavity created by a turbine case and may be configured to exhaust air in a generally circumferential direction to entrain air within the cavity to flow circumferentially to establish a consistent air temperature within the cavity thereby preventing uneven cooling of turbine engine components after shutdown and prevent damage to turbine components during a warm restart.
摘要翻译： 公开了一种涡轮发动机关闭温度控制系统，其被配置成在压缩机和涡轮叶片组件周围的空腔内促进恒定的空气温度，以消除燃气涡轮发动机的热重启期间的涡轮机和压缩机叶片尖端摩擦。 涡轮发动机关闭温度控制系统可以包括定位在涡轮机壳体中的一个或多个空气放大器。 空气放大器的排气出口可以延伸到由涡轮壳体产生的空腔中，并且可以被配置为沿大致圆周方向排出空气以夹带空腔内的空气以周向流动，以在空腔内建立一致的空气温度，从而防止不均匀 关闭后对涡轮发动机部件进行冷却，并防止在热启动期间对涡轮机部件造成损坏。
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公开(公告)号：US20120201695A1
公开(公告)日：2012-08-09
申请号：US12486249
申请日：2009-06-17
申请人： David A. Little
发明人： David A. Little
IPC分类号： F01D5/18
CPC分类号： F01D5/20 , F01D5/187 , F05D2250/611 , F05D2260/202
摘要： A turbine blade includes an airfoil, a blade tip section, a squealer tip rail, and a plurality of chordally spaced fence members. The blade tip section includes a blade tip floor located at an end of the airfoil distal from the root. The blade tip floor includes a pressure side and a suction side joined together at chordally spaced apart leading and trailing edges of the airfoil. The squealer tip rail extends radially outwardly from the blade tip floor adjacent to the suction side and extends from a first location adjacent to the airfoil trailing edge to a second location adjacent to the airfoil leading edge. The fence members are located between the airfoil leading and trailing edges and extend radially outwardly from the blade tip floor and axially from the squealer tip rail toward the pressure side.
摘要翻译： 涡轮机叶片包括翼型件，叶片尖端部分，尖叫尖端导轨和多个弦向间隔的栅栏构件。 叶片尖端部分包括位于远离根部的翼型的端部处的叶片顶部底部。 叶片顶部底板包括在翼型的弦向间隔开的前缘和后缘处连接在一起的压力侧和吸力侧。 尖叫尖端导轨从邻近吸力侧的叶片尖端底板径向向外延伸，并且从邻近翼型后缘的第一位置延伸到与翼型件前缘相邻的第二位置。 篱笆构件位于翼型件前缘和后缘之间并且从叶片尖端地面径向向外延伸并且从起搏器尖端轨道朝向压力侧轴向延伸。
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7.发明授权Fuel heating system used in conjunction with steam cooled combustors and transitions 失效燃油加热系统与蒸汽冷却燃烧器和过渡组合使用
公开(公告)号：US5826430A
公开(公告)日：1998-10-27
申请号：US636430
申请日：1996-04-23
申请人： David A. Little
发明人： David A. Little
摘要： A system is disclosed that provides for a more efficient combined cycle turbine system by using heated coolant returning from the gas turbine engine to pre-heat fuel before that fuel is injected into the combustor. Coolant, such as steam, that is used to cool gas turbine combustors and/or transitions carries high grade heat energy that was removed from the top cycle. By returning the heat energy to the incoming fuel, energy is recovered at a more efficient rate than would result from recovering that heat energy in the bottom cycle.
摘要翻译： 公开了一种系统，其通过使用从燃气涡轮发动机返回的加热的冷却剂在燃料被喷射到燃烧器中之前对燃料进行预热来提供更有效的联合循环涡轮机系统。 用于冷却燃气轮机燃烧器和/或过渡的冷却剂，例如蒸汽，从顶部循环中移除高质量的热能。 通过将热能返回到进入的燃料中，以比在底部循环中回收热能所产生的更有效的速率回收能量。
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公开(公告)号：USD309583S
公开(公告)日：1990-07-31
申请号：US34053
申请日：1987-04-02
申请人： Don H. Little , David A. Little
设计人： Don H. Little , David A. Little
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公开(公告)号：US10100737B2
公开(公告)日：2018-10-16
申请号：US13895831
申请日：2013-05-16
摘要： A cooling arrangement (100), including: a substrate having a pocket (24) defined by a rib side surface (28) and a bottom surface (26); a feature (112) formed in the rib side surface; and an impingement plate (102). In an installed configuration (116) a resilience of the impingement plate enables an interference between the impingement plate and the feature that locks the impingement plate in an installed position (118). An elastic compression of the impingement plate from the installed configuration eliminates the interference.
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公开(公告)号：US09388738B2
公开(公告)日：2016-07-12
申请号：US13252325
申请日：2011-10-04
摘要： A casing for a can annular gas turbine engine, including: a compressed air section (40) spanning between a last row of compressor blades (26) and a first row of turbine blades (28), the compressed air section (40) having a plurality of openings (50) there through, wherein a single combustor/advanced duct assembly (64) extends through each opening (50); and one top hat (68) associated with each opening (50) configured to enclose the associated combustor/advanced duct assembly (64) and seal the opening (50). A volume enclosed by the compressed air section (40) is not greater than a volume of a frustum (54) defined at an upstream end (56) by an inner diameter of the casing at the last row of compressor blades (26) and at a downstream end (60) by an inner diameter of the casing at the first row of turbine blades (28).
摘要翻译： 一种用于罐式环形燃气涡轮发动机的壳体，包括：压缩空气部分（40），跨过最后一排压缩机叶片（26）和第一排涡轮叶片（28），压缩空气部分（40）具有 多个开口（50）穿过其中，其中单个燃烧器/先进管道组件（64）延伸穿过每个开口（50）; 以及与每个开口（50）相关联的一个顶帽（68），其构造成包围相关联的燃烧器/先进管道组件（64）并密封所述开口（50）。 由压缩空气部分（40）包围的体积不大于在上游端（56）处由最后一排压缩机叶片（26）处的壳体的内径限定的平截头体（54）的体积，并且在 在第一排涡轮叶片（28）处通过壳体的内径的下游端（60）。
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