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1. 发明授权

US08444152B2 Spring seal assembly and method of sealing a gap 有权
标题翻译：弹簧密封组合和密封方法密封
公开(公告)号：US08444152B2
公开(公告)日：2013-05-21
申请号：US13100554
申请日：2011-05-04
申请人： Onika Misasha Kerber , David Richard Johns
发明人： Onika Misasha Kerber , David Richard Johns
IPC分类号： F16J15/02
CPC分类号： F16J15/0893 , F01D11/005 , F05D2240/11
摘要： A spring seal assembly includes a first plate and a second plate. One or more spring elements are located between the first plate and the second plate and compressible therebetween. The spring seal assembly is insertable into a gap between two adjacent components such that at least one of the first plate and the second plate at least partially block a flow between the two adjacent components while exerting a force on the two adjacent components to prevent vibration of the seal in the gap. A method of sealing between adjacent components includes at least partially compressing a spring seal assembly. The spring seal assembly is inserted into the gap and allowed to expand in the gap thereby at least partially blocking a flow between the two adjacent components while exerting a force on the two adjacent components to prevent vibration of the seal in the gap.
摘要翻译：弹簧密封组件包括第一板和第二板。一个或多个弹簧元件位于第一板和第二板之间，并且在它们之间可压缩。弹簧密封组件可插入到两个相邻部件之间的间隙中，使得第一板和第二板中的至少一个至少部分地阻挡两个相邻部件之间的流动，同时在两个相邻部件上施加力以防止密封在间隙。相邻部件之间的密封方法包括至少部分地压缩弹簧密封组件。弹簧密封组件插入到间隙中并允许在间隙中膨胀，从而至少部分地阻塞两个相邻部件之间的流动，同时在两个相邻部件上施加力以防止密封件在间隙中的振动。

2. 发明申请

US20120328421A1 METHODS AND SYSTEMS FOR COOLING A TRANSITION NOZZLE 有权
标题翻译：用于冷却过渡喷嘴的方法和系统
公开(公告)号：US20120328421A1
公开(公告)日：2012-12-27
申请号：US13164887
申请日：2011-06-21
申请人： Kevin Weston McMahan , Ronald James Chila , David Richard Johns
发明人： Kevin Weston McMahan , Ronald James Chila , David Richard Johns
IPC分类号： F01D25/24 , B23P15/04
CPC分类号： F01D9/023 , F05D2260/20 , F23R3/002 , F23R3/06 , F23R3/346 , F23R2900/03041 , F23R2900/03042 , Y02T50/675 , Y10T29/4932 , Y10T29/49323
摘要： A turbine assembly includes a fuel nozzle configured to mix fuel and air and a transition nozzle oriented to receive the fuel and air mixture from the fuel nozzle. The transition nozzle includes a transition portion and a nozzle portion integrally formed with the transition portion. The transition nozzle includes a plurality of openings oriented to channel air to facilitate cooling the transition portion and/or the nozzle portion. The transition portion is oriented to channel combustion gases towards the nozzle portion.
摘要翻译：涡轮组件包括构造成混合燃料和空气的燃料喷嘴和定向成从燃料喷嘴接收燃料和空气混合物的过渡喷嘴。过渡喷嘴包括过渡部分和与过渡部分一体形成的喷嘴部分。过渡喷嘴包括定向成引导空气以便于冷却过渡部分和/或喷嘴部分的多个开口。过渡部分被定向成将燃烧气体引向喷嘴部分。

3. 发明申请

US20110110771A1 AIRFOIL HEAT SHIELD 有权
标题翻译：空气温度传感器
公开(公告)号：US20110110771A1
公开(公告)日：2011-05-12
申请号：US12615674
申请日：2009-11-10
申请人： Victor John Morgan , David Richard Johns
发明人： Victor John Morgan , David Richard Johns
IPC分类号： F01D25/12 , F01D5/18
CPC分类号： F01D5/288 , F01D5/147 , F05D2230/80 , F05D2230/90 , F05D2260/202 , F05D2260/36
摘要： Exemplary embodiments include a multi-layer, modular and replaceable heat shield for gas turbines. The heat shield apparatus can include a base layer adjacent the airfoil and a thermal layer coupled to the base layer, wherein the base layer and the thermal layer match a contour of the airfoil.
摘要翻译：示例性实施例包括用于燃气轮机的多层，模块化和可更换的热屏蔽。隔热装置可以包括邻近翼型的基层和耦合到基层的热层，其中基层和热层匹配翼型的轮廓。

4. 发明授权

US07811054B2 Shroud configuration having sloped seal 失效
标题翻译：护罩配置具有倾斜密封
公开(公告)号：US07811054B2
公开(公告)日：2010-10-12
申请号：US11806140
申请日：2007-05-30
申请人： John Alan Eastman , Gary Michael Itzel , Charles Malinowski , Victor Morgan , David Richard Johns , Bryan Lewis
发明人： John Alan Eastman , Gary Michael Itzel , Charles Malinowski , Victor Morgan , David Richard Johns , Bryan Lewis
IPC分类号： F01D25/24
CPC分类号： F01D11/08 , F05D2240/11 , F05D2250/192 , F05D2250/70
摘要： A stator shroud segment is provided that includes an outer shroud having a leading edge groove and a trailing edge groove; and a plurality of inner shrouds each having a leading edge hook and a trailing edge hook, the leading and trailing hooks of each of the inner shrouds being respectively engaged with the leading and trailing edge grooves of the outer shroud so as to axially and radially lock the inner shrouds to the outer shrouds. At least one of the trailing edge hook of the inner shroud and the trailing edge groove of the outer shroud includes a sloped surface disposed at an angle to an axial direction of the rotor and to a radial direction of the rotor and facing the other of the inner and outer shrouds whereby a radial inward force on the inner shroud is transformed into a force in axial and radial directions to force the inner shroud to tightly seal a radial gap between the inner and outer shrouds.
摘要翻译：提供了一种定子护罩段，其包括具有前缘槽和后缘槽的外护罩; 以及多个内护罩，每个内护罩具有前缘钩和后缘钩，每个内护罩的前钩和尾钩分别与外护罩的前缘和后缘槽啮合，从而轴向和径向锁定内护罩到外护罩。内护罩的后缘钩和外护罩的后缘槽中的至少一个包括倾斜表面，该倾斜表面设置成与转子的轴向方向成一定角度并且与转子的径向方向相对，内部和外部护罩，由此内部护罩上的径向向内的力在轴向和径向方向上被转换成力，以迫使内部护罩紧密地密封内部和外部护罩之间的径向间隙。

5. 发明申请

US20130280040A1 COOLING ASSEMBLY FOR A GAS TURBINE SYSTEM 有权
标题翻译：用于气体涡轮机系统的冷却总成
公开(公告)号：US20130280040A1
公开(公告)日：2013-10-24
申请号：US13451053
申请日：2012-04-19
申请人： David Richard Johns , Kevin Richard Kirtley
发明人： David Richard Johns , Kevin Richard Kirtley
IPC分类号： F01D9/02
CPC分类号： F01D5/188 , F01D5/18 , F01D5/181 , F01D5/186 , F05D2240/81 , F05D2250/185 , F05D2260/201
摘要： A cooling assembly for a gas turbine system includes a turbine nozzle having at least one channel comprising a channel inlet configured to receive a cooling flow from a cooling source, wherein the at least one channel directs the cooling flow through the turbine nozzle in a radial direction at a first pressure to a channel outlet. Also included is an exit cavity for fluidly connecting the channel outlet to a region of a turbine component, wherein the region of the turbine component is at a second pressure, wherein the first pressure is greater than the second pressure.
摘要翻译：一种用于燃气涡轮机系统的冷却组件，包括具有至少一个通道的涡轮喷嘴，所述至少一个通道包括被配置为接收来自冷却源的冷却流的通道入口，其中所述至少一个通道引导所述冷却流在所述涡轮喷嘴的径向方向在第一压力下通向通道出口。还包括用于将通道出口流体连接到涡轮机部件的区域的出口腔，其中涡轮机部件的区域处于第二压力，其中第一压力大于第二压力。

6. 发明申请

US20120324898A1 COMBUSTOR ASSEMBLY FOR USE IN A TURBINE ENGINE AND METHODS OF ASSEMBLING SAME 审中-公开
标题翻译：用于涡轮发动机的燃烧器组件及其装配方法
公开(公告)号：US20120324898A1
公开(公告)日：2012-12-27
申请号：US13164948
申请日：2011-06-21
申请人： Kevin Weston McMahan , Ronald James Chila , David Richard Johns
发明人： Kevin Weston McMahan , Ronald James Chila , David Richard Johns
IPC分类号： F23R3/02 , B21D53/00 , F02C3/00
CPC分类号： F23R3/002 , F01D9/023 , F23R3/425 , F23R2900/03044 , Y10T29/49348
摘要： A combustor assembly for use with a turbine engine that includes a rotor assembly. The combustor assembly includes a casing that includes a plenum and a combustor liner that is spaced a distance from the plenum and that defines a combustion chamber therein. A transition nozzle extends between the combustor liner and the rotor assembly for channeling combustion gases from the combustion chamber to the rotor assembly. The transition nozzle includes a transition portion and a nozzle portion integrally formed with the transition portion. An annular flowsleeve is coupled radially outward from the transition nozzle such that an annular flow path is defined between the flowsleeve and the transition nozzle. The flowsleeve includes a plurality of openings extending through an outer surface of the flowsleeve for providing flow communication between the plenum and the annular flow path to facilitate impingement cooling of the flowsleeve.
摘要翻译：一种与包括转子组件的涡轮发动机一起使用的燃烧器组件。燃烧器组件包括壳体，其包括气室和与集气室隔开一定距离且在其中限定燃烧室的燃烧器衬套。过渡喷嘴在燃烧器衬套和转子组件之间延伸，用于将燃烧气体从燃烧室引导至转子组件。过渡喷嘴包括过渡部分和与过渡部分一体形成的喷嘴部分。环形流动体从过渡喷嘴径向向外耦合，使得在流动流体和过渡喷嘴之间限定环形流动路径。流动通道包括延伸穿过流动的外表面的多个开口，用于提供气室与环形流路之间的流动连通，以便于流动的冲击冷却。

7. 发明申请

US20110259015A1 Tangential Combustor 审中-公开
标题翻译：切向燃烧器
公开(公告)号：US20110259015A1
公开(公告)日：2011-10-27
申请号：US12768385
申请日：2010-04-27
申请人： David Richard Johns , Craig Steven Humanchuk
发明人： David Richard Johns , Craig Steven Humanchuk
IPC分类号： F23R3/46
CPC分类号： F23R3/425 , F23R3/58
摘要： A combustion section for a gas turbine includes a casing defining a chamber, a plurality of combustor cans disposed in the casing and oriented in an annular pattern, and a plurality of transition pieces each coupled with one of the combustor cans. The transition pieces direct products of combustion from the combustor cans into contact with rotating buckets of the gas turbine. Each of the transition pieces is angled in two planes to effect turning of the products of combustion and to shorten the gas turbine.
摘要翻译：一种用于燃气轮机的燃烧部分包括限定腔室的壳体，设置在壳体中并定向成环形图案的多个燃烧器罐和多个与所述燃烧器罐中的一个联接的过渡件。过渡件将来自燃烧器罐的燃烧产物直接与燃气轮机的旋转桶接触。每个过渡件在两个平面中成角度，以实现燃烧产物的转动并缩短燃气轮机。

8. 发明申请

US20100284800A1 TURBINE NOZZLE WITH SIDEWALL COOLING PLENUM 审中-公开
标题翻译：涡轮喷嘴与风冷冷却气球
公开(公告)号：US20100284800A1
公开(公告)日：2010-11-11
申请号：US12463606
申请日：2009-05-11
申请人： EVAN ANDREW SEWALL , DAVID RICHARD JOHNS , GARY MICHAEL ITZEL
发明人： EVAN ANDREW SEWALL , DAVID RICHARD JOHNS , GARY MICHAEL ITZEL
IPC分类号： F01D25/12
CPC分类号： F01D9/041 , F01D25/12 , F05D2240/81 , F05D2260/20 , F05D2260/201
摘要： A turbine nozzle segment includes an outer band portion, an inner band portion, and at least one nozzle vane extending between the band portions. A cooling plenum is defined in a mating side face of at least one of the band portions and extends transversely at least partially through the respective band portion. First and second cooling passages extend from the cooling plenum to respective first and second cooling chambers.
摘要翻译：涡轮喷嘴段包括外带部分，内带部分和在带部分之间延伸的至少一个喷嘴叶片。在至少一个带部分的配合侧面中限定冷却气室，并且横向至少部分延伸通过相应的带部分。第一和第二冷却通道从冷却气室延伸到相应的第一和第二冷却室。

9. 发明申请

US20100072710A1 Gas Turbine Seal 审中-公开
标题翻译：燃气轮机密封
公开(公告)号：US20100072710A1
公开(公告)日：2010-03-25
申请号：US12234989
申请日：2008-09-22
申请人： Victor John Morgan , Kevin Thomas McGovern , David Richard Johns
发明人： Victor John Morgan , Kevin Thomas McGovern , David Richard Johns
IPC分类号： F16J15/16
CPC分类号： F16J15/0887 , F01D9/042 , F01D11/005 , F05D2220/3212
摘要： A seal is provided for sealing two adjacent components of a gas turbine engine. The seal has first and second sealing surfaces that operate to seal the adjacent components to create an effective seal therebetween. Additionally, the seal has a first end and a second end, with the second end having a necked down portion, which is configured to internally engage the first end in a sliding, overlapping manner.
摘要翻译：提供用于密封燃气涡轮发动机的两个相邻部件的密封件。密封件具有第一和第二密封表面，其操作以密封相邻部件以在其间产生有效的密封。此外，密封件具有第一端和第二端，其中第二端具有颈缩部分，其被构造成以滑动重叠的方式内部接合第一端。

10. 发明授权

US08678644B2 Hot gas path measurement 失效
标题翻译：热气路测量
公开(公告)号：US08678644B2
公开(公告)日：2014-03-25
申请号：US13210849
申请日：2011-08-16
申请人： David Richard Johns , Ariel Harter Lomas , James Stewart Phillips
发明人： David Richard Johns , Ariel Harter Lomas , James Stewart Phillips
IPC分类号： G01K1/10 , G01K1/14
CPC分类号： G01K13/02 , G01K1/14 , G01K2013/024
摘要： A hot gas path measurement apparatus is provided and includes a substrate having a coating applied on a surface thereof such that the coating is interposed between the substrate and a hot gas path; and a measurement device fixed in a recess formed in the substrate, the measurement device including a sensor, and a holder configured to position the sensor in an alignment condition with a plane of a surface of the coating or at least partially within a span of the hot gas path.
摘要翻译：提供了一种热气体路径测量装置，并且包括在其表面上具有涂层的基板，使得涂层介于基板和热气路径之间; 以及测量装置，其固定在形成在所述基板中的凹部中，所述测量装置包括传感器，以及保持器，所述保持器构造成将所述传感器定位在与所述涂层的表面的平面对准的状态下或至少部分地位于所述热气路。

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