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公开(公告)号：US07329093B2
公开(公告)日：2008-02-12
申请号：US11340577
申请日：2006-01-27
申请人： Thomas W. Vandeputte , John E. Greene , Peter C. Selent , Linda J. Farral , Sze Bun Brian Chan , Brian P. Arness
发明人： Thomas W. Vandeputte , John E. Greene , Peter C. Selent , Linda J. Farral , Sze Bun Brian Chan , Brian P. Arness
IPC分类号： F01D9/00
CPC分类号： F01D5/141 , F05D2240/128 , F05D2250/74 , Y10S416/02
摘要： First stage stator vanes for a turbine comprised airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I, which define a plurality of radially spaced profile sections forming the nominal profile. The Z coordinate values for each profile section are radial distances from the turbine axis to a portion of the surface of revolution about the axis containing the profile section. The X and Y values for each profile section are coordinate values which, when connected by smooth continuing arcs define the airfoil profile section along the surface of revolution portion. The radially spaced profile sections are joined smoothly with one another to form the nominal airfoil profile.
摘要翻译： 用于涡轮机的第一级定子叶片包括基本上按照表I中以英寸为单位的X，Y和Z的笛卡尔坐标值的翼型分布，其定义了形成标称轮廓的多个径向间隔的轮廓部分。 每个轮廓截面的Z坐标值是从涡轮机轴线到围绕围绕轮廓部分的轴线的旋转表面的一部分的径向距离。 每个轮廓截面的X和Y值是坐标值，当通过平滑的连续弧连接时，沿着旋转部分的表面限定翼型轮廓部分。 径向隔开的轮廓部分彼此平滑地连接以形成标称翼型轮廓。
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公开(公告)号：US20110311353A1
公开(公告)日：2011-12-22
申请号：US13216347
申请日：2011-08-24
申请人： Brian P. Arness , John E. Greene , Sze Bun B. Chan
发明人： Brian P. Arness , John E. Greene , Sze Bun B. Chan
IPC分类号： F01D11/08
CPC分类号： F01D9/041 , F01D11/005 , F01D25/246 , F05D2220/3212 , F05D2230/64 , F05D2240/57 , F05D2250/182 , F05D2260/30 , F05D2300/505
摘要： A method for assembling a turbine nozzle assembly with respect to a combustor of a gas turbine engine is provided. The method includes coupling a radial outer retaining ring to an aft end of the combustor. A plurality of turbine nozzles is provided. Each turbine nozzle includes an inner band, a radially opposing outer band, and at least one vane extending between the inner band and the outer band. The outer band of each turbine nozzle is coupled to the outer retaining ring to define the turbine nozzle assembly. An inner retaining ring is positioned about an axis of the gas turbine engine and coupled to the inner band of each turbine nozzle.
摘要翻译： 提供了一种用于组装相对于燃气涡轮发动机的燃烧器的涡轮喷嘴组件的方法。 该方法包括将径向外保持环联接到燃烧器的后端。 提供多个涡轮喷嘴。 每个涡轮喷嘴包括内带，径向相对的外带，以及在内带和外带之间延伸的至少一个叶片。 每个涡轮喷嘴的外带连接到外保持环以限定涡轮喷嘴组件。 内部保持环围绕燃气涡轮发动机的轴线定位并且联接到每个涡轮喷嘴的内部带。
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公开(公告)号：US08403634B2
公开(公告)日：2013-03-26
申请号：US13216347
申请日：2011-08-24
申请人： Brian P. Arness , John E. Greene , Sze Bun B. Chan
发明人： Brian P. Arness , John E. Greene , Sze Bun B. Chan
IPC分类号： F01D9/04
CPC分类号： F01D9/041 , F01D11/005 , F01D25/246 , F05D2220/3212 , F05D2230/64 , F05D2240/57 , F05D2250/182 , F05D2260/30 , F05D2300/505
摘要： A retaining seal assembly for use in a gas turbine engine is provided. The retaining seal assembly comprises an outer retaining ring coupled to an aft end of a gas turbine engine combustor. A turbine nozzle is coupled to the outer retaining ring and comprises an outer band. The outer band comprises a leading edge and an opposing trailing edge that defines a slot. A retention seal comprises a first end positioned within the slot, a generally opposing second end that contacts the outer retaining ring, and a body extending between the first end and the second end. The body further comprises an insertion portion positioned within a passage formed in the outer band. The retention seal is fabricated from a resilient material and is configured to facilitate coupling the turbine nozzle to the outer retaining ring.
摘要翻译： 提供了一种用于燃气轮机的保持密封组件。 保持密封组件包括联接到燃气涡轮发动机燃烧器的后端的外保持环。 涡轮喷嘴连接到外保持环并且包括外带。 外带包括前缘和限定槽的相对的后缘。 保持密封件包括定位在槽内的第一端，与外保持环接触的大致相对的第二端，以及在第一端和第二端之间延伸的本体。 主体还包括位于形成在外带中的通道内的插入部分。 保持密封件由弹性材料制成并且构造成便于将涡轮喷嘴连接到外保持环。
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公开(公告)号：US08038389B2
公开(公告)日：2011-10-18
申请号：US11325185
申请日：2006-01-04
申请人： Brian P. Arness , John E. Greene , Sze Bun B. Chan
发明人： Brian P. Arness , John E. Greene , Sze Bun B. Chan
IPC分类号： F01D9/04
CPC分类号： F01D9/041 , F01D11/005 , F01D25/246 , F05D2220/3212 , F05D2230/64 , F05D2240/57 , F05D2250/182 , F05D2260/30 , F05D2300/505
摘要： A turbine nozzle assembly and a method for assembling the turbine nozzle assembly with respect to a combustor of a gas turbine engine are provided. The method includes coupling a radial outer retaining ring to an aft end of the combustor. A plurality of turbine nozzles are provided. Each turbine nozzle includes an inner band, a radially opposing outer band, and at least one vane extending between the inner band and the outer band. The outer band of each turbine nozzle is coupled to the outer retaining ring to define the turbine nozzle assembly. An inner retaining ring is positioned about an axis of the gas turbine engine and coupled to the inner band of each turbine nozzle.
摘要翻译： 提供了一种涡轮喷嘴组件和用于将涡轮喷嘴组件相对于燃气涡轮发动机的燃烧器组装的方法。 该方法包括将径向外保持环联接到燃烧器的后端。 提供多个涡轮喷嘴。 每个涡轮喷嘴包括内带，径向相对的外带，以及在内带和外带之间延伸的至少一个叶片。 每个涡轮喷嘴的外带连接到外保持环以限定涡轮喷嘴组件。 内部保持环围绕燃气涡轮发动机的轴线定位并且联接到每个涡轮喷嘴的内部带。
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公开(公告)号：US08011894B2
公开(公告)日：2011-09-06
申请号：US12168929
申请日：2008-07-08
IPC分类号： F01D5/30
CPC分类号： F01D5/3007 , F01D11/006 , Y10T29/49297
摘要： A sealing system for sealing a gap between a dovetail tab of a bucket and a rotor. The sealing system may include a sealing slot positioned about the dovetail tab and a pivot plate positioned within the sealing slot. The sealing slot may include a pivot point and a rest ledge such that the pivot plate pivots about the pivot point and into the gap when the bucket rotates.
摘要翻译： 一种用于密封桶的燕尾形突片和转子之间的间隙的密封系统。 密封系统可以包括围绕燕尾舌片定位的密封槽和位于密封槽内的枢轴板。 密封槽可以包括枢转点和休止凸缘，使得当铲斗旋转时，枢转板围绕枢转点枢转并进入间隙。
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公开(公告)号：US08210821B2
公开(公告)日：2012-07-03
申请号：US12168932
申请日：2008-07-08
IPC分类号： F03B3/12
CPC分类号： F01D5/3007 , F01D5/081 , F01D5/087 , F01D11/005 , F01D11/006 , F01D11/02
摘要： A labyrinth seal that may include a first leg positioned about a high-pressure side of the dovetail tab, a second leg positioned about a low-pressure side of the dovetail tab, and a labyrinth chamber positioned between the first leg and the second leg. High-pressure fluid passing through the gap about the first leg expands within the labyrinth chamber so as to limit an amount of the high-pressure fluid that passes beyond the second leg.
摘要翻译： 迷宫式密封件，其可以包括围绕燕尾形突片的高压侧定位的第一腿部，围绕燕尾形舌片的低压侧定位的第二腿部，以及位于第一腿部和第二腿部之间的迷宫腔室。 通过第一腿周围的间隙的高压流体在迷宫腔内膨胀，以限制超过第二腿的高压流体的量。
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公开(公告)号：US20100007092A1
公开(公告)日：2010-01-14
申请号：US12168932
申请日：2008-07-08
IPC分类号： F02F11/00 , F16J15/447
CPC分类号： F01D5/3007 , F01D5/081 , F01D5/087 , F01D11/005 , F01D11/006 , F01D11/02
摘要： A labyrinth seal that may include a first leg positioned about a high-pressure side of the dovetail tab, a second leg positioned about a low-pressure side of the dovetail tab, and a labyrinth chamber positioned between the first leg and the second leg. High-pressure fluid passing through the gap about the first leg expands within the labyrinth chamber so as to limit an amount of the high-pressure fluid that passes beyond the second leg.
摘要翻译： 迷宫式密封件，其可以包括围绕燕尾形突片的高压侧定位的第一腿部，围绕燕尾形舌片的低压侧定位的第二腿部，以及位于第一腿部和第二腿部之间的迷宫腔室。 通过第一腿周围的间隙的高压流体在迷宫腔内膨胀，以限制超过第二腿的高压流体的量。
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公开(公告)号：US5716192A
公开(公告)日：1998-02-10
申请号：US713321
申请日：1996-09-13
申请人： James S. Phillips , Brian P. Arness
发明人： James S. Phillips , Brian P. Arness
摘要： A bowed airfoil is provided which includes a plurality of passages disposed between a pressure side wall and a suction side wall. The pressure and suction side walls extend widthwise between a leading edge and a trailing edge, and spanwise between inner and outer platforms. Passages extend spanwise between the inner and outer platforms. Ribs, each having a rib end, separate adjacent passages. Passage turns, each having an end wall, connect the passages. The end wall of each passage turn acutely converges with one of the side walls, and a first fillet extends between the acutely converging side wall and end wall. According to one embodiment, each rib end acutely converges with the other of the side walls, and a second fillet extends between the acutely converging side wall and rib end.
摘要翻译： 提供了一种弓形翼片，其包括设置在压力侧壁和吸力侧壁之间的多个通道。 压力和吸力侧壁在前缘和后缘之间沿宽度方向延伸，并且在内平台和外平台之间展开。 通道在内外平台之间展开。 每个肋具有肋端，分隔相邻通道。 通道转动，每个都有一个端壁，连接通道。 每个通道的端壁与一个侧壁急剧地收敛，并且第一圆角在急转会的侧壁和端壁之间延伸。 根据一个实施例，每个肋端部与另一个侧壁急剧地收敛，并且第二圆角在急转弯侧壁和肋端之间延伸。
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公开(公告)号：US5403156A
公开(公告)日：1995-04-04
申请号：US143681
申请日：1993-10-26
申请人： Brian P. Arness , Wesley D. Brown
发明人： Brian P. Arness , Wesley D. Brown
CPC分类号： F01D5/081 , F01D5/3007 , Y10T29/49321 , Y10T29/49341
摘要： A meter plate formed from a depending member extending from the root of a turbine blade just short of the edge of the bottom of the broach in the disk in the live rim area is cast integrally with the blade and serves to meter coolant flow from the on board injector to internally of the blade. The final dimension can be configured in the machining operation of the blade to attain the desired amount of coolant flow for internal blade cooling.
摘要翻译： 从靠近涡轮叶片的根部延伸的仪表板，其刚好短于活动边缘区域中的盘中的拉刀的底部边缘，与叶片一体地铸造，用于测量来自 板式进样器到刀片内部。 可以在刀片的加工操作中配置最终尺寸，以获得用于内部叶片冷却的所需量的冷却剂流。
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公开(公告)号：US08210820B2
公开(公告)日：2012-07-03
申请号：US12168927
申请日：2008-07-08
申请人： Brian P. Arness , John D. Ward
发明人： Brian P. Arness , John D. Ward
IPC分类号： F03B3/12
CPC分类号： F01D5/081 , F01D5/3007 , F01D11/006 , F05D2300/614 , Y10T29/49321
摘要： A dovetail seal assembly for sealing a gap between a bucket dovetail and a rotor. The dovetail seal assembly may include a sealing slot positioned about the dovetail, a high-pressure supply hole in communication with the sealing slot, and a deformable seal positioned about the sealing slot and into the gap.
摘要翻译： 燕尾密封组件，用于密封桶形燕尾榫和转子之间的间隙。 燕尾密封组件可以包括围绕燕尾槽定位的密封槽，与密封槽连通的高压供应孔以及围绕密封槽定位到间隙中的可变形密封件。
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