专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

2. 发明公开

EP3088690A1 FULL HOOP BLADE TRACK WITH FLANGED SEGMENTS 有权转让
标题翻译： VOLLRING-SCHAUFELSPUR MIT GEFLANSCHTEN SEGMENTEN
公开(公告)号：EP3088690A1
公开(公告)日：2016-11-02
申请号：EP16165823.2
申请日：2016-04-18
申请人： Rolls-Royce Corporation , Rolls-Royce North American Technologies, Inc. , Rolls-Royce plc , Rolls-Royce High Temperature Composites, Inc.
发明人： Vetters, Daniel , Sippel, Aaron , Thomas, David , Eifert, Andrew , Davis, Paul , Jones, Simon , Hillier, Steven , Broadhead, Peter , Doyle, Joseph , Jacquinto, Michael , Thibault, Wesley , Shi, Jun , Townes, Roderick
IPC分类号： F01D25/24
摘要： A blade track assembly is disclosed. The blade track assembly comprises a plurality of ceramic matrix composite blade track segments (33, 34, 35) arranged circumferentially adjacent to one another around a central axis. Each of the blade track segments includes an arcuate runner (33R, 34R, 35R) extending in a circumferential direction around a portion of the central axis and is coupled to circumferentially adjacent blade track segments (33, 34, 35).
摘要翻译：公开了一种刀片轨道组件。刀片轨道组件包括围绕中心轴线彼此周向相邻布置的多个陶瓷基体复合刀片轨道段（33,34,35）。每个叶片轨道段包括在围绕中心轴线的一部分的圆周方向上延伸并连接到周向相邻的叶片轨道段（33,34,35）的弓形流道（33R，34R，35R）。

3. 发明公开

EP3816400A1 TURBINE VANE ASSEMBLY AND CORRESPONDING METHOD 有权
公开(公告)号：EP3816400A1
公开(公告)日：2021-05-05
申请号：EP20202605.0
申请日：2020-10-19
申请人： Rolls-Royce plc
发明人： Townes, Roderick , Holt, Andrew , Whittle, Michael
IPC分类号： F01D5/18 , F01D9/06
摘要： A turbine vane assembly adapted for use with a gas turbine engine includes an airfoil and a spar. The airfoil is formed to define a cavity that extends into the airfoil. The spar is located in the cavity to define a cooling passage that extends around the spar between the spar and the airfoil. The turbine vane assembly includes cooling features to aid heat transfer of the turbine vane assembly during operation in the gas turbine engine.

4. 发明授权

EP2258925B1 Cooling arrangements 有权转让
公开(公告)号：EP2258925B1
公开(公告)日：2019-01-23
申请号：EP10163682.7
申请日：2010-05-24
申请人： Rolls-Royce plc
发明人： Townes, Roderick , Tibbott, Ian , Dane, Edwin , Helvaci, Caner
IPC分类号： F01D5/18

5. 发明公开

EP3168420A1 SHROUDED TURBINE BLADE 无效转让
标题翻译：护套涡轮叶片
公开(公告)号：EP3168420A1
公开(公告)日：2017-05-17
申请号：EP16194116.6
申请日：2016-10-17
申请人： Rolls-Royce plc
发明人： Townes, Roderick
IPC分类号： F01D5/18 , F01D5/22 , F01D11/08
CPC分类号： F01D5/147 , F01D5/18 , F01D5/187 , F01D5/225 , F01D11/08 , F01D25/32 , F05D2220/32 , F05D2240/11 , F05D2240/307 , F05D2240/55 , F05D2240/81 , F05D2260/20
摘要： A shrouded turbine blade comprising a blade body (21) having an operationally upstream face, an operationally downstream face, a root end and a tip end and a shroud segment provided at the tip end, the blade having an inlet in the root end and a cooling passage (26) passing from the inlet to the tip end, the shroud segment comprising an arcuate platform (22) and a seal fin (25) arranged towards an operationally upstream end of the shroud platform (22) and extending away from the blade body (21) and circumferentially across the shroud platform (22), a fin cooling passage (27,23) in fluid communication with the tip end of the blade cooling passage (26), the fin cooling passage (27,23) having at least one outlet (20) on an operationally downstream facing side of the fin (25), and a flow discourager (24) arranged towards an operationally downstream end of the shroud platform (22).
摘要翻译：一种罩式涡轮机叶片，其包括具有操作上游面，操作下游面，根部端和顶端的叶片主体（21）以及设置在顶端的护罩区段，所述叶片在根部端具有入口和冷却通道（26）从所述入口通到所述末端，所述护罩段包括弓形平台（22）和朝向所述护罩平台（22）的操作上游端布置的密封翅片（25）并且远离所述叶片（21）并沿圆周方向跨越所述护罩平台（22），与所述叶片冷却通道（26）的末端流体连通的鳍片冷却通道（27,23），所述鳍片冷却通道（27,23）具有在位于翅片（25）的面向操作下游侧的至少一个出口（20）以及朝向护罩平台（22）的操作下游端布置的流动阻挡器（24）。

6. 发明公开

EP2258925A2 Cooling arrangements 有权转让
标题翻译：冷却装置
公开(公告)号：EP2258925A2
公开(公告)日：2010-12-08
申请号：EP10163682.7
申请日：2010-05-24
申请人： Rolls-Royce plc
发明人： Townes, Roderick , Tibbott, Ian , Dane, Edwin , Helvaci, Caner
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2250/11 , F05D2250/70 , F05D2260/2212 , F05D2260/22141
摘要： The invention discloses an aerofoil (1) of a gas turbine engine having a rotation axis, the aerofoil comprises an internal passage (22) for a cooling fluid, the passage is partly formed by first and second opposing walls (27,26) wherein the first wall (27) comprises at least one aperture (28) and the second wall (26) comprises angled wall portions (26a,26b) forming a tip region (26t) adjacent the first wall, the passage also comprises ribs (23,24,33,34) which together with the wall portions (26a,26b) create at least two vortices (25a,25b) in the coolant fluid adjacent the aperture to increase the dynamic head of cooling fluid through the aperture.

7. 发明公开

EP3608511A1 GAS TURBINE ENGINE WITH CERAMIC MATRIX COMPOSITE TURBINE COMPONENTS 有权转让
公开(公告)号：EP3608511A1
公开(公告)日：2020-02-12
申请号：EP19189309.8
申请日：2019-07-31
申请人： Rolls-Royce plc
发明人： Townes, Roderick , Dunning, Pascal , Whittle, Michael
IPC分类号： F01D5/28 , F01D15/12 , F01D25/12 , F02C3/107 , F02K3/06
摘要： A gas turbine engine (10) for an aircraft with an engine core (11) comprising a first turbine (19), a first compressor (14), and a first core shaft (26) connecting the first turbine to the first compressor, a second turbine (17), a combustor, a second compressor (15), and a second core shaft (27) connecting the second turbine to the second compressor, the second turbine, second compressor, and second core shaft being arranged to rotate at a higher rotational speed than the first core shaft, the gas turbine engine further comprising a fan (23) comprising a plurality of fan blades and a gearbox (30) that receives an input from the first core shaft (26) and outputs drive to the fan so as to drive the fan at a lower rotational speed than the first core shaft, wherein part (C) of the flow (A) that enters the engine core bypasses the combustor and is used as turbine cooling flow to cool the turbine, a cooling flow requirement is defined as the ratio of the mass flow rate of the turbine cooling flow (C) to the mass flow rate of the flow entering the engine core (A) at cruise conditions,a turbine entry temperature is defined as the temperature (K) at the inlet to the most axially upstream turbine rotor in the gas turbine engine at a maximum power condition of the gas turbine engine and the cooling efficiency ratio, defined as the ratio between the turbine entry temperature and the cooling flow requirement, is in the range of from 8000 to 20000 K.

8. 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。

9. 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。

10. 发明公开

EP3730738A1 TURBINE ASSEMBLY FOR A GAS TURBINE ENGINE WITH CERAMIC MATRIX COMPOSITE VANE 有权
公开(公告)号：EP3730738A1
公开(公告)日：2020-10-28
申请号：EP20165662.6
申请日：2020-03-25
申请人： Rolls-Royce plc
发明人： Razzell, Anthony , Shepherd, David , Townes, Roderick , Whittle, Michael , Forbes, Duncan
IPC分类号： F01D5/14 , F01D5/28 , F01D9/04 , F01D25/00
摘要： A turbine assembly (18) adapted for use in a gas turbine engine (10). The turbine assembly (18) includes a turbine vane (44) comprising ceramic matrix composite materials configured for use in high temperature environments. The turbine assembly (18) further includes a vane-stage support (26) for holding the turbine vane (44) and other components in place relative to a turbine case (20).

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式