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1. 发明授权

EP2479382B1 Rotor blade 有权
标题翻译：转子叶片
公开(公告)号：EP2479382B1
公开(公告)日：2013-12-25
申请号：EP12150445.0
申请日：2012-01-09
申请人： Rolls-Royce plc
发明人： Cheong, Brian , Diamond, Stephen , Sehra, Gurmukh
IPC分类号： F01D5/20
CPC分类号： F01D5/20
摘要： A rotor blade has a radially extending aerofoil body which provides an aerofoil surface having pressure and suction sides extending between a leading edge and a trailing edge of the aerofoil body. The rotor blade further has squealer tip at the radially outward end of the aerofoil body. The squealer tip comprises a peripheral wall surrounding a cavity which is open at the radially outward end of the blade and at the trailing edge of the aerofoil body. The peripheral wall has at least one first region which extends radially from the aerofoil surface and which has a first outer surface which is a continuation of the aerofoil surface. The peripheral wall further has, along at least part of at least one of the pressure side and the suction side, at least one second region which is inclined outwardly of the cavity with respect to the radial direction of the blade and which has a second outer surface which extends obliquely outwardly of the blade from the aerofoil surface. A radially outer portion of the second outer surface turns towards the radial direction to truncate the outward extension of the second outer surface.

2. 发明公开

EP2378074A1 Rotor blade and corresponding gas turbine engine 审中-公开
标题翻译：转子叶片和相应的燃气涡轮发动机
公开(公告)号：EP2378074A1
公开(公告)日：2011-10-19
申请号：EP11159160.8
申请日：2011-03-22
申请人： Rolls-Royce plc
发明人： Diamond, Stephen , Helvaci, Caner , Townes, Roderick , Tibbott, Ian , Jackson, Dougal
IPC分类号： F01D5/20
CPC分类号： F01D5/20
摘要： A rotor blade 40 for a gas turbine engine has an aerofoil portion 42 from a root 48 to a tip 54. In use, combustion gas may leak over the tip 54 from the pressure face 52 to the suction face 50. A gutter 62 extends across the tip 54 to entrain any over tip leakage gap. The floor of the gutter defines an increased depth portion 72 at the exit end of the gutter 62.
摘要翻译：用于燃气涡轮发动机的转子叶片40具有从根部48到尖端54的翼型部分42.在使用中，燃烧气体可以从尖端54上从压力面52泄漏到负压面50上。沟槽62横跨尖端54夹带任何超过尖端泄漏间隙。沟槽的底部在沟槽62的出口端处限定增加的深度部分72。

3. 发明公开

EP2378076A1 Rotor blade and corresponding gas turbine engine 无效转让
标题翻译： Laufschaufel undzugehörigesGasturbinenkraftwerk
公开(公告)号：EP2378076A1
公开(公告)日：2011-10-19
申请号：EP11159162.4
申请日：2011-03-22
申请人： Rolls-Royce plc
发明人： Diamond, Stephen , Helvaci, Caner , Townes, Roderick
IPC分类号： F01D5/20
CPC分类号： F01D5/20 , F16L19/0225
摘要： A rotor blade 52 for a gas turbine engine has an aerofoil portion 38 and a tip region 40. The tip region 40 is at the radially outermost end of the blade 52. The radially outermost surface 54 carries abrasive material (not shown) to interact with an abradable surface. The tip 40 has a recess 60 in which cooling air outlets are formed. The recess 60 is open in a circumferential direction 64. This allows cooling air outlets 62 to be formed without interference from the abrasive material, and inhibits any tendency for abrasion debris to collect in the recess 60 and interfere with the flow of cooling air.
摘要翻译：用于燃气涡轮发动机的转子叶片52具有机翼部分38和尖端区域40.尖端区域40位于叶片52的径向最外端。径向最外表面54承载磨料（未示出）以与可磨损的表面。尖端40具有形成有冷却空气出口的凹部60。凹部60沿圆周方向64打开。这允许冷却空气出口62形成而不受磨料的干扰，并且阻止磨损碎屑收集在凹部60中并且干扰冷却空气流动的任何倾向。

4. 发明公开

EP2378075A1 Rotor blade and corresponding gas turbine engine 审中-公开
标题翻译：转子叶片和相应的燃气涡轮发动机
公开(公告)号：EP2378075A1
公开(公告)日：2011-10-19
申请号：EP11159161.6
申请日：2011-03-22
申请人： Rolls-Royce plc
发明人： Diamond, Stephen , Helvaci, Caner , Townes, Roderick , Tibbott, Ian , Jackson, Dougal
IPC分类号： F01D5/20
CPC分类号： F01D5/20
摘要： A turbine blade (40) for a gas turbine engine has an aerofoil portion (42) extending from a root (48) to a tip (54). The tip (54) carries winglets (56, 58). A gutter (62) extends across the tip (54) to entrain gas leaking around the tip (54) (over tip leakage). The aerofoil portion (42) has a mean camber line and the gutter (62) has a centre line. In the examples described, the conditions that (a) the mean camber line and the centre line coincide at the exit when viewed from the tip towards the root, and (b) the mean camber line and the centre line are parallel at the exit when viewed as aforesaid, are not both fulfilled.
摘要翻译：用于燃气涡轮发动机的涡轮叶片（40）具有从根部（48）延伸至尖端（54）的翼型部分（42）。尖端（54）带有小翼（56,58）。沟槽（62）延伸穿过尖端（54）以夹带围绕尖端（54）泄漏的气体（超过尖端泄漏）。翼型部分（42）具有平均弧线，并且檐槽（62）具有中心线。在所描述的例子中，（a）当从尖端朝向根部观察时，平均弧线和中心线在出口处重合的条件和（b）平均弧线和中心线在出口处平行如前所述，都没有达到。

5. 发明公开

EP2479382A1 Rotor blade 有权
标题翻译：转子叶片
公开(公告)号：EP2479382A1
公开(公告)日：2012-07-25
申请号：EP12150445.0
申请日：2012-01-09
申请人： Rolls-Royce plc
发明人： Cheong, Brian , Diamond, Stephen , Sehra, Gurmukh
IPC分类号： F01D5/20
CPC分类号： F01D5/20
摘要： A rotor blade has a radially extending aerofoil body which provides an aerofoil surface having pressure and suction sides extending between a leading edge and a trailing edge of the aerofoil body. The rotor blade further has squealer tip at the radially outward end of the aerofoil body. The squealer tip comprises a peripheral wall surrounding a cavity which is open at the radially outward end of the blade and at the trailing edge of the aerofoil body. The peripheral wall has at least one first region which extends radially from the aerofoil surface and which has a first outer surface which is a continuation of the aerofoil surface. The peripheral wall further has, along at least part of at least one of the pressure side and the suction side, at least one second region which is inclined outwardly of the cavity with respect to the radial direction of the blade and which has a second outer surface which extends obliquely outwardly of the blade from the aerofoil surface. A radially outer portion of the second outer surface turns towards the radial direction to truncate the outward extension of the second outer surface.
摘要翻译：转子叶片具有径向延伸的翼型体，该翼型体提供翼型表面，该翼型表面具有在翼型体的前缘和后缘之间延伸的压力侧和吸力侧。转子叶片在翼型体的径向外端还具有凹槽尖端。凹槽顶端包括围绕空腔的周壁，该空腔在叶片的径向外端处和机翼体的后缘处开口。周壁具有至少一个第一区域，该第一区域从翼型表面径向延伸并且具有作为翼型表面的延续部分的第一外表面。所述周壁沿着所述压力侧和所述吸力侧中的至少一个的至少一部分还具有至少一个第二区域，所述至少一个第二区域相对于所述叶片的径向向所述空腔的外部倾斜并且具有第二外部表面从叶片表面向叶片外倾斜地延伸。第二外表面的径向外部部分朝向径向方向转向以截断第二外表面的向外延伸部。

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