Abstract Some design and experimental data on three cascades with the same 12° bending angle for the primary nozzle block of a gas turbine are presented. As is seen from the investigation the most efficient at the transonic velocities of the outward flow are the blades, the back curvature of which in the bevel cut zone decreases to the trailing edge. Also presented is the fact that the blade with the increasing back curvature has noticeably larger losses.
On choice of the blade back profile curvature in transonic turbine cascades
Russian Aeronautics (Iz VUZ) ; 54 , 2 ; 159-164
2011-06-01
6 pages
Article (Journal)
Electronic Resource
English
Investigations into rotating blade cascades for transonic flow
Engineering Index Backfile | 1964
|The base pressure problem in transonic turbine cascades
TIBKAT | 1978
|Transonic turbine blade cascade testing facility
NTRS | 1992
|Transonic turbine blade cascade testing facility
AIAA | 1992
|