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1. 发明公开

EP1589195A1 A rotor blade containment assembly for a gas turbine engine 有权
标题翻译： Berstschutzvorrichtungfüreine Gasturbine
公开(公告)号：EP1589195A1
公开(公告)日：2005-10-26
申请号：EP05251841.2
申请日：2005-03-24
申请人： ROLLS-ROYCE PLC
发明人： Harper, Cedric Brett , Martindale, Ian Graham
IPC分类号： F01D21/04 , F01D25/24
CPC分类号： F01D21/045 , F05B2260/301 , F05D2260/30 , F05D2300/121 , F05D2300/125 , F05D2300/133 , F05D2300/211 , F05D2300/2261 , F05D2300/2283 , F05D2300/614 , F05D2300/702 , Y02T50/672
摘要： A gas turbine engine rotor blade containment assembly (38) comprising a generally cylindrical, or frustoconical, casing (40). The casing (40) having at least one member (54) and the member (54) has a first portion (53) extending radially from the casing (40) and a second portion (55) extending axially from the first portion (53) of the member (54). At least one cassette (80) being provided and one or more liner panels (74) being arranged in each cassette (80). A first end (84) of each cassette (80) being locatable on the second portion (55) of the member (54) and the first end (84) of each cassette (80) being shaped to correspond to the shape of the first and second portions (53,55) of the at least one member (54) to protect the first and second portions (53,55) of the at least one member (54). The second end (86) of each cassette (80) having at least one axially extending member (96) removably securable to the casing (40).
摘要翻译：一种燃气涡轮发动机转子叶片容纳组件（38），其包括大致圆柱形或截头圆锥形的壳体（40）。具有至少一个构件（54）和构件（54）的壳体（40）具有从壳体（40）径向延伸的第一部分（53）和从第一部分（53）轴向延伸的第二部分（55）的成员（54）。设置至少一个盒（80），并且每个盒（80）中布置有一个或多个衬板（74）。每个盒（80）的第一端（84）可定位在构件（54）的第二部分（55）上，并且每个盒（80）的第一端（84）成形为对应于第一和所述至少一个构件（54）的第二部分（53,55），以保护所述至少一个构件（54）的第一和第二部分（53,55）。每个盒（80）的第二端（86）具有可拆卸地固定到壳体（40）的至少一个轴向延伸构件（96）。

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. 发明公开

EP1087104A3 A gas turbine engine blade containment assembly 有权
标题翻译：燃气涡轮机的防爆
公开(公告)号：EP1087104A3
公开(公告)日：2003-11-12
申请号：EP00307954.8
申请日：2000-09-13
申请人： ROLLS-ROYCE PLC
发明人： Sathianathan, Sivasubramaniam Kathirgamathamby , Martindale, Ian Graham , Geary, David , Reed, Julian Mark
IPC分类号： F01D21/04
CPC分类号： F01D21/045 , Y02T50/671
摘要： A turbofan gas turbine engine (10) comprises a fan rotor (32) carrying a plurality of radially extending fan blades (34). A fan blade containment assembly (38) surrounds the fan blades (34) and the fan blade containment assembly (38) comprises a generally cylindrical, or frustoconical, metal casing (40). The casing (40) comprises an annular hook (54) positioned axially upstream of the tip (37) of the fan blade (34). The annular hook (54) extends in a radially inwardly and axially downstream direction from the metal casing (40) towards the tip (37) of the fan blade (34). The metal casing (40) has a containment portion (A) downstream of the annular hook (54) and substantially in the plane of the leading edge of the tip (37) of the fan blade (34). The containment portion (A) of the casing (40) has a greater diameter than the diameter of the casing (40) at the annular hook (54) to restrain upstream movement of a detached fan blade (34).

4. 发明公开

EP1087105A2 A gas turbine engine blade containment assembly 有权
标题翻译： BerstschutzeinrichtungfürGasturbinen
公开(公告)号：EP1087105A2
公开(公告)日：2001-03-28
申请号：EP00307955.5
申请日：2000-09-13
申请人： ROLLS-ROYCE plc
发明人： Sathinathan, Sivasubramaniam Kathirgamathamby , Martindale, Ian Graham , Lawson, Michael Rayner
IPC分类号： F01D21/04 , F01D25/24
CPC分类号： F01D25/24 , F01D21/045 , Y02T50/671
摘要： A gas turbine engine rotor blade containment assembly (38) comprising a generally cylindrical, or frustoconical, first metal casing (40) and a plurality of generally cylindrical, or frustoconical, axially spaced second metal casings (54,56&58). The second metal casings (54,56,58) surround and abut the first metal casing (40). The first metal casing (40) is relatively hard and tough to contain a fan blade (34). The second metal casing (54,56,58) are relatively soft and lightweight to stiffen the first metal casing (40) in fan blade containment regions (A, B&C). The second metal casings (54,56,58) are arranged coaxially with the first metal casing (40). One of the second metal casings (56) is in a plane (Y) containing the fan blades (34) of the gas turbine engine (10). The first metal casing (40) comprises steel and the second metal casings (54,56,58) comprise aluminium. The fan blade containment assembly (38) is lighter for large diameter turbofan gas turbine engine (10).
摘要翻译：一种燃气涡轮发动机转子叶片容纳组件（38），其包括大致圆柱形或截头圆锥形的第一金属壳体（40）和多个大致圆柱形或截头圆锥形的轴向隔开的第二金属壳体（54,56和58）。第二金属外壳（54,56,58）围绕并邻接第一金属外壳（40）。第一金属壳体（40）相对硬且难以容纳风扇叶片（34）。第二金属外壳（54,56,58）相对较软和轻便，以加强风扇叶片容纳区域（A，B和C）中的第一金属外壳（40）。第二金属壳体（54,56,58）与第一金属壳体（40）同轴布置。第二金属壳体（56）中的一个位于包含燃气涡轮发动机（10）的风扇叶片（34）的平面（Y）中。第一金属外壳（40）包括钢，第二金属外壳（54,56,58）包括铝。对于大直径涡轮风扇燃气涡轮发动机（10），风扇叶片容纳组件（38）较轻。

5. 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

6. 发明授权

EP1087104B1 A gas turbine engine blade containment assembly 有权
标题翻译：容器装置，用于燃气涡轮机转子叶片
公开(公告)号：EP1087104B1
公开(公告)日：2005-03-16
申请号：EP00307954.8
申请日：2000-09-13
申请人： ROLLS-ROYCE PLC
发明人： Sathianathan, Sivasubramaniam Kathirgamathamby , Martindale, Ian Graham , Geary, David , Reed, Julian Mark
IPC分类号： F01D21/04
CPC分类号： F01D21/045 , Y02T50/671

7. 发明公开

EP1245791A3 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：EP1245791A3
公开(公告)日：2004-10-13
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
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) and a downstream portion (60). 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) and the downstream portion (60). The downstream portion (60) has impact protection means (64B) located on its inner surface (62) to protect the downstream portion (60) of the containment casing (40). The impact protection means (64) comprises a plurality of radially inwardly and circumferentially extending ribs (80) on the inner surface (62) of the downstream portion (60) to act as spacer between an inner portion of a detached fan blade (34) and the downstream portion (60).

8. 发明授权

EP1589195B1 A rotor blade containment assembly for a gas turbine engine 有权
标题翻译：用于燃气轮机突发保护
公开(公告)号：EP1589195B1
公开(公告)日：2008-01-09
申请号：EP05251841.2
申请日：2005-03-24
申请人： ROLLS-ROYCE PLC
发明人： Harper, Cedric Brett , Martindale, Ian Graham
IPC分类号： F01D21/04 , F01D25/24
CPC分类号： F01D21/045 , F05B2260/301 , F05D2260/30 , F05D2300/121 , F05D2300/125 , F05D2300/133 , F05D2300/211 , F05D2300/2261 , F05D2300/2283 , F05D2300/614 , F05D2300/702 , Y02T50/672

9. 发明公开

EP1860283A2 Fan casing for a gas turbine engine 审中-公开
标题翻译：樊舒use use ines。。。。。。。。。。。。。
公开(公告)号：EP1860283A2
公开(公告)日：2007-11-28
申请号：EP07251769.1
申请日：2007-04-26
申请人： Rolls-Royce plc
发明人： Harper, Cedric Brett , Martindale, Ian Graham
IPC分类号： F01D21/04
CPC分类号： F01D21/045 , F02C7/05 , F02K3/06 , F05D2240/90 , F05D2260/30 , Y02T50/671
摘要： An annular fan casing of a gas turbine engine includes a plurality of fan track liner panels, secured to the radially inner surface of the fan casing. The panels are secured using mechanical fasteners, which are secured into non-load-bearing regions of the fan casing so as not to compromise the load-carrying or containment functions of the fan casing.
摘要翻译：燃气涡轮发动机的环形风扇壳体包括固定到风扇壳体的径向内表面的多个风扇履带衬板。面板使用机械紧固件固定，其被固定到风扇壳体的非承载区域中，以便不损害风扇壳体的承载或容纳功能。

10. 发明公开

EP1087105A3 A gas turbine engine blade containment assembly 有权
标题翻译：燃气涡轮机的防爆
公开(公告)号：EP1087105A3
公开(公告)日：2004-01-28
申请号：EP00307955.5
申请日：2000-09-13
申请人： ROLLS-ROYCE plc
发明人： Sathinathan, Sivasubramaniam Kathirgamathamby , Martindale, Ian Graham , Lawson, Michael Rayner
IPC分类号： F01D25/24 , F01D21/04
CPC分类号： F01D25/24 , F01D21/045 , Y02T50/671
摘要： A gas turbine engine rotor blade containment assembly (38) comprising a generally cylindrical, or frustoconical, first metal casing (40) and a plurality of generally cylindrical, or frustoconical, axially spaced second metal casings (54,56&58). The second metal casings (54,56,58) surround and abut the first metal casing (40). The first metal casing (40) is relatively hard and tough to contain a fan blade (34). The second metal casing (54,56,58) are relatively soft and lightweight to stiffen the first metal casing (40) in fan blade containment regions (A, B&C). The second metal casings (54,56,58) are arranged coaxially with the first metal casing (40). One of the second metal casings (56) is in a plane (Y) containing the fan blades (34) of the gas turbine engine (10). The first metal casing (40) comprises steel and the second metal casings (54,56,58) comprise aluminium. The fan blade containment assembly (38) is lighter for large diameter turbofan gas turbine engine (10).

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