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1. 发明授权

EP1091089B1 Cooling air supply through bolted flange assembly 有权
标题翻译：供给冷却空气通过涡轮机转子的连接凸缘
公开(公告)号：EP1091089B1
公开(公告)日：2005-06-01
申请号：EP00307192.5
申请日：2000-08-22
申请人： GENERAL ELECTRIC COMPANY
发明人： Dziech, Aaron Michael , Reisenauer, Daniel E. , Bolt, William Zachary , Albrecht, Richard William, Jr. , Ward, Steven Douglas
IPC分类号： F01D5/08 , F01D5/06
CPC分类号： F01D5/066 , F01D5/082 , F01D5/088 , Y02T50/671 , Y02T50/676

2. 发明公开

EP1091089A3 Cooling air supply through bolted flange assembly 有权
标题翻译：供给冷却空气通过涡轮机转子的连接凸缘
公开(公告)号：EP1091089A3
公开(公告)日：2003-12-03
申请号：EP00307192.5
申请日：2000-08-22
申请人： GENERAL ELECTRIC COMPANY
发明人： Dziech, Aaron Michael , Reisenauer, Daniel E. , Bolt, William Zachary , Albrecht, Richard William, Jr. , Ward, Steven Douglas
IPC分类号： F01D5/08 , F01D5/06
CPC分类号： F01D5/066 , F01D5/082 , F01D5/088 , Y02T50/671 , Y02T50/676
摘要： A preferred embodiment of the present invention is a gas turbine engine rotor assembly (10) having axially spaced apart forward and aft disks (16, 20) circumferentially disposed about an axis (A). The forward disk (16) has an aftwardly extending annular forward arm (58) and the aft disk (20) has a forwardly extending annular aft arm (60). Forward and aft flanges (64, 68) are located at forward and aft ends (70, 72) of the forward and aft arms (58, 60) respectively. Forward and aft pluralities (76, 78) of aligned forward and aft bolt holes (80, 82) extending axially through the forward and aft flanges (64, 68) respectively. A scalloped annular ring (88) having a plurality of circumferentially spaced apart tabs (83) with spaces (84) therebetween is disposed between the flanges. A plurality of ring bolt holes (86) extend axially through the plurality of circumferentially spaced apart tabs (83) such that corresponding ones of the ring, forward, and aft bolt holes (80, 82) are axially aligned. Forward and aft pluralities (76, 78) of apertures (94, 96) extend axially through the forward and aft flanges (64, 68) and the spaces (84) are in fluid flow communication with corresponding forward and aft ones of the apertures (94). A plurality of bolts (100) are preferably used to attach the forward and aft flanges (64, 68) together and each of the bolts (100) is disposed through corresponding ones of the ring, forward, and aft bolt holes.

3. 发明公开

EP1091089A2 Cooling air supply through bolted flange assembly 有权
标题翻译： Kühlluftzufuhrdurch die Verbindungsflansche eines Turbinenrotors
公开(公告)号：EP1091089A2
公开(公告)日：2001-04-11
申请号：EP00307192.5
申请日：2000-08-22
申请人： GENERAL ELECTRIC COMPANY
发明人： Dziech, Aaron Michael , Reisenauer, Daniel E. , Bolt, William Zachary , Albrecht, Richard William, Jr. , Ward, Steven Douglas
IPC分类号： F01D5/08 , F01D5/06
CPC分类号： F01D5/066 , F01D5/082 , F01D5/088 , Y02T50/671 , Y02T50/676
摘要： A preferred embodiment of the present invention is a gas turbine engine rotor assembly (10) having axially spaced apart forward and aft disks (16, 20) circumferentially disposed about an axis (A). The forward disk (16) has an aftwardly extending annular forward arm (58) and the aft disk (20) has a forwardly extending annular aft arm (60). Forward and aft flanges (64, 68) are located at forward and aft ends (70, 72) of the forward and aft arms (58, 60) respectively. Forward and aft pluralities (76, 78) of aligned forward and aft bolt holes (80, 82) extending axially through the forward and aft flanges (64, 68) respectively. A scalloped annular ring (88) having a plurality of circumferentially spaced apart tabs (83) with spaces (84) therebetween is disposed between the flanges. A plurality of ring bolt holes (86) extend axially through the plurality of circumferentially spaced apart tabs (83) such that corresponding ones of the ring, forward, and aft bolt holes (80, 82) are axially aligned. Forward and aft pluralities (76, 78) of apertures (94, 96) extend axially through the forward and aft flanges (64, 68) and the spaces (84) are in fluid flow communication with corresponding forward and aft ones of the apertures (94). A plurality of bolts (100) are preferably used to attach the forward and aft flanges (64, 68) together and each of the bolts (100) is disposed through corresponding ones of the ring, forward, and aft bolt holes.
摘要翻译：本发明的优选实施例是一种燃气涡轮发动机转子组件（10），其具有围绕轴线（A）周向设置的轴向间隔开的前后盘片（16,20）。前盘（16）具有向后延伸的环形前臂（58），并且后盘（20）具有向前延伸的环形后臂（60）。前后翼缘（64,68）分别位于前臂和后臂（58,60）的前端和后端（70,72）。对齐的前后翼螺栓孔（80,82）分别轴向延伸穿过前凸缘和后凸缘（64,68）的前后多个（76,78）。具有多个周向间隔开的突片（83）的扇形环形环（88）在其间具有间隙（84），设置在凸缘之间。多个环形螺栓孔（86）轴向延伸穿过多个周向间隔开的突片（83），使得环形，前部和后部螺栓孔（80,82）中的对应的轴向对准。前后多孔（76,78）的孔（94,96）轴向地延伸穿过前和后凸缘（64,68），并且空间（84）与对应的前和后的孔之间流体连通 94）。多个螺栓（100）优选地用于将前后凸缘（64,68）附接在一起，并且每个螺栓（100）通过相应的环形，前部和后部螺栓孔布置。

4. 发明公开

EP0497519A1 Method and system for the disassembly of an annular combustor 失效
标题翻译： Verfahren und Vorrichtung zum Demontieren einer Ringbrennkammer。
公开(公告)号：EP0497519A1
公开(公告)日：1992-08-05
申请号：EP92300633.2
申请日：1992-01-24
申请人： GENERAL ELECTRIC COMPANY
发明人： Ward, Steven Douglas , Hansel, Harold Ray
IPC分类号： F23R3/60 , F01D25/28 , F23R3/50
CPC分类号： F23R3/60 , F01D25/285 , F23R3/50 , F23R2900/00017 , F23R2900/00019
摘要： An apparatus and method for effecting the disassembly of an annular combustor (12) for the maintenance of very large power generation gas generators such as those used in military aircraft engines, commercial aircraft engines, and smaller power generation turbines. The apparatus utilizes rollers (54) which are attachable to a lower half outer casing (16). An inversion ring (42) located radially inward from the lower half outer casing is supported by the rollers. By disconnecting a removable upper half outer casing (14), the combustor segments (24) of a first section of the combustor can be removed. Supports (58) connected to the first section of the combustor are secured by pins to a tool ring (50) which is in turn secured to the inversion ring (42) so as to create a closed path. By removing pins (50) which secure the inversion ring and lower half outer casing to supports connected to a second section of combustor segments, the combustor can be rotated so that the second section of formerly inaccessible segments can be easily removed.
摘要翻译：用于实现用于维护非常大的发电气体发生器（例如在军用飞机发动机，商用飞机发动机和较小发电涡轮机中使用的那些）的环形燃烧器（12）的拆卸的装置和方法。该装置使用可附接到下半壳体（16）的辊（54）。从下半壳体径向向内定位的反转环（42）由辊支撑。通过断开可拆卸的上半壳体（14），可以去除燃烧器的第一部分的燃烧器段（24）。连接到燃烧器的第一部分的支撑件（58）通过销固定到工具环（50），工具环（50）又固定到反转环（42），以便产生闭合路径。通过移除将反转环和下半外壳固定到与燃烧器段的第二部分连接的支撑件的销（50），可以旋转燃烧器，使得可以容易地去除以前不可接近的段的第二部分。

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