Jendrassik Cs-1 Engine
Axial-flow design with 15-stage compressor and 7-stage turbine, it incorporated many modern features. These included a rigid compressor-turbine rotor assembly carried on front and rear bearings. There was a single annular combustion chamber, of reverse-flow configuration to shorten the engine, air cooling of the turbine discs and turbine blades with extended roots to reduce heat transfer to the disc. The annular air intake surrounded a reduction gear for propeller drive takeoff, and the exhaust duct was also annular.
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With predicted output of 1,000 bhp at 13,500 rpm the Cs-1 stirred interest in the Hungarian aircraft industry with its potential to power a modern generation of high-performance aircraft, and construction was begun of a twin-engined fighter-bomber, the
Varga RMI-1 X/H, to be powered by it.
The first bench run took place in 1940, becoming the world's first turboprop engine to run. However, although the design was inherently sound, combustion problems were experienced which limited the output to around 400 bhp.
] 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.
Work on the engine stopped in 1941 when the
Hungarian Air Force selected the
Messerschmitt Me 210 for the heavy fighter role, and the engine factory converted over to the
Daimler-Benz DB 605 to power it. The prototype RMI-1 was later fitted with these engines in 1944.