公开(公告)号：US09200535B2

公开(公告)日：2015-12-01

申请号：US13688892

申请日：2012-11-29

Applicant: ROLLS-ROYCE PLC

Inventor： Anthony John Rawlinson ,  Matthew Adams ,  Peter Philip Ramwell

IPC: F03D11/00 ,  F01D25/12 ,  F01D5/18

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：US09797261B2

公开(公告)日：2017-10-24

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 ,  F01D9/04 ,  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.