maitya wrote:We slightly increase the mass flow (by artificially enlarging the core) thru the compressor stages (refer to the Euler turbine equation above) and keep a tight-lease on this temperature increase across HPC stages.
But then that would mean going back by atleast 3-4years and do the whole assembly-testing-flight testing etc etc cycle once again.
You would like this. From the DRDO e-book.
Various tests like aeromechanical mapping, performance mapping, and inlet distortion tolerance tests were carried out. The improved HP Compressor gave 3 per cent improved mass flow rate and increased pressure ratio. 50 h of testing was done at various inlet conditions.
maitya wrote:But there can be a better solution as well.
Can we keep the make the current compressor stages more "heat-resistant" and tide over this. Possible, if we are able to master the casting methodology etc for the intricate internal-cooling-passage-based blade cooling tech (with hollow shafts which would carry-in the cold-air and also carry out (towards the combustor) hot air etc). Pls note until very recently we were importing the wax-and-ceramic based moulds for the HPT stage (for the DS based blades with intricate internal-cooling-passages). But then again that's absolute cutting edge of the compressor blade tech.
Isn't this what DMRL is advertising. They are saying that they got from a hollow blade with a single channel
to something which has multiple channels to handle multiple airflows.
Are you suggesting something like this?