To provide a method and a device for cooling a gas turbine rotor blade.
A blade shape part 42 for a gas turbine 20 includes a leading edge 48, a trailing edge 50, a distal end plate 54, a first side wall 44 extending between a blade shape part root 52 and the distal end plate over a radial direction span, and a second side wall 46 connected to the first side wall at the leading edge and the trailing edge and having a cooling cavity 56 formed therein. The side wall extends between the blade shape part root and the distal end plate over the radial direction span. The blade shape part includes a trailing edge slot 70 penetrating the first side wall and arranged in a tandem style with a plurality of longitudinal interval. The slot has a flowing connection condition with a cooling cavity and is arranged in uneven distribution along the trailing edge to make the number of slots in at least one part of the trailing edge greater than that in other part of the trailing edge.
LAGRANGE BENJAMIN A
| JPS56159507A | 1981-12-08 | |||
| JP2001027102A | 2001-01-30 | |||
| JPH0814001A | 1996-01-16 | |||
| JPS63149076A | 1988-06-21 |
Hirokazu Ogura
Nobukazu Ito
Toshihisa Kurokawa
Next Patent: FUEL INJECTOR PROVIDED WITH FASTENING SLEEVE AS ABUTMENT PART FOR VALVE NEEDLE