Which kind of degree?Melbourne Guy said:
How so?Rive said:
°F, °R, °C or K? The radiator rejects heat to space, so that implies a heat source of a greater temperature. 2500°F would be manageable with a Mo alloy (mp 2883 K), while Nb (mp 2741 K) might be too soft. If 2500°C (Nb would liquid, Mo would be creeping or flowing), the one would have to use a Ta or W alloy (Ta, mp 3269 K; W, mp 3683 K). Ref: W. D. Klopp, "Technology Status of Molybdenum and Tungsten Alloys," Proceedings of the first symposium on Space Nuclear Power Systems, M.S. El-Genk and M. D. Hoover, Eds., Orbit Book Company, 1985. The symposium was held in Albuquerque, New Mexico.Melbourne Guy said:
I'm not aware of the 'R' units, @Astronuc, but thank you for the detailed suggestions, and note that the other side of the exchanger is even hotter. I'll take a look at the ASTAR alloys, I've not come across them beforeAstronuc said:
°R is the absolute scale, Rankine, related to °F, as K is related to °C. T(°R) = T(°F) + 459.67°, and 1 K = 1.8°R, or 1.8*T(K) = T(°R). °F, °R are in the English system (lbm, ft, s), while °C, K are used in SI or MKS system. The 2500 reminded me of 1371°C (2500°F) or about the melting point of many steels. Ni-alloys are melting by around 1430°C, so at 1371°C, they would have very little strength and would probably be 'flowing' under low to moderate stress.Melbourne Guy said:
They are somewhat esoteric as far as alloys go.Melbourne Guy said:
Esoteric is good, this is sci-fi, after allAstronuc said:
Then maybe it's better to leave it like that.Melbourne Guy said:
It's just absurdly high. Usually a (thermal) power plant has a 'hot leg' around a few hundred Celsius at most, and your spacecraft has its 'cold leg' higher without utilization?Melbourne Guy said:
It's dumping the heat of the bubble drive, which folds spacetime like an Alcubierre warp drive and that generates significant thermal load! Or at least, I've now decided it does, based on this threadRive said:
The best material for a heat exchanger on a space ship would be a high thermal conductivity material that is also lightweight and able to withstand extreme temperatures. Some examples of suitable materials could be copper, aluminum, or titanium.
The material used in a heat exchanger can greatly impact its efficiency. A material with high thermal conductivity will allow for faster heat transfer, while a lightweight material will reduce the overall weight of the heat exchanger and the space ship. Additionally, a material that can withstand high temperatures will ensure the heat exchanger can function properly in the extreme conditions of space.
Yes, there are several important properties that a material should have to be considered suitable for a heat exchanger on a space ship. These include high thermal conductivity, low density, high melting point, and resistance to corrosion and thermal fatigue.
In most cases, a single material would not be able to meet all the necessary requirements for a heat exchanger on a space ship. Instead, a combination of materials may be used in different parts of the heat exchanger to optimize its performance and durability.
The choice of material is crucial in the design and functionality of a heat exchanger on a space ship. The material not only affects the efficiency of the heat exchanger but also impacts the weight, durability, and overall performance of the space ship. Choosing the right material is essential for the successful operation of a heat exchanger in the extreme conditions of space.