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1. 发明授权

US11933231B2 Methods and systems for tuning a gas turbine engine 有权
公开(公告)号：US11933231B2
公开(公告)日：2024-03-19
申请号：US17665935
申请日：2022-02-07
申请人： Power Systems Mfg., LLC
发明人： Wenping Wang , Matthew Yaquinto , Nicolas Demougeot , Alex Steinbrenner , Cory Dodson , Jaime Serrano
IPC分类号： F02C9/28
CPC分类号： F02C9/28 , F05D2270/07 , F05D2270/20
摘要： A method for tuning a gas turbine engine includes performing a sensitivity step process on a tuning parameter. An operating parameter is monitored. The gas turbine is operating in a first operational state and the operating parameter has an initial condition. The tuning parameter is selected for adjustment. The tuning parameter is adjusted by a predefined amount. The adjustment includes applying an incremental bias adjustment to a fuel flow fraction schedule. The gas turbine engine transitions to a second operational state, wherein the operating parameter has an adjusted condition. The adjusted condition and the initial condition of the operating parameter are applied to a cost function. It is then determined that the cost function results in a cost function value indicative of a decreased cost. The incremental bias adjustment and the cost function value is written to a bias look-up table and are associated with the selected tuning parameter.

2. 发明公开

US20230408097A1 MULTITUBE PILOT INJECTOR HAVING A FLAME ANCHOR FOR A GAS TUBINE ENGINE 审中-公开
公开(公告)号：US20230408097A1
公开(公告)日：2023-12-21
申请号：US17980263
申请日：2022-11-03
申请人： Power Systems Mfg., LLC
发明人： Bryan KALB , Matthew YAQUINTO , Gene CHONG , David PARADES , James BRACKETT , Gregory VOGEL , Hany RIZKALLA , Bernard Tam Yen SAM , Ramesh KESHAVA-BHATTU , Fred HERNANDEZ , Joshua R. MCNALLY
IPC分类号： F23R3/34 , F23R3/28
CPC分类号： F23R3/343 , F23R3/286
摘要： An injector for a combustor of a gas turbine engine is provided with a plurality of air/fuel mixing tubes divided into radially outer and radially inner subsets of air/fuel mixing tubes with a first fuel manifold in fluid communication with the radially outer subset of air/fuel mixing tubes and a second fuel manifold in fluid communication with the radially inner subset of air/fuel mixing tubes. A blocker is provided at an outlet portion of each of the air/fuel mixing tubes of the radially outer subset of air/fuel mixing tubes and/or the radially inner subset of air/fuel mixing tubes to form a flame anchoring surface.

3. 发明申请

US20230135396A1 MULTITUBE PILOT INJECTOR HAVING A SPLIT AIRFLOW FOR A GAS TURBINE ENGINE 有权
公开(公告)号：US20230135396A1
公开(公告)日：2023-05-04
申请号：US17980273
申请日：2022-11-03
申请人： Power Systems Mfg., LLC
发明人： Bryan KALB , Matthew YAQUINTO , Gene CHONG , David PARADES , James BRACKETT , Gregory VOGEL , Hany RIZKALLA , Bernard Tam Yen SAM , Ramesh KESHAVA-BHATTU , Fred HERNANDEZ , Joshua R. MCNALLY
IPC分类号： F23R3/28 , F23R3/04
摘要： An injector for a combustor of a gas turbine engine is provided with a plurality of air/fuel mixing tubes divided into radially outer and radially inner subsets of air/fuel mixing tubes with a first fuel manifold in fluid communication with the radially outer subset of air/fuel mixing tubes and a second fuel manifold in fluid communication with the radially inner subset of air/fuel mixing tubes. Each of the air/fuel mixing tubes of the radially outer subset of air/fuel mixing tubes includes a substantially quadrilateral cross-sectional profile, and each of the air/fuel mixing tubes of the radially inner subset of air/fuel mixing tubes includes a substantially circular cross-sectional profile.

4. 发明授权

US11015459B2 Additive manufacturing optimized first stage vane 有权
公开(公告)号：US11015459B2
公开(公告)日：2021-05-25
申请号：US16598550
申请日：2019-10-10
申请人： Power Systems Mfg., LLC
发明人： Gregory Edwin Vogel , Joshua Robert McNally , Vladimir Kitaigorod
IPC分类号： F01D5/28 , F01D9/04
摘要： An airfoil and turbine vanes and vane assemblies incorporating the same. The airfoil has an uncoated profile substantially in accordance with Cartesian coordinate values of X, Y, and Z as set forth in Table 1, carried to four decimal places. The Z values refer to a percentage of the radial span of the airfoil measured radially from a radially outwardly facing surface of the inner platform. The turbine vane includes an inner platform, an outer platform, and an airfoil such as the one discussed above extending radially outward from the inner platform toward the outer platform. And the vane assembly includes an inner platform, an outer platform, and two or more first stage vanes extending from the inner platform to the outer platform. Each of the two or more first stage vanes include an airfoil as discussed above.

5. 发明授权

US10739007B2 Flamesheet diffusion cartridge 有权
公开(公告)号：US10739007B2
公开(公告)日：2020-08-11
申请号：US15974870
申请日：2018-05-09
申请人： Power Systems Mfg., LLC
发明人： Alfredo Cires , Peter Stuttaford , Matthew Yaquinto , Hany Rizkalla , Khalid Oumejjoud , Fred Hernandez , Bryan Kalb , Nicolas Demougeot , Joshua R McNally , Ramesh Keshava Bhattu , Bernard Tam-Yen Sam
IPC分类号： F23R3/34 , F23R3/60
摘要： A diffusion cartridge assembly for a gas turbine engine, and methods of using the same. The diffusion cartridge assembly includes a tip plate with an array of fuel supply openings and a mounting hole radially inward of the array of fuel supply openings, an end cover, and an outer sleeve extending from the tip plate to the end cover and defining an open inner chamber. A fuel supply line is coupled to the end cover and extends within the open inner chamber toward the tip plate. A manifold is coupled to an end of the fuel supply line proximate to the tip plate, and includes an array of fuel injector tips. Each of the fuel injector tips extends through a respective one of the array of fuel supply openings in the tip plate. The manifold also includes a thermally free mounting pin extending into the mounting hole.

6. 发明授权

US08136359B2 Gas turbine fuel nozzle having improved thermal capability 有权
标题翻译：具有改善的热能的燃气轮机燃料喷嘴
公开(公告)号：US08136359B2
公开(公告)日：2012-03-20
申请号：US11953162
申请日：2007-12-10
申请人： Peter Stuttaford , Paul Economo , Khalid Oumejjoud , Max Dufflocq , Hany Rizkalla
发明人： Peter Stuttaford , Paul Economo , Khalid Oumejjoud , Max Dufflocq , Hany Rizkalla
IPC分类号： F02C1/00
CPC分类号： F23R3/286 , F23D2900/00008 , F23R2900/00001 , F23R2900/00005
摘要： Embodiments for minimizing relative thermal growth within a fuel nozzle of a gas turbine combustor are disclosed. Fuel nozzle configurations are provided in which a heating fluid is provided to one or more passages in a fuel nozzle from feed holes in the fuel nozzle base. The heating fluid passes through the fuel nozzle, thereby raising the operating temperature of portions of the fuel nozzle to reduce differences in thermal gradients within the fuel nozzle. Various fuel nozzle configurations and passageway geometries are also disclosed.
摘要翻译：公开了用于使燃气轮机燃烧器的燃料喷嘴内的相对热增长最小化的实施例。提供了一种燃料喷嘴结构，其中加热流体从燃料喷嘴基座中的进料孔设置在燃料喷嘴中的一个或多个通道中。加热流体通过燃料喷嘴，从而提高燃料喷嘴部分的工作温度，以减少燃料喷嘴内热梯度的差异。还公开了各种燃料喷嘴构造和通道几何形状。

7. 发明申请

US20090145983A1 GAS TURBINE FUEL NOZZLE HAVING IMPROVED THERMAL CAPABILITY 有权
标题翻译：具有改进的热能的气体涡轮机燃油喷嘴
公开(公告)号：US20090145983A1
公开(公告)日：2009-06-11
申请号：US11953162
申请日：2007-12-10
申请人： Peter Stuttaford , Paul Economo , Khalid Oumejjoud , Max Dufflocq , Hany Rizkalla
发明人： Peter Stuttaford , Paul Economo , Khalid Oumejjoud , Max Dufflocq , Hany Rizkalla
IPC分类号： F02M61/18
CPC分类号： F23R3/286 , F23D2900/00008 , F23R2900/00001 , F23R2900/00005
摘要： Embodiments for minimizing relative thermal growth within a fuel nozzle of a gas turbine combustor are disclosed. Fuel nozzle configurations are provided in which a heating fluid is provided to one or more passages in a fuel nozzle from feed holes in the fuel nozzle base. The heating fluid passes through the fuel nozzle, thereby raising the operating temperature of portions of the fuel nozzle to reduce differences in thermal gradients within the fuel nozzle. Various fuel nozzle configurations and passageway geometries are also disclosed.
摘要翻译：公开了用于使燃气轮机燃烧器的燃料喷嘴内的相对热增长最小化的实施例。提供了一种燃料喷嘴结构，其中加热流体从燃料喷嘴基座中的进料孔设置在燃料喷嘴中的一个或多个通道中。加热流体通过燃料喷嘴，从而提高燃料喷嘴部分的工作温度，以减少燃料喷嘴内热梯度的差异。还公开了各种燃料喷嘴构造和通道几何形状。

8. 发明申请

US20090145099A1 TRANSITION DUCT COOLING FEED TUBES 有权
标题翻译： TRANSITION DUCT冷却进料管
公开(公告)号：US20090145099A1
公开(公告)日：2009-06-11
申请号：US11951790
申请日：2007-12-06
申请人： Stephen Jennings , Peter Stuttaford , Stephen W. Jorgensen
发明人： Stephen Jennings , Peter Stuttaford , Stephen W. Jorgensen
IPC分类号： F01D25/12 , F02C3/00 , F02C7/12
CPC分类号： F01D25/12 , F01D9/023 , F05D2260/20 , F05D2260/201
摘要： Embodiments for an apparatus and associated method for providing a cooling fluid to a gas turbine transition duct in order to lower the effective operating temperatures of the transition duct are disclosed. The transition duct has an inner liner and an impingement sleeve positioned radially outward with a passageway formed therebetween. The impingement sleeve has a plurality of openings where a portion of the openings each have a feed tube extending through the opening and into the passageway. The feed tubes are oriented at an angle relative to the impingement sleeve, such that an inlet to the feed tube is directed generally towards an oncoming flow of cooling fluid. The feed tubes direct a portion of the cooling fluid toward the inner liner and into the passageway for cooling of the transition duct.
摘要翻译：公开了用于向燃气轮机过渡管道提供冷却流体以降低过渡管道的有效操作温度的装置和相关方法的实施例。过渡管道具有内衬和径向向外定位的冲击套筒，其间形成有通道。冲击套筒具有多个开口，其中开口的一部分各自具有延伸穿过开口并进入通道的进料管。进料管相对于冲击套筒定向成一定角度，使得进料管的入口通常朝着迎面而来的冷却流体流动。进料管将一部分冷却流体引向内衬并进入通道以冷却过渡管道。

9. 发明授权

US07513115B2 Flashback suppression system for a gas turbine combustor 有权
标题翻译：用于燃气轮机燃烧器的闪回抑制系统
公开(公告)号：US07513115B2
公开(公告)日：2009-04-07
申请号：US10908682
申请日：2005-05-23
申请人： Peter John Stuttaford
发明人： Peter John Stuttaford
IPC分类号： F02C1/00 , F02G3/00 , F23D14/82
CPC分类号： F23R3/286 , F23D14/82 , F23L7/00 , F23L2900/07002 , F23R3/24
摘要： A gas turbine combustor having improved flashback margin is disclosed. Multiple embodiments of the present invention are disclosed including combustors having a single premix chamber as well as multiple premix chambers. Flashback margin is increased for the combustor by incorporating a means for introducing an inert gas, such as nitrogen, into the premix chamber(s) at the region proximate the boundary layer to purge the boundary layer of combustible mixture, thereby ensuring that no combustion reaction occurs in the boundary layer.
摘要翻译：公开了一种具有改善的闪回余量的燃气轮机燃烧器。公开了本发明的多个实施例，包括具有单个预混合室的燃烧器以及多个预混室。通过在靠近边界层的区域引入惰性气体（例如氮气）到预混合室中来提高燃烧器的闪回余量，以清除可燃混合物的边界层，从而确保没有燃烧反应发生在边界层。

10. 发明授权

US07386980B2 Combustion liner with enhanced heat transfer 有权
标题翻译：具有增强热传递的燃烧衬管
公开(公告)号：US07386980B2
公开(公告)日：2008-06-17
申请号：US10906074
申请日：2005-02-02
申请人： Andrew Green , Peter Stuttaford , John Carella , Vamsi Duraibabu , Stephen Jennings
发明人： Andrew Green , Peter Stuttaford , John Carella , Vamsi Duraibabu , Stephen Jennings
IPC分类号： F02C1/00 , F02G3/00
CPC分类号： F23R3/42 , F23R3/005 , Y02T50/675
摘要： A combustion liner having enhanced heat transfer over at least a portion of the liner is disclosed. The combustion liner comprises, amongst other features, an outer surface wherein at least a region of the outer surface is textured in a substantially uniform pattern such that the surface area exposed to a passing cooling medium is increased, thereby increasing the heat transfer through the combustion liner. Multiple embodiments of textured patterns are also disclosed.
摘要翻译：公开了一种在衬套的至少一部分上具有增强的热传递的燃烧衬套。除了其它特征之外，燃烧衬套包括外表面，其中外表面的至少一个区域以基本均匀的图案纹理化，使得暴露于通过的冷却介质的表面积增加，从而增加通过燃烧的热传递衬垫。还公开了纹理图案的多个实施例。

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