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1. 发明公开

EP2286983A1 Electrical conductor path 有权
标题翻译： einemfaserverstärkten的Elektrischer Leiter Verbundstruktur sowie前身dafür
公开(公告)号：EP2286983A1
公开(公告)日：2011-02-23
申请号：EP10172116.5
申请日：2010-08-06
申请人： Rolls-Royce plc
发明人： Roberts, David Vaughan , McMillan, Alison Jane , Booth, Stephen John
IPC分类号： B29C70/88 , F01D5/28 , F01D17/02
CPC分类号： F01D25/24 , B29C70/882 , B29D99/0025 , B29L2031/08 , B29L2031/7504 , F01D5/282 , F01D17/02 , F05D2300/507 , Y02T50/672 , Y02T50/673
摘要： A component, for example an aerofoil vane or other gas path structure in a gas turbine machine such as a gas turbine engine, in which an insulated electrical conductor path (2) is embedded structurally integrally, and in which electromagnetic shielding (1, 2, 20, 22), for the embedded electrical conductor path is provided structurally integrally.
摘要翻译：在绝缘电导体路径（2）被结构地一体地嵌入的燃气轮机中，例如燃气轮机的机翼例如机翼叶片或其他气路结构，其中电磁屏蔽（1,2， 20,22），嵌入式电导体路径在结构上一体地提供。

2. 发明公开

EP1277919A1 Joint arrangement 有权
标题翻译：联合安排
公开(公告)号：EP1277919A1
公开(公告)日：2003-01-22
申请号：EP02254742.6
申请日：2002-07-05
申请人： ROLLS-ROYCE PLC
发明人： Sathianathan, Sivasubramaniam K. , Farrington, Peter Edward , Martindale, Ian Graham , Mclachlan, Caroline , Booth, Stephen John , Auterson, Duncan , Yazdani, David Sherier
IPC分类号： F01D25/14 , F01D25/24 , F01D9/04 , F02K1/80 , F16L23/16 , F16L39/00 , F16B5/02
CPC分类号： F01D21/045 , F01D25/24 , F01D25/243 , F02C7/04 , F16B5/02 , Y02T50/671 , Y10T403/32861 , Y10T403/32885
摘要： A joint assembly 80 for limiting an extension of the joint 80 in the direction of a load path derived from an impact comprising a first member 40 having a portion 82 and a second member 50 having a portion 84, the portions 82, 84 overlapping one another and arranged generally parallel to one another and secured together via securing means 78 disposed through corresponding holes 92, 94 defined therein. One of the overlapping portions 82, 84 further defines, sequentially in the direction of extension, a shear neck 100, a pocket 10 and a catcher portion 104. In the event of a worst case impact load the securing means 78 shears through the shear neck 100 and the pocket 106 and is arrested by the catcher portion, thereby the extension of the joint assembly 80 is limited and the joint assembly 80 remains integral.
摘要翻译：用于限制接头80在由冲击产生的负载路径的方向上的延伸的接头组件80包括具有部分82的第一部件40和具有部分84的第二部件50，部分82,84彼此重叠并且大致彼此平行地布置并且通过固定装置78固定在一起，固定装置78穿过限定在其中的相应孔92,94布置。重叠部分82,84中的一个进一步在延伸方向上依次限定剪切颈部100，袋10和捕捉部分104.在最坏情况下的冲击载荷的情况下，固定装置78剪切穿过剪切颈部 100和袋106并被捕集器部分阻止，由此限制接头组件80的延伸并且接头组件80保持一体。

3. 发明授权

EP1798378B1 A mounting arrangement of a gas turbine vane 失效
标题翻译：燃气涡轮机叶片的结构安排
公开(公告)号：EP1798378B1
公开(公告)日：2010-06-09
申请号：EP05257826.7
申请日：2005-12-19
申请人： ROLLS-ROYCE PLC
发明人： Booth, Stephen John , McMillan, Alison Jane
IPC分类号： F01D9/04
CPC分类号： F01D25/246 , F05D2230/642 , F05D2300/501

4. 发明公开

EP1143112A1 A gas turbine engine blade containment assembly 有权
标题翻译： Berstschutzeinrichtungfüreine Gasturbine
公开(公告)号：EP1143112A1
公开(公告)日：2001-10-10
申请号：EP01302205.8
申请日：2001-03-09
申请人： ROLLS-ROYCE plc
发明人： Booth, Stephen John
IPC分类号： F01D21/04
CPC分类号： F01D21/045 , Y02T50/671
摘要： A gas turbine engine fan blade containment assembly (38) comprising a generally cylindrical, or frustoconical, metal casing (40) has an upstream portion (56), a blade containment portion (54) and a transition portion (58). The upstream portion (56) has a flange (52) connecting the metal containment casing (40) to an axially adjacent casing (). The upstream portion (56) of the casing (40) has a greater diameter (D 1 ) than the diameter (D 2 ) of the blade containment portion (54) and the blade containment portion (54) has a greater thickness (T 2 ) than the thickness (T 1 ) of the upstream portion (54). The transition portion (58) connects the blade containment portion (54) and the upstream portion (56) to transmit loads from the blade containment portion (54) to the upstream flange (52). The transition portion (58) has a smoothly curved increase in diameter between the blade containment portion (54) and the upstream portion (56) whereby the transition portion (58) is allowed to flex to reduce impact loads transmitted to the upstream flange (52).
摘要翻译：包括大致圆柱形或截头圆锥形的金属壳体（40）的燃气涡轮发动机风扇叶片容纳组件（38）具有上游部分（56），叶片容纳部分（54）和过渡部分（58）。上游部分（56）具有将金属容纳壳体（40）连接到轴向相邻的壳体（）上的凸缘（52）。壳体（40）的上游部分（56）具有比叶片容纳部分（54）的直径（D2）更大的直径（D1），并且叶片容纳部分（54）的厚度（T2）比上游部分（54）的厚度（T1）。过渡部分（58）连接叶片容纳部分（54）和上游部分（56），以将负载从叶片容纳部分（54）传递到上游凸缘（52）。过渡部分（58）在叶片容纳部分（54）和上游部分（56）之间具有平滑弯曲的直径增加，从而允许过渡部分（58）弯曲以减少传递到上游凸缘（52）的冲击载荷）。

5. 发明公开

EP1726788A3 A rotor blade containment assembly for a gas turbine engine 有权
标题翻译：遏制了一种用于燃气涡轮发动机的转子叶片
公开(公告)号：EP1726788A3
公开(公告)日：2010-10-13
申请号：EP06252225.5
申请日：2006-04-26
申请人： Rolls-Royce plc
发明人： Beckford, Peter Rowland , Booth, Stephen John
IPC分类号： F01D21/04 , F01D25/24 , F02C7/24 , F02K1/82
CPC分类号： F01D25/24 , F01D21/045
摘要： A fan blade containment assembly (38) for a turbofan gas turbine engine (10) comprises a cylindrical, or frustoconical, casing (40) arranged to surround an arrangement of fan blades (26). At least one hollow tubular member (66) is arranged radially within and secured to the casing (40) and the at least one hollow tubular member (66) contains a filler material (68). The at least one hollow tubular member (66) extends circumferentially. The hollow tubular member (66) is helical and the axial spacing between the adjacent turns of the tubular member (66) varies and the density of the filler material (68) varies in order to match the severity of the impact expected at each axial location along the casing 40 of the fan blade containment assembly (38).

6. 发明授权

EP1245794B1 A gas turbine engine blade containment assembly 有权
标题翻译： Berstschutzvorrichtung
公开(公告)号：EP1245794B1
公开(公告)日：2008-08-13
申请号：EP02251829.4
申请日：2002-03-14
申请人： ROLLS-ROYCE PLC
发明人： Sathianathan, Sivasubramaniam Kathirgamathamby , Booth, Stephen John
IPC分类号： F01D21/04 , F01D25/24 , F01D9/04 , F01D9/02 , F02C7/24 , F02K1/82
CPC分类号： F01D21/045 , F01D25/24 , F02C7/24 , F05D2250/283

7. 发明公开

EP1245794A3 A gas turbine engine blade containment assembly 有权
标题翻译：突发保护
公开(公告)号：EP1245794A3
公开(公告)日：2004-10-06
申请号：EP02251829.4
申请日：2002-03-14
申请人： ROLLS-ROYCE plc
发明人： Sathianathan, Sivasubramaniam Kathirgamathamby , Booth, Stephen John
IPC分类号： F01D21/04 , F01D25/24 , F01D9/04 , F01D9/02 , F02C7/24 , F02K1/82
CPC分类号： F01D21/045 , F01D25/24 , F02C7/24 , F05D2250/283
摘要： A gas turbine engine fan blade containment assembly (38) comprising a generally cylindrical, or frustoconical, metal casing (40) has an upstream portion (56), a transition portion (58) and a blade containment portion (54). The upstream portion (56) has a flange (42) connecting the metal casing (40) to a flange (48) on axially adjacent casing (46). The blade containment portion (54) has a greater thickness (T 2 ) than the thickness (T 1 ) of the upstream portion (54). The transition portion (58) connects the blade containment portion (54) and the upstream portion (56) to transmit loads from the blade containment portion (54) to the flange (42) on the upstream portion (56). The ratio of the thickness (T 4 ) of the flange (42) on the upstream portion (56) to the thickness (T 1 ) of the upstream portion (56) is between 3 to 1 and 6 to 1. The flange (42) on the upstream portion (56) is radially scalloped (41) between adjacent fasteners (49,51) and the upstream portion (54) is relatively thin such that the flange (42) and upstream portion (56) are allowed to deform to reduce impact loads transmitted to the flange (48) on the casing (46).

8. 发明授权

EP1245791B1 A gas turbine engine blade containment assembly 有权
标题翻译：用于燃气轮机突发保护
公开(公告)号：EP1245791B1
公开(公告)日：2012-08-22
申请号：EP02251830.2
申请日：2002-03-14
申请人： ROLLS-ROYCE PLC
发明人： Sathianathan, Sivasubramaniam Kathirgamathamby , Booth, Stephen John , Martindale, Ian Graham
IPC分类号： F01D21/04 , F01D25/24 , F02C7/24 , F02K1/82
CPC分类号： F01D21/045

9. 发明授权

EP1726788B1 A rotor blade containment assembly for a gas turbine engine 有权
标题翻译：遏制了一种用于燃气涡轮发动机的转子叶片
公开(公告)号：EP1726788B1
公开(公告)日：2011-10-12
申请号：EP06252225.5
申请日：2006-04-26
申请人： Rolls-Royce plc
发明人： Beckford, Peter Rowland , Booth, Stephen John
IPC分类号： F01D21/04 , F01D25/24 , F02C7/24 , F02K1/82
CPC分类号： F01D25/24 , F01D21/045

10. 发明公开

EP1798378A1 A mounting arrangement of a gas turbine vane 失效
标题翻译： Aufbauanordnung einer Gasturbinenleitschaufel
公开(公告)号：EP1798378A1
公开(公告)日：2007-06-20
申请号：EP05257826.7
申请日：2005-12-19
申请人： ROLLS-ROYCE PLC
发明人： Booth, Stephen John , McMillan, Alison Jane
IPC分类号： F01D9/04
CPC分类号： F01D25/246 , F05D2230/642 , F05D2300/501
摘要： Appropriate location of components such as vanes (1, 21, 31, 41, 51, 61, 71, 81, 91) in gas turbine engines is important. These components are located between tangs (7, 27, 37, 47, 57, 67, 87, 97) held in interference engagement. There are four relatively rigid mounting points constituted by the tangs (7, 27, 37, 47, 57, 67, 87, 97) engaging respective opposed slots (8) in a casing (3) or a mounting ring (2). Only three point limitation with respect to displacement and rotation is adequate so provision of a fourth locator causes unnecessary constraint. A relatively resilient or compliant locator (37, 47, 57, 67, 87, 97) means it is possible to reduce the amount of constraint upon the component mounting whilst the other locators (7, 27) are adequate for positioning of the component (1, 21, 31, 41, 51, 61, 71, 81, 91).
摘要翻译：在燃气涡轮发动机中的诸如叶片（1,21,31,41,51,61,71,81,91）的部件的适当位置是重要的。这些部件位于保持干涉接合的柄脚（7,27,37,47,57,67,87,97）之间。由在壳体（3）或安装环（2）中与相应的相对的槽（8）接合的柄脚（7,27,37,47,57,67,87,97）构成的四个相对刚性的安装点。相对于位移和旋转只有三点限制是足够的，所以第四定位器的提供引起不必要的约束。相对有弹性或顺从的定位器（37,47,57,67,87,97）意味着可以减少对部件安装的约束量，而其他定位器（7,27）足以用于定位部件（ 1，21，31，41，51，61，71，81，91）。

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