-
公开(公告)号：US06932568B2
公开(公告)日：2005-08-23
申请号：US10375441
申请日：2003-02-27
申请人： Andrew Charles Powis , Ronald Eugene McRae, Jr. , Jonathan Philip Clarke , Jonathan Jordan Peterman , Robert Alan Frederick , Edward Eugene Gibler , Brian David Keith
发明人： Andrew Charles Powis , Ronald Eugene McRae, Jr. , Jonathan Philip Clarke , Jonathan Jordan Peterman , Robert Alan Frederick , Edward Eugene Gibler , Brian David Keith
CPC分类号： F01D9/041 , B22C21/14 , E05Y2900/402 , F01D5/189 , F01D25/246 , F05D2240/12 , F05D2240/81 , F05D2260/201 , F05D2260/22141 , F05D2260/30 , Y02T50/67 , Y02T50/676
摘要： A turbine nozzle segment includes at least one hollow airfoil extending radially between radially outer and inner band segments, a clockwise open hook on a clockwise end at an aft end of the outer band segment, and counter-clockwise open hook on a counter-clockwise end at the aft end of the outer band segments. An exemplary embodiment of the turbine nozzle segment includes a load stop extending radially outwardly from the outer band segment. At least one aftwardly facing load face is at the aft end of the nozzle segment at the outer band segment. The clockwise open hook is C-shaped and the counter-clockwise open hook is a shiplap hook. Another embodiment of the turbine nozzle segment has only one hollow airfoil with an airfoil wall surrounding a bifurcated cavity divided into forward and aft cavities by a bifurcating rib extending between pressure and suction sides of the airfoil wall.
摘要翻译： 涡轮喷嘴段包括至少一个在径向外带段和内带段之间径向延伸的中空翼型件，在外带段的后端处的顺时针端部上的顺时针打开的钩子，以及逆时针方向的逆时针方向的开口钩 在外带段的后端。 涡轮喷嘴段的示例性实施例包括从外带段径向向外延伸的负载停止。 至少一个面向前的负载面处于外带段处的喷嘴段的后端。 顺时针打开的钩子是C形的，逆时针打开的钩子是一个shiplap钩子。 涡轮喷嘴段的另一个实施例仅具有一个中空翼型件，其翼型壁围绕通过在翼型件壁的压力侧和抽吸侧之间延伸的分叉肋分成前部和后部空腔的分叉空腔。
-
公开(公告)号：US07008185B2
公开(公告)日：2006-03-07
申请号：US10375415
申请日：2003-02-27
申请人： Jonathan Jordan Peterman , Andrew Charles Powis , Ronald Eugene McRae, Jr. , Jonathan Philip Clarke , Robert Alan Frederick , Edward Eugene Gibler , Brian David Keith
发明人： Jonathan Jordan Peterman , Andrew Charles Powis , Ronald Eugene McRae, Jr. , Jonathan Philip Clarke , Robert Alan Frederick , Edward Eugene Gibler , Brian David Keith
CPC分类号： F01D5/189 , F01D9/041 , F05D2240/81 , F05D2250/70 , F05D2260/201 , F05D2260/30 , Y02T50/67 , Y02T50/676
摘要： A turbine nozzle bifurcated impingement baffle includes axially forward and aft chambers with a gap therebetween, impingement holes through forward and aft baffle walls of the forward and aft chambers respectively, and a plenum chamber in fluid flow communication with the forward and aft chambers. An exemplary embodiment of the bifurcated impingement baffle further includes a single cooling air inlet to the plenum chamber enclosed within a plenum chamber enclosure the plenum chamber. A sealing plate is mounted between and sealed to the plenum chamber enclosure and the forward and aft chambers. The sealing plate has forward and aft inlet apertures disposed between the plenum chamber and the forward and aft chambers respectively. Forward and aft end plates cap radially inner ends of the forward and aft chambers. An outlet aperture in the forward end plate has an interstage seal cavity feed tube disposed therethrough.
摘要翻译： 涡轮喷嘴分叉冲击挡板包括轴向前后空间，其间具有间隙，冲击孔分别通过前后舱的前后挡板壁和与前室和后室流体连通的增压室。 分叉式冲击挡板的示例性实施例还包括一个单独的冷却空气入口，该冷却空气入口封闭在包围增压室的增压室内。 密封板安装在密封室之间并密封到增压室外壳和前后室。 密封板具有分别设置在增压室和前后室之间的前后入口孔。 前端和后端板盖住前后室的径向内端。 前端板中的出口孔具有穿过其设置的级间密封腔供给管。
-
3.发明授权Gas turbine engine turbine nozzle segment with a single hollow vane having a bifurcated cavity 有权燃气涡轮发动机涡轮喷嘴段具有单个空心叶片，其具有分叉腔公开(公告)号：US06969233B2
公开(公告)日：2005-11-29
申请号：US10375585
申请日：2003-02-27
申请人： Andrew Charles Powis , Ronald Eugene McRae, Jr. , Jonathan Philip Clarke , Jonathan Jordan Peterman , Robert Alan Frederick , Edward Eugene Gibler , Brian David Keith
发明人： Andrew Charles Powis , Ronald Eugene McRae, Jr. , Jonathan Philip Clarke , Jonathan Jordan Peterman , Robert Alan Frederick , Edward Eugene Gibler , Brian David Keith
CPC分类号： F01D5/189 , B22C21/14 , F05D2240/12 , F05D2240/81 , F05D2260/201 , F05D2260/22141 , Y02T50/67 , Y02T50/671 , Y02T50/676
摘要： A turbine nozzle segment includes a single hollow airfoil extending radially between radially outer and inner band segments. The airfoil has an airfoil wall with pressure and suction sides extending axially between leading and trailing edges of the airfoil. The airfoil wall surrounds a bifurcated cavity and a bifurcating rib extends through the bifurcated cavity and between the pressure and suction sides of the airfoil wall dividing the bifurcated cavity into forward and aft cavities. A stiffening rib extends radially outwardly from and along a radially outer surface of the outer band segment and axially and circumferentially from a pressure side forward corner of the outer band segment to the bifurcating rib. The outer and inner band segments, the bifurcating rib, and the stiffening rib are integral and made from a unitary one-piece casting.
摘要翻译： 涡轮喷嘴段包括在径向外部段和内部带段之间径向延伸的单个中空翼型件。 翼型件具有翼型壁，其压力和吸力侧面在翼型的前缘和后缘之间轴向延伸。 翼型壁围绕分叉的空腔并且分叉肋延伸穿过分叉的空腔，并且在翼型壁的压力和吸力侧之间延伸，将分叉腔分成前后空腔。 加强筋从外带段的径向外表面径向向外延伸，并且从外带段的压力侧前角轴向和周向延伸到分叉肋。 外带和内带段，分叉肋和加强筋是整体的，由一体式单件铸件制成。
-
公开(公告)号：US06609880B2
公开(公告)日：2003-08-26
申请号：US09998835
申请日：2001-11-15
IPC分类号： F10D906
CPC分类号： F01D25/12 , F01D5/189 , F01D9/02 , F05D2260/201 , Y02T50/676
摘要： A method for assembling a turbine nozzle for a gas turbine engine facilitates improving cooling efficiency of the turbine nozzle. The method includes providing a hollow doublet including a leading airfoil and a trailing airfoil coupled by at least one platform, wherein each airfoil includes a first sidewall and a second sidewall that extend between a respective leading and trailing edge. The method also includes inserting an insert into at least one of the airfoils, wherein the insert includes a first sidewall including a first plurality of cooling openings that extending therethrough, and a second sidewall including a second plurality of cooling openings extending therethrough, and wherein the first plurality of cooling openings facilitate more airfoil vane sidewall cooling than the second plurality of cooling openings.
摘要翻译： 用于组装燃气涡轮发动机的涡轮喷嘴的方法有利于提高涡轮喷嘴的冷却效率。 该方法包括提供一个中空的双层结构，该空心双层结构包括一个由至少一个平台联接的先导翼型件和后翼型件，其中每个翼型件包括在相应的前缘和后缘之间延伸的第一侧壁和第二侧壁。 该方法还包括将插入件插入到至少一个翼型件中，其中插入件包括第一侧壁，第一侧壁包括第一多个冷却开口，第一多个冷却开口延伸穿过其中，第二侧壁包括延伸穿过其中的第二多个冷却开口， 第一多个冷却开口有助于比第二多个冷却开口更多的翼型叶片侧壁冷却。
-
公开(公告)号：USRE40658E1
公开(公告)日：2009-03-10
申请号：US11287565
申请日：2005-11-23
IPC分类号： F01D9/06
CPC分类号： F01D25/12 , F01D5/189 , F01D9/02 , F05D2260/201 , Y02T50/676
摘要： A method for assembling a turbine nozzle for a gas turbine engine facilitates improving cooling efficiency of the turbine nozzle. The method includes providing a hollow doublet including a leading airfoil and a trailing airfoil coupled by at least one platform, wherein each airfoil includes a first sidewall and a second sidewall that extend between a respective leading and trailing edge. The method also includes inserting an insert into at least one of the airfoils, wherein the insert includes a first sidewall including a first plurality of cooling openings that extending therethrough, and a second sidewall including a second plurality of cooling openings extending therethrough, and wherein the first plurality of cooling openings facilitate more cooling of the airfoil than the second plurality of cooling openings.
摘要翻译： 用于组装燃气涡轮发动机的涡轮喷嘴的方法有利于提高涡轮喷嘴的冷却效率。 该方法包括提供一个中空的双层结构，该空心双层结构包括一个由至少一个平台联接的先导翼型件和后翼型件，其中每个翼型件包括在相应的前缘和后缘之间延伸的第一侧壁和第二侧壁。 该方法还包括将插入件插入到至少一个翼型件中，其中插入件包括第一侧壁，第一侧壁包括第一多个冷却开口，第一多个冷却开口延伸穿过其中，第二侧壁包括延伸穿过其中的第二多个冷却开口， 第一多个冷却开口有助于翼型件比第二多个冷却开口更多的冷却。
-
公开(公告)号：US07147432B2
公开(公告)日：2006-12-12
申请号：US10720430
申请日：2003-11-24
CPC分类号： F01D11/08 , F01D9/04 , F01D25/12 , F05D2240/81 , F05D2260/201 , F05D2260/202 , Y02T50/676 , Y10S165/908
摘要： A turbine shroud assembly asymmetrical cooling element such as a shroud segment or a baffle includes an arcuate panel. The panel has a plurality of cooling apertures extending through the panel and an axially extending midline of the panel parallel to an axis of rotation of the arcuate panel. A symmetric portion of the cooling apertures have a symmetrical density of aperture inlets that is symmetric with respect to the axially extending midline. An asymmetric portion of the cooling apertures have an asymmetrical density of aperture inlets that is asymmetric with respect to the axially extending midline. One exemplary cooling element includes a high density area of the cooling apertures in the asymmetric portion having a higher density of aperture inlets than in the symmetric portion. A low density area of the cooling apertures in the asymmetric portion has a lower density of aperture inlets than in the symmetric portion of the cooling apertures.
摘要翻译： 涡轮机罩组件诸如护罩段或挡板的不对称冷却元件包括弓形面板。 面板具有延伸穿过面板的多个冷却孔，并且面板的轴向延伸的中线平行于弧形面板的旋转轴线。 冷却孔的对称部分具有相对于轴向延伸的中线对称的孔径入口的对称密度。 冷却孔的不对称部分具有相对于轴向延伸中线不对称的孔入口的不对称密度。 一个示例性的冷却元件包括不对称部分中的冷却孔的高密度区域，其具有比在对称部分中更高密度的孔入口。 不对称部分中的冷却孔的低密度区域具有比在冷却孔的对称部分中更小的孔入口密度。
-
公开(公告)号：US06652220B2
公开(公告)日：2003-11-25
申请号：US09998947
申请日：2001-11-15
IPC分类号： F01D906
CPC分类号： F01D25/12 , F01D5/189 , F01D9/02 , F05D2260/201 , Y02T50/676
摘要： A method for assembling a turbine nozzle for a gas turbine engine facilitates improving cooling efficiency of the turbine nozzle. The method includes providing a hollow doublet including a leading airfoil and a trailing airfoil coupled by at least one platform, wherein each airfoil includes a first sidewall and a second sidewall that extend between a respective leading and trailing edge. The method also includes inserting an insert into at least one of the airfoils, wherein the insert includes a first sidewall including a first plurality of cooling openings that extending therethrough, and a second sidewall including a second plurality of cooling openings extending therethrough, and wherein the first plurality of cooling openings facilitate more cooling of the airfoil than the second plurality of cooling openings.
-
公开(公告)号：US06602047B1
公开(公告)日：2003-08-05
申请号：US10085996
申请日：2002-02-28
IPC分类号： F01D906
CPC分类号： F01D5/187 , F01D9/04 , F05D2230/21 , F05D2240/128 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
摘要： A turbine nozzle for a gas turbine engine includes a hollow airfoil vane including a first wall, a second wall, and a plurality of pins extending therebetween. The nozzle also includes at least one row of turbulators. The first and second walls are connected at a leading edge and a trailing edge. The first wall includes a plurality of slots extending towards the trailing edge, and the row of turbulators are substantially radially-aligned and extend between the plurality of slot and the pins.
摘要翻译： 用于燃气涡轮发动机的涡轮喷嘴包括中空翼型叶片，其包括第一壁，第二壁和在其间延伸的多个销。 喷嘴还包括至少一排湍流器。 第一和第二壁连接在前缘和后缘。 第一壁包括朝向后缘延伸的多个槽，并且该排湍流器基本上径向对准并且在多个槽和销之间延伸。
-
公开(公告)号：US07762761B2
公开(公告)日：2010-07-27
申请号：US11290010
申请日：2005-11-30
申请人： Duane Busch , Andrew Charles Powis
发明人： Duane Busch , Andrew Charles Powis
IPC分类号： F01D9/00
CPC分类号： F01D25/246 , F01D9/042 , F05D2250/70 , F05D2260/94 , F05D2260/941 , Y02T50/671
摘要： A method for assembling a turbine nozzle for a gas turbine engine. The method includes providing a turbine nozzle including a plurality of airfoil vanes extending between an inner band and an outer band, wherein the outer band includes a forward hook assembly having a rail and at least one hook, providing at least one scalloped recessed area within the forward hook assembly at least one hook to facilitate reducing stresses induced to the turbine nozzle, and coupling the turbine nozzle into the gas turbine engine using the forward hook assembly such that the turbine nozzle is at least partially supported by the forward hook assembly.
摘要翻译： 一种用于组装燃气涡轮发动机的涡轮喷嘴的方法。 该方法包括提供涡轮喷嘴，该涡轮喷嘴包括在内带和外带之间延伸的多个翼型叶片，其中外带包括具有导轨和至少一个钩的前挂钩组件，该至少一个钩提供至少一个扇形凹陷区域 前向钩组件至少一个钩子，以便于减少引起涡轮喷嘴的应力，以及使用前向挂钩组件将涡轮喷嘴耦合到燃气涡轮发动机中，使得涡轮喷嘴至少部分地由前挂钩组件支撑。
-
公开(公告)号：US06503059B1
公开(公告)日：2003-01-07
申请号：US09899543
申请日：2001-07-06
申请人： Wilson Frost , Mark Edward Stegemiller , Andrew Charles Powis , Peter P. Pirolla , David John Humanchuk , Gunnar Leif Siden
发明人： Wilson Frost , Mark Edward Stegemiller , Andrew Charles Powis , Peter P. Pirolla , David John Humanchuk , Gunnar Leif Siden
IPC分类号： F01D514
CPC分类号： F01D5/141 , F05D2240/301 , Y10S416/02
摘要： The fourth-stage buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I wherein Z is a perpendicular distance from a plane normal to a radius of the turbine centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at the radially innermost aerodynamic section of the airfoil and X and Y are coordinate values defining the airfoil profile at each distance Z. The X, Y and Z values may be scaled as a function of the same constant or number to provide a scaled-up or scaled-down airfoil section for the bucket.
摘要翻译： 第四级铲斗具有基本上符合表I中以英寸表示的X，Y和Z的笛卡尔坐标值的翼型，其中Z是垂直于涡轮机中心线半径的平面的垂直距离，并且包含X和 Y值在Z轴的X，Y平面上从零开始，X和Y在翼型的径向最内空气动力学部分处开始，X和Y是定义每个距离Z处的翼面轮廓的坐标值.X，Y和Z值可以被缩放 作为相同常数或数字的函数，以提供用于铲斗的放大或缩小的翼型部分。
-
-
-
-
-
-
-
-
-
搜索结果
11 条记录 (耗时 0.034 秒)