公开(公告)号：US20130156603A1

公开(公告)日：2013-06-20

申请号：US13688892

申请日：2012-11-29

Applicant: ROLLS-ROYCE PLC

Inventor： Anthony John RAWLINSON ,  Matthew ADAMS ,  Peter Philip RAMWELL

IPC: F01D25/12

CPC classification number: F01D25/12 ,  F01D5/187 ,  F05D2250/185

Abstract: An aerofoil blade or vane for the turbine of a gas turbine engine is provided. The blade or vane includes an aerofoil portion which, in use, extends radially across a working gas annulus of the engine. A coolant inlet is formed at an end of the aerofoil portion for the entry of a cooling air flow into the portion. A corresponding coolant exhaust is formed at the trailing edge of the aerofoil portion for spent cooling air to flow from the portion. A passage within the aerofoil portion connects the inlet to the exhaust. A fence within the aerofoil portion extends radially and forwardly from a start position at the end of the aerofoil portion adjacent the trailing edge to an end position. The passage forms a loop which extends along one side of the fence, wraps around the end position, and extends along the other side of the fence.

Abstract translation: 提供了一种用于燃气涡轮发动机的涡轮机的机翼叶片或叶片。 叶片或叶片包括机翼部分，其在使用中径向延伸穿过发动机的工作气体环。 在机翼部分的端部处形成冷却剂入口，用于使冷却空气流进入该部分。 在机翼部分的后缘处形成相应的冷却剂排气，用于废冷却空气从该部分流出。 机翼部分内的通道将入口连接到排气口。 机翼部分内的围栏从靠近后缘的机翼部分的端部处的起始位置径向向前延伸到终点位置。 通道形成一个沿着围栏的一侧延伸的环，围绕终端位置包裹，并沿栅栏的另一侧延伸。

公开(公告)号：US20160097286A1

公开(公告)日：2016-04-07

申请号：US14846284

申请日：2015-09-04

Applicant: ROLLS-ROYCE PLC

Inventor： Ian TIBBOTT ,  Peter Thomas IRELAND ,  Anthony John RAWLINSON ,  Irene CRESCI

IPC: F01D5/18 ,  F01D9/06

CPC classification number: F01D5/188 ,  F01D5/189 ,  F01D9/041 ,  F01D9/065 ,  F05D2240/126 ,  F05D2240/127 ,  F05D2260/201 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/673 ,  Y02T50/676

Abstract: A gas turbine engine component, especially an aerofoil-sectioned nozzle guide vane (NGV), having at least one internal cooling chamber for passage of cooling air, the chamber including leading edge portion and one inlet portion via which cooling air may enter the chamber from feed source, wherein the component includes a partitioning element, e.g. curved or scoop-shaped partitioning plate or wall, provided in the chamber inlet portion and defining within the inlet portion a sub-chamber adjacent the leading edge portion, and wherein partitioning element is configured so the cooling air velocity in the sub-chamber is less than the cooling air velocity in the remainder of inlet portion. The reduced velocity of the cooling air in the sub-chamber adjacent the leading edge serves to increase pressure therein, thereby maintaining desired backflow pressure margin between the feed pressure of the cooling air delivered to the showerhead holes and the gas-path from the combustor.

Abstract translation: 一种燃气涡轮发动机部件，特别是翼型截面喷嘴引导叶片（NGV），其具有用于冷却空气通过的至少一个内部冷却室，所述内部冷却室包括前缘部分和一个入口部分，冷却空气可通过该入口部分从冷却空气进入室 进料源，其中所述组件包括分隔元件，例如 弯曲或铲形的分隔板或壁，设置在室入口部分中，并且在入口部分内限定与前缘部分相邻的子室，并且其中分隔元件被构造成使得子室中的冷却空气速度较小 比进口部分的剩余部分中的冷却风速快。 靠近前缘的副室中的冷却空气的减小的速度用于增加其中的压力，从而在输送到喷头孔的冷却空气的进料压力和来自燃烧器的气体路径之间保持期望的回流压力裕度。

公开(公告)号：US20140178207A1

公开(公告)日：2014-06-26

申请号：US14100784

申请日：2013-12-09

Applicant: ROLLS-ROYCE PLC

Inventor： Li HE ,  Qiang ZHANG ,  Anthony John RAWLINSON

IPC: F01D5/18 ,  F01D11/08

CPC classification number: F01D5/187 ,  F01D5/20 ,  F01D11/08 ,  F05D2250/13

Abstract: A rotor stage of a turbine has a rotational axis, a shroud and radially inward thereof a turbine blade defined partly by a pressure side wall, a suction side wall and a tip portion. The tip portion has a pressure side tip rib and a tip cavity floor defining a tip cavity. The pressure side tip rib has a width Wps, a height Hps above the tip cavity and defines a tip gap Gps with the shroud. The pressure side tip rib has a sloping side joining the tip cavity floor and having an angle αps to a radial line ZZ. The width Wps is in the range Gps to 5Gps, the height Hps is in the range 5Gps to 15Gps and the angle αps is in the range 20° to 70°.

Abstract translation: 涡轮机的转子级具有旋转轴线，护罩和径向向内的涡轮叶片，其部分地由压力侧壁，吸力侧壁和尖端部分限定。 尖端部分具有限定尖端腔的压力侧末端肋和尖端腔底。 压力侧末端肋具有宽度Wps，在尖端腔上方的高度Hps，并且与护罩限定尖端间隙Gps。 压力侧末端肋具有接合尖端空腔底板并且具有与径向线ZZ的角度αps的倾斜侧。 宽度Wps在Gps到5Gps的范围内，高度Hps在5Gps到15Gps的范围内，角度αps在20°到70°的范围内。