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。

公开(公告)号：US20170091354A1

公开(公告)日：2017-03-30

申请号：US15268359

申请日：2016-09-16

Applicant: ROLLS-ROYCE plc

Inventor： Junsok YI ,  Li HE ,  Paolo ADAMI

IPC: G06F17/50

CPC classification number: G06F17/5009 ,  G06F17/5018 ,  G06F2217/16

Abstract: A computer-based method of simulating rotor-stator unsteady turbulent flow interaction in turbomachinery, which includes performing CFD ensemble-averaged flow field simulation over the coarse mesh and performing CFD large eddy simulations over the fine meshes, the ensemble-averaged and large eddy simulations being coupled to each other, and the large eddy simulations of the regions of the selected blade passages being used to derive unsteady turbulence stress terms in the ensemble-averaged simulation for corresponding regions of the blade passages of the first and second rows without fine meshes.

公开(公告)号：US20140245741A1

公开(公告)日：2014-09-04

申请号：US14192363

申请日：2014-02-27

Applicant: ROLLS-ROYCE PLC

Inventor： Li HE ,  Amir RAHIM ,  Bidur KHANAL ,  Eduardo ROMERO

IPC: F01D9/04

CPC classification number: F01D9/041 ,  F01D5/141 ,  F01D5/145 ,  F01D5/146 ,  F05D2250/38 ,  F05D2250/73

Abstract: In a gas turbine engine, each vane has pressure and suction surfaces extending radially from an inner to outer endwall of an annular working gas engine passage, and extending axially from a leading to a trailing edge of the vane. Each vane has transverse sections providing respective aerofoil sections. Neighbouring vanes are arranged in unequally-shaped pairs in which either: (i) the first vane of each pair exhibits compound lean, and the second vane of the pair exhibits reverse compound lean or has substantially no tangential lean, (ii) the first vane of each pair has substantially no tangential lean, and the second vane of the pair exhibits reverse compound lean, or (iii) the first vane of each pair exhibits reverse compound lean, and the second vane of the pair exhibits greater reverse compound lean. Within each unequally-shaped pair the first vane is on the pressure surface side of the second vane.

Abstract translation: 在燃气涡轮发动机中，每个叶片具有从环形工作燃气发动机通道的内壁到外端壁的径向延伸的压力和吸力表面，并从叶片的导向到后缘轴向延伸。 每个叶片具有提供相应机翼部分的横截面。 相邻叶片布置成不均匀的对，其中：（i）每对的第一叶片表现出复合稀薄，并且该对的第二叶片表现出相反的复合物倾斜或基本上没有切向倾斜，（ii）第一叶片 每对的基本上没有切向倾斜，并且该对的第二叶片显示相反的复合稀薄，或（iii）每对的第一叶片表现出相反的复合稀薄，并且该对的第二叶片显示更大的反向化合物浓度。 在每个不相等的对中，第一叶片在第二叶片的压力表面侧上。