2 ms·
Am I misreading your link? I see temperatures listed "only" up to 2,000 K; but the successful NTR tests went up over 2,500 K. (Excluding the failed ones that me
by perihelions 5y ago
Am I misreading your link? I see temperatures listed "only" up to 2,000 K; but the successful NTR tests went up over 2,500 K. (Excluding the failed ones that melted, of course).
- "The average exit gas temperature was 2,550 K (2,280 °C), the highest ever recorded by Project Rover. The chamber temperature was 2,750 K (2,480 °C), another record."
https://en.wikipedia.org/wiki/Project_Rover https://en.wikipedia.org/wiki/Project_Rover
There's also one notable difference: internal combustion turbines see their highest temperatures in the gas phase, which is somewhat insulated from the turbine blades (by weird fluid dynamic effects I don't understand). No solid material needs to withstand the peak temperature.
https://en.wikipedia.org/wiki/Turbine_blade#Film_cooling https://en.wikipedia.org/wiki/Turbine_blade#Film_cooling
- rich_sasha 5y agoI was focusing on turbine elements with temperatures well in excess of 1000 deg C, which is much higher than the temperatures described above. Indeed, exhaust gases are even hotter. I believe turbine elements are cooled by grouch internal channels these days, which is quite mind blowing.