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1. 发明申请

US20120102951A1 APPARATUS FOR REDUCING EMISSIONS AND METHOD OF ASSEMBLY 审中-公开
标题翻译：减少排放的装置和装配方法
公开(公告)号：US20120102951A1
公开(公告)日：2012-05-03
申请号：US12915653
申请日：2010-10-29
申请人： Gilbert Otto Kraemer , Paul Thomas Marks , Robert Frank Hoskin
发明人： Gilbert Otto Kraemer , Paul Thomas Marks , Robert Frank Hoskin
IPC分类号： F01K13/00 , F01K27/00
CPC分类号： F01K23/10 , Y02E20/16
摘要： A heat recovery steam generator (HRSG) is coupled to a gas turbine engine that is configured to combust a fuel in air to produce shaft power and a flow of exhaust gases including oxides of nitrogen (NOx). The HRSG includes at least one duct burner for heating the exhaust gases and at least one NOx reduction element coupled downstream from the at least one duct burner and configured to facilitate reducing an amount of NOx in the exhaust gases that are channeled into the at least one NOx reduction element.
摘要翻译：热回收蒸汽发生器（HRSG）耦合到燃气涡轮发动机，其被配置为在空气中燃烧燃料以产生轴功率和包括氮氧化物（NOx）的废气流。 HRSG包括至少一个用于加热废气的管道燃烧器和至少一个NOx还原元件，其连接在至少一个管道燃烧器的下游，并被配置为有助于减少排放到所述至少一个管道燃烧器中的废气中的NOx的量 NOx还原元件

2. 发明授权

US07614847B2 Pattern for the surface of a turbine shroud 有权
标题翻译：涡轮机护罩表面的图案
公开(公告)号：US07614847B2
公开(公告)日：2009-11-10
申请号：US10996878
申请日：2004-11-24
申请人： Warren Arthur Nelson , Brian Peter Arness , Paul Thomas Marks , Raymond Edward Chupp , Tara Easter Mcgovern
发明人： Warren Arthur Nelson , Brian Peter Arness , Paul Thomas Marks , Raymond Edward Chupp , Tara Easter Mcgovern
IPC分类号： F01D11/12
CPC分类号： F01D11/12 , F01D11/122
摘要： A pattern for improving aerodynamic performance of a turbine includes a material disposed in a pattern at a base surface of a turbine shroud such that the material is capable of abradable contact with a tip portion of a turbine bucket. The pattern includes a first plurality of ridges disposed at the base surface such that a first portion of the first plurality of ridges corresponding to a back portion of the turbine bucket is oriented at a first angle with respect to an axis of rotation of the turbine bucket. Each ridge of the first plurality of ridges has a first sidewall and a second sidewall having a first end and a second end. The first ends of the first and second sidewalls extend from the base surface. The first and second sidewalls slope toward each other with substantially equal but opposite slopes until meeting at the second ends of respective first and second sidewalls defining a centerline and a top portion of the ridge.
摘要翻译：用于改善涡轮机的空气动力学性能的模式包括在涡轮机护罩的基面处以图案设置的材料，使得该材料能够与涡轮机桶的尖端部分磨损接触。该图案包括设置在基部表面处的第一多个脊，使得对应于涡轮机桶的后部的第一多个脊的第一部分相对于涡轮叶片的旋转轴线以第一角度定向。第一多个脊中的每个脊具有第一侧壁和具有第一端和第二端的第二侧壁。第一和第二侧壁的第一端从基面延伸。第一和第二侧壁彼此相对倾斜，具有基本上相等但相反的斜面，直到在相应的第一和第二侧壁的第二端处共同限定脊的中心线和顶部。

3. 发明授权

US06226974B1 Method of operation of industrial gas turbine for optimal performance 有权
标题翻译：工业燃气轮机的最佳运行方式
公开(公告)号：US06226974B1
公开(公告)日：2001-05-08
申请号：US09339956
申请日：1999-06-25
申请人： Philip Lynn Andrew , Paul Thomas Marks , Daniel Robert Dwyer , John David Stampfli , Joseph Anthony Cotroneo , Harold Edward Miller , Ronald Richard Wesorick
发明人： Philip Lynn Andrew , Paul Thomas Marks , Daniel Robert Dwyer , John David Stampfli , Joseph Anthony Cotroneo , Harold Edward Miller , Ronald Richard Wesorick
IPC分类号： F02C1310
CPC分类号： F02C9/28 , F04D27/02 , F05D2270/05 , Y02E20/16
摘要： A gas turbine operational strategy is provided for the optimization of ISO-Day rated performance. The invention is realized by setting the nominal operating line equal to or slightly below the operating limit line, so that ISO full load performance is maximized. Thus, the first stage turbine nozzle throat area is sized such that, without inlet bleed heat addition, and at Base-Load pressure ratio and firing temperature, the compressor operates within its operational limits on a ISO day. As ambient conditions change, levels of inlet bleed heat and firing temperature are controlled and the inlet guide vane angle is set whereby the nominal operating line is equal to or slightly below the operating limit line.
摘要翻译：提供燃气轮机操作策略，以优化ISO-Day的性能。本发明通过将标称操作线设置为等于或稍低于操作限制线来实现，使得ISO满载性能最大化。因此，第一级涡轮喷嘴喉部区域的尺寸使得在没有入口放热加入的情况下，并且在基本负载压力比和烧制温度下，压缩机在ISO日的运行限度内运行。随着环境条件的变化，入口排放热量和燃烧温度的水平被控制，并且入口导向叶片角度被设定，由此标称操作线等于或略低于操作极限线。

4. 发明授权

US06168377A Method and apparatus for eliminating thermal bowing of steam turbine rotors 失效
标题翻译：用于消除汽轮机转子热弯的方法和装置
公开(公告)号：US06168377A
公开(公告)日：2001-01-02
申请号：US09238257
申请日：1999-01-27
申请人： Christopher Edward Wolfe , Frederick George Baily , Lawrence Edward Rentz , Alexander Morson , Norman Arnold Turnquist , Paul Thomas Marks , Roger Jordan Carr
发明人： Christopher Edward Wolfe , Frederick George Baily , Lawrence Edward Rentz , Alexander Morson , Norman Arnold Turnquist , Paul Thomas Marks , Roger Jordan Carr
IPC分类号： F01D1100
CPC分类号： F01D11/001 , F16J15/3288
摘要： Brush seals are employed on steam turbine rotors without the risk of causing thermal rotor bowing and without compromising the sealing performance. In one form, a groove in the rotor has an insert in frictional contact with the brush seal. The non-uniform distribution of heat due to frictional contact between the brush seal and proud portions of the rotor is dissipated within the insert such that adjoining rotor portions are substantially uniformly heated without causing thermal bow. In a further form, a groove or grooves are provided in the rotor surface adjacent to the brush seal and maintain non-uniform heat distribution locally in the rotor without causing thermal bow of the rotor. In another form, a land projects radially outwardly of the rotor surface in contact with the brush seal. The non-uniform distribution of heat due to frictional contact between proud portions of the land and the brush seal dissipates into a uniform distribution of heat in the rotor proper to avoid thermal bowing. In a final form, the brush seal has frictional contact with bucket dovetail or wheel protrusions spaced radially outwardly of the rotor such that non-uniform distribution dissipates into a uniform distribution within the rotor.
摘要翻译：汽轮机转子上使用刷子密封件，而不会导致热转子弯曲并且不影响密封性能。在一种形式中，转子中的槽具有与刷密封件摩擦接触的插入件。由于刷子密封件和转子的骄人部分之间的摩擦接触引起的热量的不均匀分布在插入件内消散，使得相邻的转子部分基本均匀地加热而不引起热弓。在另一种形式中，在转子表面中设置有与刷子密封件相邻的凹槽或槽，并且在转子中局部地保持不均匀的热分布，而不会导致转子的热弓。在另一种形式中，一个脊面与转子表面径向向外突出地与刷子密封接触。由于陆地骄傲部分和刷子密封件之间的摩擦接触导致的热量的不均匀分布在转子中散发成均匀的热分布，以避免热弯曲。在最终形式中，刷子密封件与铲斗的燕尾榫摩擦接触或轮毂径向向外偏离转子，使得不均匀的分布在转子内消散成均匀的分布。

5. 发明授权

US08007246B2 Methods and apparatus for coating gas turbine engines 失效
标题翻译：喷气式发动机的方法和装置
公开(公告)号：US08007246B2
公开(公告)日：2011-08-30
申请号：US11654182
申请日：2007-01-17
申请人： Raymond Grant Rowe , Tara Easter McGovern , Jane Ann Murphy , Andrew Jay Skoog , William R. Stowell , Paul Thomas Marks , Lisa DeBellis , James H. Clare
发明人： Raymond Grant Rowe , Tara Easter McGovern , Jane Ann Murphy , Andrew Jay Skoog , William R. Stowell , Paul Thomas Marks , Lisa DeBellis , James H. Clare
IPC分类号： F01D5/18
CPC分类号： C23C4/02 , F01D5/288 , F05D2230/90 , Y02T50/673
摘要： A method of fabricating a component for a gas turbine engine is provided. The method includes applying a bond coat to at least a portion of the component, applying a dense vertically cracked (DVC) thermal barrier coating to at least a portion of the bond coat using a spray mechanism positioned a first distance from the component, and overlying at least a portion of the DVC thermal barrier coating with a soft coat thermal barrier coating using a spray mechanism that is positioned a second distance away from the component, wherein the second distance is greater than the first distance to facilitate adherence of the soft coating thermal barrier coating to the DVC thermal barrier coating.
摘要翻译：提供一种制造用于燃气轮机的部件的方法。该方法包括将粘合涂层施加到部件的至少一部分上，使用位于距部件第一距离的喷涂机构将至少一部分粘合涂层施加致密的垂直裂纹（DVC）热障涂层，并且覆盖所述DVC热障涂层的至少一部分具有使用喷涂机构的软涂层热障涂层，所述喷涂机构位于远离所述部件的第二距离处，其中所述第二距离大于所述第一距离以促进所述软涂层热粘附阻隔涂层到DVC隔热涂层。

6. 发明授权

US6131910A Brush seals and combined labyrinth and brush seals for rotary machines 失效
标题翻译：刷子密封件和旋转机器的组合式迷宫式和刷式密封件
公开(公告)号：US6131910A
公开(公告)日：2000-10-17
申请号：US855013
申请日：1997-05-13
申请人： Bharat S. Bagepalli , R. Paul Chiu , Robert Harold Cromer , Gregory Allan Crum , Osman Saim Dinc , Anthony Holmes Furman , Paul Thomas Marks , Rudolf Matthias Markytan , David Robert Skinner , Norman Arnold Turnquist , Christopher Edward Wolfe
发明人： Bharat S. Bagepalli , R. Paul Chiu , Robert Harold Cromer , Gregory Allan Crum , Osman Saim Dinc , Anthony Holmes Furman , Paul Thomas Marks , Rudolf Matthias Markytan , David Robert Skinner , Norman Arnold Turnquist , Christopher Edward Wolfe
IPC分类号： F01D11/00 , F01D11/02 , F01D11/08 , F01D11/12 , F16J15/32 , F16J15/44 , F16J15/447
CPC分类号： F16J15/442 , F01D11/001 , F01D11/02 , F01D11/08 , F01D11/12 , F01D11/127 , F01D5/225 , F01D5/3046 , F16J15/3288 , F16J15/4472 , F05D2240/56 , F05D2250/182 , F05D2300/6012
摘要： Brush seals are retrofitted into existing turbine labyrinth seal rings to create a fail-safe seal design at locations wherever labyrinth seals are currently used, including interstage shaft seals, rotor end seals, bucket (or blade) tip seals and spill strips. Brush seals, per se, when used in place of labyrinth seals, can result in considerable span reductions of steam turbines, or machines with more turbine stages for a given span. Application to end packings results in the potential elimination of gland sealing/exhauster systems. Brush seal life can be improved by retrofitting brush segments to labyrinth seal segments that are either spring-backed, or use pressure loads to obtain design clearances only after steady state operating conditions are achieved. The brush seals are provided with backing plates shaped like labyrinth teeth, resulting in a fail-safe design. Also, the use of existing labyrinth teeth as bristle backing plates results in a brush seal with diminished susceptibility to hysteresis when compared to conventional brush seal designs. Low friction coatings can also be used to reduce brush seal hysteresis. Incorporation of brush seals in labyrinth seal rings that are either spring-backed or held in place by pressure forces results in extremely low brush seal wear.
摘要翻译：电刷密封件改装成现有的涡轮迷宫式密封环，以在目前使用迷宫式密封件的位置创建故障安全密封设计，包括级间轴密封件，转子端部密封件，铲斗（或刀片）末端密封件和溢出条。刷子密封件本身在用于代替迷宫式密封件时，可以导致蒸汽轮机或具有更多涡轮级的机器在给定跨度上的相当大的跨度减少。对端部密封的应用导致密封/排气系统的潜在消除。刷子密封寿命可以通过将刷段改装为弹簧密封段，或者使用压力负载仅在达到稳态工作条件之后才能获得设计间隙。刷子密封件设置有类似迷宫齿的背板，从而形成故障安全设计。此外，与传统的刷密封设计相比，使用现有的迷宫齿作为刷毛背板导致刷密封，对滞后的敏感性降低。低摩擦涂层也可用于减少刷子密封滞后。将刷子密封件装入迷宫式密封环中，弹簧支撑或通过压力力保持在适当位置导致极低的刷密封磨损。

7. 发明授权

US07600968B2 Pattern for the surface of a turbine shroud 有权
标题翻译：涡轮机护罩表面的图案
公开(公告)号：US07600968B2
公开(公告)日：2009-10-13
申请号：US10907972
申请日：2005-04-22
申请人： Warren Arthur Nelson , Brian Peter Arness , Paul Thomas Marks , Raymond Edward Chupp , Tara Easter McGovern
发明人： Warren Arthur Nelson , Brian Peter Arness , Paul Thomas Marks , Raymond Edward Chupp , Tara Easter McGovern
IPC分类号： F01D11/12
CPC分类号： F01D11/12 , F01D11/122
摘要： An article of manufacture pattern for improving aerodynamic performance of a turbine including an abradable material capable of abradable contact. The abradable material is disposed in a pattern. The pattern includes a first plurality of ridges disposed at a base surface of the turbine. Each ridge of the first plurality of ridges has a first sidewall and a second sidewall having a first end and a second end. The first ends of the first and second sidewalls extend from the base surface. The first and second sidewalls slope toward each other with substantially equal but opposite slopes until meeting at the second ends of respective first and second sidewalls defining a centerline and a top portion of the ridge.
摘要翻译：一种用于改善涡轮机的空气动力性能的制造模式的制品，其包括能够耐磨的接触的耐磨材料。耐磨材料以图案设置。该图案包括设置在涡轮机的基面处的第一多个脊。第一多个脊中的每个脊具有第一侧壁和具有第一端和第二端的第二侧壁。第一和第二侧壁的第一端从基面延伸。第一和第二侧壁彼此相对倾斜，具有基本上相等但相反的斜面，直到在相应的第一和第二侧壁的第二端处共同限定脊的中心线和顶部。

8. 发明申请

US20110044821A1 Methods and apparatus for coating gas turbine engines 失效
公开(公告)号：US20110044821A1
公开(公告)日：2011-02-24
申请号：US11654182
申请日：2007-01-17
申请人： Raymond Grant Rowe , Tara Easter McGovern , Jane Ann Murphy , Andrew Jay Skoog , William R. Stowell , Paul Thomas Marks , Lisa DeBellis , James H. Clare
发明人： Raymond Grant Rowe , Tara Easter McGovern , Jane Ann Murphy , Andrew Jay Skoog , William R. Stowell , Paul Thomas Marks , Lisa DeBellis , James H. Clare
IPC分类号： F03B3/12 , B05D1/36
CPC分类号： C23C4/02 , F01D5/288 , F05D2230/90 , Y02T50/673
摘要： A method of fabricating a component for a gas turbine engine is provided. The method includes applying a bond coat to at least a portion of the component, applying a dense vertically cracked (DVC) thermal barrier coating to at least a portion of the bond coat using a spray mechanism positioned a first distance from the component, and overlying at least a portion of the DVC thermal barrier coating with a soft coat thermal barrier coating using a spray mechanism that is positioned a second distance away from the component, wherein the second distance is greater than the first distance to facilitate adherence of the soft coating thermal barrier coating to the DVC thermal barrier coating.

9. 发明授权

US06550253B2 Apparatus and methods for controlling flow in turbomachinery 有权
标题翻译：用于控制涡轮机械流量的装置和方法
公开(公告)号：US06550253B2
公开(公告)日：2003-04-22
申请号：US09682511
申请日：2001-09-12
申请人： Jason Paul Mortzheim , Ming Zhou , Paul Thomas Marks
发明人： Jason Paul Mortzheim , Ming Zhou , Paul Thomas Marks
IPC分类号： F02C608
CPC分类号： F02C7/12 , F01D17/105 , F01D25/12 , F02C7/18 , F05D2260/601 , F05D2270/301
摘要： In turbomachinery, first and second flowpaths coupled to stages of the compressor flow cooling medium at different temperatures and pressures to components of the turbine. An ejector is provided in the first flowpath for suctioning flow from the second flowpath and combining the two flows for delivery to a component of the turbine at a temperature and pressure intermediate the temperature and pressure of the first and second flows. A flow sensor, flow controller and throttling valve are interposed in the motive flowpath, the exit flowpath or the suction flowpath relative to the ejector for controlling the flow through the ejector.
摘要翻译：在涡轮机械中，第一和第二流动路径在不同的温度和压力下耦合到压缩机流动冷却介质的阶段，以使涡轮的部件。喷射器设置在第一流动路径中，用于从第二流动路径抽吸流动并将两个流合并在涡轮机的部件中，温度和压力介于第一和第二流量的温度和压力之间。流量传感器，流量控制器和节流阀相对于喷射器介于动力流动路径，出口流动路径或抽吸流动路径中，用于控制通过喷射器的流动。

10. 发明授权

US06412270B1 Apparatus and methods for flowing a cooling or purge medium in a turbine downstream of a turbine seal 失效
标题翻译：在涡轮密封件下游的涡轮中流动冷却或吹扫介质的装置和方法
公开(公告)号：US06412270B1
公开(公告)日：2002-07-02
申请号：US09682510
申请日：2001-09-12
申请人： Jason Paul Mortzheim , Ming Zhou , Paul Thomas Marks
发明人： Jason Paul Mortzheim , Ming Zhou , Paul Thomas Marks
IPC分类号： F02C500
CPC分类号： F01D25/12 , F01D11/04 , F01D25/125 , F05D2260/601
摘要： Leakage flows through seals are used to cool components of a turbine downstream of the seals. At certain seal locations, the leakage flows are restricted to the extent that cooling of downstream components cannot be effected by the leakage flows. The cooling air leakage flow is augmented by extracting bleed air from different stages at different temperatures from a compressor and combining the extracted flows in an ejector to provide a flow having a temperature intermediate the temperatures of the extracted flow streams for augmenting the leakage flow to cool the component. The ejector thus uses high extraction air to entrain lower temperature extraction air to lower the ejector exit air temperature, reducing the magnitude of air required to cool the downstream component and enhancing the effectiveness of the advanced seal.
摘要翻译：渗漏通过密封件的流体被用来冷却密封件下游涡轮的部件。在某些密封位置，泄漏流量受限于下游部件的冷却不会受到泄漏流的影响。通过从与压缩机不同温度的不同阶段提取出气，并将提取的流合并在喷射器中以提供具有在提取的流动流的温度之间的温度的流动以增加泄漏流以冷却来增加冷却空气泄漏流量组件。因此，喷射器使用高提取空气来夹带较低温度的提取空气以降低喷射器出口空气温度，减少冷却下游部件所需的空气的大小并提高先进密封的有效性。

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