Wikipedia says that the first turboprop aircraft engine was the Jendrassik Cs-1 invented in Hungary by György Jendrassik.
It says it was supposed to run at 1000 hp but "combustion problems" limited it to 400 hp.
I would like to know what turbine blade alloy it used. Could not find this info online. I have a feeling the blade alloy limits were what limited the engine power, since that is the main limiting factors on gas turbines in general.
Note: The Hungarian version of the wikipedia article says the turbine ran at 550 C, and...
A turbinalapátokat 50% reakciófokú csavart, szárnyprofil keresztmetszetű hőálló acélból gyártották precíziós öntéssel, és speciális beerősítéssel szerelték a rotorba.
Google translate:
The turbine blades are made of 50% reactive twisted, heat-resistant steel with wing section cross-sections, and are specially mounted in the rotor.
Don't know what that means. 50% steel? Then what is the other 50%? Also, there is no citation for it.
There was nothing inherently wrong with the design, however, and continued work on the flame cans should have allowed it to develop to full power.
is uncited. $\endgroup$ – DrZ214 Jan 9 '20 at 6:34