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11. 发明授权

US06402466B1 Leaf seal for gas turbine stator shrouds and a nozzle band 有权
标题翻译：燃气轮机定子护罩和喷嘴带的叶片密封
公开(公告)号：US06402466B1
公开(公告)日：2002-06-11
申请号：US09571814
申请日：2000-05-16
申请人： Steven Sebastian Burdgick , Brendan Francis Sexton
发明人： Steven Sebastian Burdgick , Brendan Francis Sexton
IPC分类号： F10D1108
CPC分类号： F01D9/04 , F01D11/005 , F05D2240/11 , F05D2240/55 , F05D2260/30 , F16J15/0887
摘要： A leaf seal assembly is secured to the trailing edge of a shroud segment for sealing between the shroud segment and the leading edge side wall of a nozzle outer band. The leaf seal includes a circumferentially elongated seal plate biased by a pair of spring clips disposed in a groove along the trailing edge of the shroud segment to maintain the seal plate in engagement with the flange on the leading edge side wall of the nozzle outer band. The leaf seal plate and spring clips receive pins tack-welded to the shroud segment to secure the leaf seal assembly in place.
摘要翻译：叶片密封组件固定到护罩段的后缘，用于密封护罩段和喷嘴外带的前缘侧壁之间。叶片密封件包括由沿着护罩段的后缘设置在凹槽中的一对弹簧夹偏压的周向细长的密封板，以保持密封板与喷嘴外带的前缘侧壁上的凸缘接合。叶片密封板和弹簧夹接收固定在护罩部分上的销钉，以将叶片密封组件固定就位。

12. 发明授权

US08684697B2 Steam turbine singlet nozzle design for breech loaded assembly 有权
标题翻译：蒸汽轮机单线嘴设计用于后膛加载组件
公开(公告)号：US08684697B2
公开(公告)日：2014-04-01
申请号：US12966476
申请日：2010-12-13
申请人： Dominick Joseph Werther , Steven Sebastian Burdgick
发明人： Dominick Joseph Werther , Steven Sebastian Burdgick
IPC分类号： F01D25/28
CPC分类号： F01D9/042
摘要： A steam turbine nozzle airfoil with integral inner and outer sidewalls is engaged with an inner ring and an outer ring in a nozzle assembly. Previous designs required large clearances between radial surfaces to permit simultaneous circumferential loading of the inner and outer sidewall into the inner and outer rings. The inventive arrangement provides for breech loading of the inner sidewall into the inner ring which allows near line-to-line radial contact on the hooks between the rings and the integral sidewalls of the Singlet nozzle airfoil. Tighter radial clearance overcome problems with loose assembly such as movement during welding, gaps leading to stress risers and performance issues associated with nozzle throat control.
摘要翻译：具有整体内壁和外侧壁的汽轮机喷嘴翼型件与喷嘴组件中的内环和外环接合。以前的设计需要径向表面之间的大间隙，以允许内侧壁和外侧壁同时周向地加载到内圈和外圈中。本发明的装置提供了内侧壁进入内环的后膛加载，其允许在环之间的钩和单列喷嘴翼型的整体侧壁之间的近线对线的径向接触。更紧密的径向间隙克服了松动组装的问题，例如焊接过程中的移动，导致应力梯度的间隙和与喷嘴喉部控制相关的性能问题。

13. 发明申请

US20120141260A1 STEAM TURBINE SINGLET INTERFACE FOR MARGIN STAGE NOZZLES WITH PINNED OR BOLTED INNER RING 有权
标题翻译：蒸汽涡轮机接口，用于带刺或内嵌环的舷梯
公开(公告)号：US20120141260A1
公开(公告)日：2012-06-07
申请号：US12958807
申请日：2010-12-02
申请人： Steven Sebastian Burdgick , Dominick Joseph Werther
发明人： Steven Sebastian Burdgick , Dominick Joseph Werther
IPC分类号： F01D9/02 , B23P15/04
CPC分类号： F01D9/042
摘要： A steam turbine singlet nozzle airfoil with integral outer sidewall is engaged with an inner ring and an outer ring in a nozzle assembly. The interface of the outer sidewall with the outer ring may include a plurality of mechanical hooks on one or both of the upstream face and the outer radial face of the outer sidewall that engage with complimentary structures on the outer ring. The outer interface may further include low energy welds along limited distances of one or both of the upstream or downstream interface of the outer sidewall and the outer ring. An inner radial end of the singlet nozzle airfoil is pinned into position and fastened to the inner ring. Without a need for high heat welds, distortion of the airfoil and the steam flow path and the associated rework is eliminated and stage performance is improved.
摘要翻译：具有整体外侧壁的蒸汽轮机单线喷嘴翼型件与喷嘴组件中的内环和外环接合。外侧壁与外环的界面可以包括在外侧壁的上游面和外径向面中的一个或两个上与外环上的互补结构接合的多个机械钩。外界面还可以包括沿着外侧壁和外环的上游或下游界面中的一个或两个的有限距离的低能量焊缝。单列喷嘴翼型的内径向端部被固定到位并紧固到内圈。不需要高热焊接，消除了翼型件和蒸汽流动路径的变形以及相关的返工，并且提高了工作台性能。

14. 发明授权

US07458770B2 Adjustable support for steam turbine diaphragms 有权
标题翻译：可调节支持汽轮机隔膜
公开(公告)号：US07458770B2
公开(公告)日：2008-12-02
申请号：US11164603
申请日：2005-11-30
申请人： Thomas Patrick Russo , Kenneth J. Robertson , Steven Sebastian Burdgick
发明人： Thomas Patrick Russo , Kenneth J. Robertson , Steven Sebastian Burdgick
IPC分类号： F01D25/24
CPC分类号： F01D3/02 , F01D25/24 , F01D25/246 , F05D2220/31
摘要： The present invention provides a steam turbine that has upper and lower halves of diaphragm. The steam turbine of the present invention also provides an adjustable support bar attached to at least the upper half or the lower half of the diaphragm. The adjustable support bar of the present invention has a screw therein such that the adjustable support bar can raise or lower the upper half or the lower half of the diaphragm without removing each half of the diaphragm. Also provided are methods for adjusting and supporting a vertical position of the upper half and the lower half of the diaphragm at a horizontal split line in a steam turbine.
摘要翻译：本发明提供一种具有隔膜的上半部和下半部的汽轮机。本发明的蒸汽轮机还提供了一个可调节的支撑杆，该支撑杆至少连接到隔膜的上半部或下半部。本发明的可调节支撑杆在其中具有螺钉，使得可调节支撑杆可以在不隔离隔膜的每一半的情况下升高或降低隔膜的上半部或下半部。还提供了用于在蒸汽轮机中的水平分割线处调节和支撑隔膜的上半部和下半部的垂直位置的方法。

15. 发明授权

US07104761B2 Hybrid turbine blade and related method 失效
标题翻译：混合式涡轮叶片及相关方法
公开(公告)号：US07104761B2
公开(公告)日：2006-09-12
申请号：US10900222
申请日：2004-07-28
申请人： Steven Sebastian Burdgick , Guy W. DeLeonardo , Wendy W. Lin , Christophe Lanaud
发明人： Steven Sebastian Burdgick , Guy W. DeLeonardo , Wendy W. Lin , Christophe Lanaud
IPC分类号： F01D5/28
CPC分类号： F01D5/147 , Y02T50/672 , Y10T29/49337
摘要： A method of manufacturing a blade for assembly on a steam turbine rotor wheel includes forming an airfoil portion with plural pockets and filling the pockets with more than one filler material chosen as a function of required temperature capability.
摘要翻译：制造用于组装在蒸汽轮机转子轮上的叶片的方法包括：形成具有多个袋的翼型部分，并且根据所需的温度能力选择多种填充材料来填充袋。

16. 发明授权

US06648332B1 Steam turbine packing casing horizontal joint seals and methods of forming the seals 有权
标题翻译：蒸汽涡轮机包装水平接头密封件和形成密封件的方法
公开(公告)号：US06648332B1
公开(公告)日：2003-11-18
申请号：US10206827
申请日：2002-07-29
申请人： Steven Sebastian Burdgick
发明人： Steven Sebastian Burdgick
IPC分类号： F16J15447
CPC分类号： F01D11/02 , F01D11/003 , F01D11/005 , F01D25/246 , F16J15/0887 , F16J15/122
摘要： Spline seals are formed at the joints between packing casing shells in a steam turbine having high pressure and intermediate pressure turbine sections sealing between the high pressure and intermediate pressure regions on opposite axial sides of the packing casing. The spline seals extend in registering grooves from adjacent the seal segments of the rotor radially outwardly to adjacent axial load surfaces cooperable between the outer shell and the packing casing. The spline seals minimize or eliminate steam leakage paths through the horizontal joint of the packing casing shells.
摘要翻译：花键密封件形成在具有高压和中压涡轮部分的蒸汽涡轮机中的包装壳体之间的接头处，该部分密封在包装壳体的相对轴向侧上的高压和中压区域之间。花键密封件沿对准凹槽从转子的密封段径向向外延伸到在外壳和包装壳体之间配合的相邻的轴向载荷表面。花键密封最小化或消除穿过包装壳体壳体的水平接头的蒸汽泄漏路径。

17. 发明授权

US06506013B1 Film cooling for a closed loop cooled airfoil 有权
标题翻译：闭环冷却翼型薄膜冷却
公开(公告)号：US06506013B1
公开(公告)日：2003-01-14
申请号：US09561865
申请日：2000-04-28
申请人： Steven Sebastian Burdgick , Yufeng Phillip Yu , Gary Michael Itzel
发明人： Steven Sebastian Burdgick , Yufeng Phillip Yu , Gary Michael Itzel
IPC分类号： F01D514
CPC分类号： F01D5/186 , F01D5/188 , F05D2260/201 , F05D2260/202 , F05D2260/205 , F05D2260/2322
摘要： Turbine stator vane segments have radially inner and outer walls with vanes extending therebetween. The inner and outer walls are compartmentalized and have impingement plates. Steam flowing into the outer wall plenum passes through the impingement plate for impingement cooling of the outer wall upper surface. The spent impingement steam flows into cavities of the vane having inserts for impingement cooling the walls of the vane. The steam passes into the inner wall and through the impingement plate for impingement cooling of the inner wall surface and for return through return cavities having inserts for impingement cooling of the vane surfaces. At least one film cooling hole is defined through a wall of at least one of the cavities for flow communication between an interior of the cavity and an exterior of the vane. The film cooling hole(s) are defined adjacent a potential low LCF life region, so that cooling medium that bleeds out through the film cooling hole(s) reduces a thermal gradient in a vicinity thereof, thereby the increase the LCF life of that region.
摘要翻译：涡轮机定子叶片段具有径向的内壁和外壁，叶片在其间延伸。内壁和外壁分隔开并具有冲击板。流入外壁集气室的蒸汽通过冲击板，用于外壁上表面的冲击冷却。废冲击蒸汽流入具有用于冲击冷却叶片壁的插入件的叶片的空腔中。蒸汽进入内壁并通过冲击板，用于内壁表面的冲击冷却，并通过具有用于叶片表面的冲击冷却的插入件的返回腔返回。至少一个薄膜冷却孔通过至少一个空腔的壁限定，用于腔的内部和叶片的外部之间的流动连通。膜冷却孔邻近潜在的低LCF寿命区限定，使得通过膜冷却孔渗出的冷却介质降低其附近的热梯度，从而增加该区域的LCF寿命。

18. 发明授权

US06435814B1 Film cooling air pocket in a closed loop cooled airfoil 失效
标题翻译：薄膜冷却气囊在闭环冷却翼型中
公开(公告)号：US06435814B1
公开(公告)日：2002-08-20
申请号：US09571813
申请日：2000-05-16
申请人： Yufeng Phillip Yu , Gary Michael Itzel , Sarah Jane Osgood , Radhakrishna Bagepalli , Waylon Willard Webbon , Steven Sebastian Burdgick
发明人： Yufeng Phillip Yu , Gary Michael Itzel , Sarah Jane Osgood , Radhakrishna Bagepalli , Waylon Willard Webbon , Steven Sebastian Burdgick
IPC分类号： F01D904
CPC分类号： F02C7/18 , F01D5/189 , F05D2240/12 , F05D2240/81 , F05D2260/201 , F05D2260/205 , F05D2260/2212 , F05D2260/2322
摘要： Turbine stator vane segments have radially inner and outer walls with vanes extending between them. The inner and outer walls are compartmentalized and have impingement plates. Steam flowing into the outer wall plenum passes through the impingement plate for impingement cooling of the outer wall upper surface. The spent impingement steam flows into cavities of the vane having inserts for impingement cooling the walls of the vane. The steam passes into the inner wall and through the impingement plate for impingement cooling of the inner wall surface and for return through return cavities having inserts for impingement cooling of the vane surfaces. To provide for air film cooing of select portions of the airfoil outer surface, at least one air pocket is defined on a wall of at least one of the cavities. Each air pocket is substantially closed with respect to the cooling medium in the cavity and cooling air pumped to the air pocket flows through outlet apertures in the wall of the airfoil to cool the same.
摘要翻译：涡轮机定子叶片段具有径向的内壁和外壁，叶片在它们之间延伸。内壁和外壁分隔开并具有冲击板。流入外壁集气室的蒸汽通过冲击板，用于外壁上表面的冲击冷却。废冲击蒸汽流入具有用于冲击冷却叶片壁的插入件的叶片的空腔中。蒸汽进入内壁并通过冲击板，用于内壁表面的冲击冷却，并通过具有用于叶片表面的冲击冷却的插入件的返回腔返回。为了提供翼型件外表面的选定部分的空气膜冷却，至少一个气穴限定在至少一个空腔的壁上。每个空气袋相对于空腔中的冷却介质基本封闭，并且泵送到空气袋的冷却空气流过翼型件的壁中的出口孔以使其冷却。

19. 发明授权

US06331096B1 Apparatus and methods for impingement cooling of an undercut region adjacent a side wall of a turbine nozzle segment 有权
标题翻译：用于与涡轮喷嘴段的侧壁相邻的底切区域的冲击冷却的装置和方法
公开(公告)号：US06331096B1
公开(公告)日：2001-12-18
申请号：US09543457
申请日：2000-04-05
申请人： Steven Sebastian Burdgick , Gary Michael Itzel
发明人： Steven Sebastian Burdgick , Gary Michael Itzel
IPC分类号： F01D2508
CPC分类号： F01D25/12 , F01D11/005 , F05D2240/81
摘要： A gas turbine nozzle segment has outer and inner bands. Each band includes a side wall, a cover and an impingement plate between the cover and nozzle wall defining two cavities on opposite sides of the impingement plate. Cooling steam is supplied to one cavity for flow through apertures of the impingement plate to cool the nozzle wall. The side wall of the band and inturned flange define with the nozzle wall an undercut region. The inturned flange has a plurality of apertures for directing cooling steam to cool the side wall between adjacent nozzle segments.
摘要翻译：燃气涡轮喷嘴段具有外带和内带。每个带包括在盖和喷嘴壁之间的侧壁，盖和冲击板，其在冲击板的相对侧上限定两个空腔。冷却蒸汽被供应到一个空腔以流过冲击板的孔以冷却喷嘴壁。带和内壁凸缘的侧壁限定了喷嘴壁的底切区域。内翻法兰具有多个孔，用于引导冷却蒸汽冷却相邻喷嘴段之间的侧壁。

20. 发明授权

US06190120B1 Partially turbulated trailing edge cooling passages for gas turbine nozzles 有权
标题翻译：用于燃气轮机喷嘴的部分紊流后缘冷却通道
公开(公告)号：US06190120B1
公开(公告)日：2001-02-20
申请号：US09312427
申请日：1999-05-14
申请人： Jonathan Carl Thatcher , Steven Sebastian Burdgick
发明人： Jonathan Carl Thatcher , Steven Sebastian Burdgick
IPC分类号： F01D518
CPC分类号： F01D5/187 , F05D2260/2212 , F05D2260/22141
摘要： A plurality of passages are spaced one from the other along the length of a trailing edge of a nozzle vane in a gas turbine. The passages lie in communication with a cavity in the vane for flowing cooling air from the cavity through the passages through the tip of the trailing edge into the hot gas path. Each passage is partially turbulated and includes ribs in an aft portion thereof to provide enhanced cooling effects adjacent the tip of the trailing edge. The major portions of the passages are smooth bore. By this arrangement, reduced temperature gradients across the trailing edge metal are provided. Additionally, the inlets to each of the passages have a restriction whereby a reduced magnitude of compressor bleed discharge air is utilized for trailing edge cooling purposes.
摘要翻译：沿着燃气轮机中的喷嘴叶片的后缘的长度，多个通道彼此间隔开。通道与叶片中的空腔连通，用于使来自空腔的冷却空气通过通过后缘的尖端的通道进入热气体通道。每个通道部分地是混浊的，并且在其后部包括肋，以提供邻近后缘的尖端的增强的冷却效果。通道的主要部分是光滑的孔。通过这种布置，提供了跨越后缘金属的降低的温度梯度。此外，每个通道的入口具有限制，由此减小压缩机排放空气的大小用于后缘冷却目的。

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