To reduce a friction loss of a working fluid, and to enhance an efficiency of a turbine engine.
This device/method includes an aerofoil 154 including a concave pressure face 160 and a convex suction face 162 extended from a platform 156, in each of blades 152 separated in a peripheral direction, and projected radial-directionally, each flow passage 164 is defined by the aerofoils 154 of the adjacent blades 152 and an inner wall 157 formed by bringing the platforms 156 of the adjacent blades 152 into contact, and the inner wall 157 forms an inner radial-directional boundary. The inner wall 157 of the flow passage 164 includes a means for reducing the friction loss between a flow passing through the turbine engine 100 and the inner wall 157. The means for reducing the friction loss may include a non-axisymmetric trough 170 arranged between the adjacent aerofoils 154.
COPYRIGHT: (C)2010,JPO&INPIT
BIELEK CRAIG A
BARR BRIAN C
BOYER BRADLEY T
VANDEPUTTE THOMAS W
GAILIE PETER A
| JP2007247542A | 2007-09-27 |
| WO2006033407A1 | 2006-03-30 |
Hirokazu Ogura
Toshihisa Kurokawa
Next Patent: METHOD, SYSTEM AND/OR APPARATUS RELATING TO INDUCER FOR TURBINE ENGINE