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31. 发明申请

US20100018210A1 COMBUSTOR APPARATUS IN A GAS TURBINE ENGINE 有权
标题翻译：燃气涡轮发动机中的燃烧器装置
公开(公告)号：US20100018210A1
公开(公告)日：2010-01-28
申请号：US12233903
申请日：2008-09-19
申请人： Timothy A. Fox , David J. Wiebe , David M. Ritland , John Carl Glessner
发明人： Timothy A. Fox , David J. Wiebe , David M. Ritland , John Carl Glessner
IPC分类号： F02C7/22 , F23R3/28
CPC分类号： F23R3/16 , F23R3/283 , F23R3/346 , F23R2900/00005
摘要： A combustion apparatus in a gas turbine engine comprises a combustor shell for receiving air, a fuel injection system associated with the combustor shell, a first fuel supply structure, and a shield structure. The fuel supply structure is in fluid communication with a source of fuel for delivering fuel from the source of fuel to the fuel injection system and comprises a first fuel supply elements including a first section extending along a first path having a component in an axial direction and a second section extending from the first section along a second path having a component in a circumferential direction. The shield structure is associated with at least a portion of the second section of the first fuel supply element.
摘要翻译：燃气涡轮发动机中的燃烧装置包括用于接收空气的燃烧器壳体，与燃烧器壳体相关联的燃料喷射系统，第一燃料供应结构和屏蔽结构。燃料供应结构与燃料源流体连通，用于将燃料从燃料源输送到燃料喷射系统，并且包括第一燃料供应元件，其包括沿着沿轴向方向具有部件的第一路径延伸的第一部分，以及第二部分沿着沿圆周方向具有部件的第二路径从第一部分延伸。屏蔽结构与第一燃料供应元件的第二部分的至少一部分相关联。

32. 发明授权

US09316153B2 Purge and cooling air for an exhaust section of a gas turbine assembly 有权
标题翻译：用于燃气轮机组件的排气部分的吹扫和冷却空气
公开(公告)号：US09316153B2
公开(公告)日：2016-04-19
申请号：US13746486
申请日：2013-01-22
申请人： Harry Patat , Cheryl A. Schopf , Jerome H. Katy , Adam Wallace , David J. Wiebe
发明人： Harry Patat , Cheryl A. Schopf , Jerome H. Katy , Adam Wallace , David J. Wiebe
IPC分类号： F01D25/12 , F01D9/02 , F01D9/06 , F01D25/16 , F01D25/30 , F02C6/08 , F02C7/18
CPC分类号： F02C7/18 , F01D9/02 , F01D9/065 , F01D25/12 , F01D25/125 , F01D25/162 , F01D25/30 , F02C6/08 , F05D2240/15
摘要： A turbine exhaust casing having an outer casing, an inner casing, an annular exhaust gas path defined between outer and inner flow path walls, and a turbine exhaust casing cavity located radially outward and radially inward from the gas path. A plurality of structural struts support the inner casing to the outer casing, and a fairing surrounds each of the struts in an area extending between the outer and inner flow path walls. A first purge air path extends through at least one of the struts for conducting purge cooling air radially inward to the inner casing, and a second purge air path extends through the strut for further conducting the purge cooling air radially outward to provide a flow of purge air to a location of the exhaust casing cavity radially outward from the outer flow path wall.
摘要翻译：具有外壳，内壳，限定在外流路壁和内流路壁之间的环形排气通道的涡轮机排气外壳以及从气体路径径向向外和径向向内定位的涡轮排气壳体腔。多个结构支柱将内壳支撑到外壳，并且整流罩围绕在外流路壁和内流路壁之间延伸的区域中的每个支柱。第一吹扫空气路径延伸穿过支柱中的至少一个，用于将吹扫冷却空气径向向内引导到内部壳体，并且第二吹扫空气路径延伸穿过支柱，以进一步将吹扫冷却空气径向向外引导以提供吹扫流空气从外部流路壁向径向外侧排出到排气套管腔的位置。

33. 发明授权

US09115600B2 Insulated wall section 有权
标题翻译：绝缘墙段
公开(公告)号：US09115600B2
公开(公告)日：2015-08-25
申请号：US13221156
申请日：2011-08-30
申请人： David J. Wiebe
发明人： David J. Wiebe
IPC分类号： F01D25/26 , F01D25/24
CPC分类号： F01D25/26 , F01D25/24
摘要： A turbine section of a turbine engine includes rotatable structure, an outer casing disposed about the rotatable structure, and an inner casing disposed about the rotatable structure and suspended radially inwardly from the outer casing. Rotation of the rotatable structure during operation drives at least one of a compressor and a generator. The inner casing defines a hot gas flow path through which hot combustion gases pass during operation. The inner casing comprises a plurality of wall sections. Each wall section includes a panel having an inner portion and an outer portion opposed from and affixed to the inner portion. The inner portion at least partially defines the hot gas flow path and the inner portion is radially spaced from the outer portion such that a substantially fluid tight chamber is formed therebetween. The fluid tight chamber reduces thermal energy transfer from the inner portion to the outer portion.
摘要翻译：涡轮发动机的涡轮机部分包括旋转结构，围绕可旋转结构设置的外壳，以及围绕可旋转结构设置并从外壳径向向内悬挂的内壳。在操作期间可旋转结构的旋转驱动压缩机和发电机中的至少一个。内壳限定了在运行期间热燃气通过的热气流路径。内壳包括多个壁部。每个壁部分包括具有内部部分和与内部部分相对并固定到内部部分的外部部分的面板。所述内部部分至少部分地限定所述热气体流动路径，并且所述内部部分与所述外部部分径向间隔开，从而在其间形成基本上流体密封的腔室。流体密封室减少从内部到外部的热能传递。

34. 发明授权

US08920116B2 Wear prevention system for securing compressor airfoils within a turbine engine 有权
标题翻译：用于固定涡轮发动机内的压缩机翼型的防磨系统
公开(公告)号：US08920116B2
公开(公告)日：2014-12-30
申请号：US13267954
申请日：2011-10-07
申请人： David J. Wiebe , Adam C. Pela
发明人： David J. Wiebe , Adam C. Pela
IPC分类号： F01D5/16 , F01D25/06 , F01D25/24
CPC分类号： F01D25/246
摘要： A wear prevention system for securing compressor airfoils within a turbine engine while reducing wear of related components may include a compressor diaphragm spring positioned in an airfoil receiving channel between a radially outer surface of a diaphragm base and a radially inner surface of the airfoil receiving channel. The spring may bias the diaphragm base and airfoil attached thereto radially inward against upstream and downstream arms formed from upstream and downstream recesses extending axially from the airfoil receiving channel in the compressor case. The compressor diaphragm spring may dampen vibration and increase service life of the diaphragm base.
摘要翻译：一种用于在涡轮发动机内固定压缩机翼型件同时减少相关部件的磨损的磨损防止系统可以包括定位在隔膜基座的径向外表面和翼型件接收通道的径向内表面之间的翼型件接收通道中的压缩机隔膜弹簧。弹簧可以将隔膜底座和翼型件偏置到其上，径向向内抵靠从压缩机壳体中的翼型件接收通道轴向延伸的上游和下游凹部形成的上游和下游臂。压缩机膜片弹簧可以抑制振动并增加隔膜基座的使用寿命。

35. 发明申请

US20140245740A1 COMBUSTOR APPARATUS IN A GAS TURBINE ENGINE 有权
标题翻译：燃气涡轮发动机中的燃烧器装置
公开(公告)号：US20140245740A1
公开(公告)日：2014-09-04
申请号：US13783857
申请日：2013-03-04
申请人： David J. Wiebe , Stephen A. Ramier , Robert H. Bartley , Daniel W. Garan , Erick J. Deane , Mark L. Adamson , Yadollah Naghian
发明人： David J. Wiebe , Stephen A. Ramier , Robert H. Bartley , Daniel W. Garan , Erick J. Deane , Mark L. Adamson , Yadollah Naghian
IPC分类号： F23R3/28
CPC分类号： F23R3/28 , F02C7/22 , F02C7/222 , F05D2300/50211 , F05D2300/50212 , F05D2300/506 , F16L13/007 , F16L15/006 , F16L19/061 , F16L25/0072 , F16L41/084 , F16L41/086 , F23K2301/20 , F23R3/283 , F23R3/286 , F23R3/34 , F23R2900/00005
摘要： A combustor apparatus defines a combustion zone where air and fuel are burned to create high temperature combustion products. The combustor apparatus includes an outer wall, coupling structure on the outer wall adjacent to a fuel inlet opening thereof, a fuel injection system, a fuel feed assembly, and a fitting member. The fuel injection system provides fuel to be burned in the combustion zone. The fuel supply structure includes a threaded inner surface formed from a first material. The fuel feed assembly includes a fuel feed pipe that extends through the fuel inlet opening in the outer wall and has an outlet portion formed from the first material and that is threadedly engaged with the fuel supply structure, and an inlet portion affixed to the outlet portion and formed from a second material. The fitting member secures the fuel feed assembly relative to the outer wall.
摘要翻译：燃烧器装置限定了燃烧区域，其中空气和燃料被燃烧以产生高温燃烧产物。燃烧器装置包括外壁，与其燃料入口相邻的外壁上的联接结构，燃料喷射系统，燃料供给组件和配件构件。燃料喷射系统提供在燃烧区域燃烧的燃料。燃料供给结构包括由第一材料形成的螺纹内表面。所述燃料供给组件包括燃料供给管，所述燃料供给管延伸穿过所述外壁中的所述燃料入口，并且具有由所述第一材料形成并与所述燃料供应结构螺纹接合的出口部分，以及固定到所述出口部分的入口部分并由第二材料形成。装配构件相对于外壁固定燃料供给组件。

36. 发明授权

US08585356B2 Control of blade tip-to-shroud leakage in a turbine engine by directed plasma flow 失效
标题翻译：通过定向等离子体流控制涡轮发动机中的叶片到壳体的泄漏
公开(公告)号：US08585356B2
公开(公告)日：2013-11-19
申请号：US12729380
申请日：2010-03-23
申请人： David J. Wiebe , Matthew D. Montgomery
发明人： David J. Wiebe , Matthew D. Montgomery
IPC分类号： F01D11/20
CPC分类号： F01D11/10 , F01D11/20 , F05D2270/172
摘要： An electrode (54) in the tip (31) of a turbine or compressor blade (30), and a series of electrodes (68) in a shroud (36, 64) that surrounds a rotation path (33) of the blade tip. As the blade tip reaches each shroud electrode, a controller (74) activates an electrical potential between them that generates a plasma-induced gas flow (76) directed toward the pressure side (PS) of the airfoil. The plasma creates a seal between the blade tip and the shroud, and induces a gas flow that opposes a leakage gas flow (52) from the pressure side to the suction side (SS) of the blade over the blade tip (31).
摘要翻译：涡轮或压缩机叶片（30）的尖端（31）中的电极（54）和围绕叶片尖端的旋转路径（33）的护罩（36,64）中的一系列电极（68）。当叶片尖端到达每个护罩电极时，控制器（74）激活它们之间的电位，其产生指向翼型的压力侧（PS）的等离子体引起的气流（76）。等离子体在叶片尖端和护罩之间产生密封，并且引起气体流动，该气流与来自叶片尖端（31）的叶片的压力侧到吸力侧（SS）的泄漏气体流（52）相对。

37. 发明申请

US20130081399A1 CASING FOR A GAS TURBINE ENGINE 有权
标题翻译：用于燃气涡轮发动机
公开(公告)号：US20130081399A1
公开(公告)日：2013-04-04
申请号：US13252325
申请日：2011-10-04
申请人： David J. Wiebe , David A. Little , Richard C. Charron
发明人： David J. Wiebe , David A. Little , Richard C. Charron
IPC分类号： F02C3/14
CPC分类号： F02C3/14 , F01D9/023 , F23R3/02 , F23R3/46
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）。

38. 发明申请

US20130051995A1 INSULATED WALL SECTION 有权
标题翻译：绝缘墙部分
公开(公告)号：US20130051995A1
公开(公告)日：2013-02-28
申请号：US13221156
申请日：2011-08-30
申请人： David J. Wiebe
发明人： David J. Wiebe
IPC分类号： F01D25/26
CPC分类号： F01D25/26 , F01D25/24
摘要： A turbine section of a turbine engine includes rotatable structure, an outer casing disposed about the rotatable structure, and an inner casing disposed about the rotatable structure and suspended radially inwardly from the outer casing. Rotation of the rotatable structure during operation drives at least one of a compressor and a generator. The inner casing defines a hot gas flow path through which hot combustion gases pass during operation. The inner casing comprises a plurality of wall sections. Each wall section includes a panel having an inner portion and an outer portion opposed from and affixed to the inner portion. The inner portion at least partially defines the hot gas flow path and the inner portion is radially spaced from the outer portion such that a substantially fluid tight chamber is formed therebetween. The fluid tight chamber reduces thermal energy transfer from the inner portion to the outer portion.
摘要翻译：涡轮发动机的涡轮机部分包括旋转结构，围绕可旋转结构设置的外壳以及围绕可旋转结构设置并从外壳径向向内悬挂的内壳。在操作期间可旋转结构的旋转驱动压缩机和发电机中的至少一个。内壳限定了在运行期间热燃气通过的热气流路径。内壳包括多个壁部。每个壁部分包括具有内部部分和与内部部分相对并固定到内部部分的外部部分的面板。所述内部部分至少部分地限定所述热气体流动路径，并且所述内部部分与所述外部部分径向间隔开，使得在其间形成基本上流体密封的腔室。流体密封室减少从内部到外部的热能传递。

39. 发明授权

US06672073B2 System and method for supporting fuel nozzles in a gas turbine combustor utilizing a support plate 有权
标题翻译：利用支撑板在燃气轮机燃烧器中支撑燃料喷嘴的系统和方法
公开(公告)号：US06672073B2
公开(公告)日：2004-01-06
申请号：US10152517
申请日：2002-05-22
申请人： David J. Wiebe
发明人： David J. Wiebe
IPC分类号： F02C300
CPC分类号： F23R3/283 , F23R3/286 , F23R3/60
摘要： A system for supporting a plurality of fuel nozzles in a combustor includes a plurality of fuel nozzles coupled to a fuel nozzle support housing proximate an upstream end of each fuel nozzle, a plurality of swirler vanes rigidly coupled to respective fuel nozzles proximate an intermediate portion of the fuel nozzle, a plurality of shrouds rigidly coupled to respective swirler vanes, each shroud having an upstream end adjacent the intermediate portion of the fuel nozzle and a downstream end and a support plate rigidly coupled to the plurality of shrouds proximate an intermediate portion of each of the shrouds. The support plate has a perimeter approximately equal to an inside perimeter of combustor housing which allow the support plate to limit the movement and vibration of the fuel nozzles.
摘要翻译：用于在燃烧器中支撑多个燃料喷嘴的系统包括多个燃料喷嘴，其联接到靠近每个燃料喷嘴的上游端的燃料喷嘴支撑壳体，多个旋流器叶片刚性地联接到相应的燃料喷嘴，燃料喷嘴，刚性地联接到相应的旋流器叶片的多个护罩，每个护罩具有邻近燃料喷嘴的中间部分的上游端，以及下游端和支撑板，刚性地联接到多个护罩，靠近每个护罩的中间部分的护罩。支撑板具有大约等于燃烧器壳体的内周边的周长，其允许支撑板限制燃料喷嘴的运动和振动。

40. 发明授权

US4380896A Annular combustor having ceramic liner 失效
标题翻译：具有陶瓷衬垫的环形燃烧器
公开(公告)号：US4380896A
公开(公告)日：1983-04-26
申请号：US189536
申请日：1980-09-22
申请人： David J. Wiebe
发明人： David J. Wiebe
IPC分类号： F23R3/00 , F23R3/50 , F02C7/20
CPC分类号： F23R3/007 , F23R3/50
摘要： An annular combustor for a jet turbine engine of generally rectangular cr-section having an axially-projecting aft exhaust outlet is lined by a plurality of circumferentially-extending heat-insulating liner segments, preferably ceramic, spaced from the metal shell of the combustor by spring-like spacers. The liner segments have offset tabs at their edges to slidably mate with each other and with retaining clips adjacent to the exhaust outlet, thereby being slidably secured to accept expansion of the metal shell without placing appreciable stress on the liner segments. Arcuate, generally planer liner segments along the forward and aft walls of the combustor are keyed in place by a radially-inward flanged liner segment along the outer perimetrical wall of the shell.
摘要翻译：用于具有轴向突出的后排气出口的具有大致矩形横截面的喷气涡轮发动机的环形燃烧器由多个周向延伸的绝热衬垫段（优选为陶瓷）排列，所述隔热衬套段通过弹簧与燃烧器的金属壳间隔开类间隔物。衬垫段在它们的边缘处具有偏移突出部，以便彼此滑动配合并且具有与排气出口相邻的保持夹，从而可滑动地固定以接受金属壳的膨胀，而不会在衬片段上施加明显的应力。沿着燃烧器的前壁和后壁的弧形，通常为平面的衬垫段通过沿着外壳的外周壁的径向向内的带凸缘的衬垫段键合就位。

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