Abstract
The U. S. Air Force is currently developing electrical generators for a variety of airborne applications requiring high-power and high-voltage capability [1]. The airborne environment imposes severe constraints on volume and weight which make a superconducting generator an attractive approach owing to its small size and high power-to-volume ratio. Since superconducting generators are in direct competition with other energy production schemes for these applications, the design of the cryogenic support subsystem strongly influences system potential. A study*, therefore, has been underway to evaluate techniques and system designs for providing the cryogenic cooling to support an airborne superconducting generator system. This paper describes the system constraints, airborne applications, and the resulting cryogenic cooling requirements. The design methodology and trade-off considerations are discussed for the airborne support system, the ground support system, and the cryogenic transport system. Primary emphasis was placed on minimizing the weight of the airborne system and providing the most cost-effective approach for supplying the cryogenic cooling from the wellhead source to the aircraft.
Air Force Flight Dynamics Labortory Contract No. F33615-78-C-3413.
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Abbreviations
- C g :
-
= specific heat of generator, J/g-K
- C p :
-
= specific heat of helium, J/g-K
- h in :
-
= enthalpy of gas entering generator, J/g
- h L :
-
= enthalpy of gas exiting through power leads, J/g
- h T :
-
= enthalpy of gas exiting through torque tube, J/g
- m g :
-
= mass of generator, g
- ṁ He :
-
= mass flow of 4.5 K gas to generator, g/s
- ṁ L :
-
= mass flow of gas exiting through power leads, g/s
- ṁ T :
-
= mass flow of gas exiting through the torque tube, g/s
- Q L :
-
= total leak to generator through power leads, W
- Q R :
-
= total radiation heat leak to generator, W
- Q T :
-
= total heat leak to generator through torque tube, W
- t :
-
= time, s
- t c :
-
= cooldown time, s
- T :
-
= temperature, K
- T R :
-
= generator standby steady-state temperature, K
- θ :
-
= T generator-T helium, K
- θ final :
-
= 10.0 K − 4.2 K = 5.8 K
- θ initial :
-
= T R - 4.2 K
References
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R. D. Blaugher, J. L. McCabria, and J. H. Parker, Jr., IEEE Trans. Magn. Mag-13:755 (1977).
B. B. Gamble, T. Keim, and P. A. Rios, “Superconducting Rotor Research,” AFAPL-TR-77–68 General Electric Company (November 1977).
B. B. Gamble, private communication.
P. Hickey, private communication.
“Helium, A Public Policy Problem,” report by the Helium Study Committee, Board on Mineral and Energy Resources Commission on Natural Resources, National Research Council, National Academy of Sciences, Washington, D.C. (1978).
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H. E. Simpkins and R. L. Reed, in Advances in Cryogenic Engineerings Vol. 12, Plenum Press, New York (1967), p. 640.
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Kerney, P.J., Lessard, P.A. (1980). Cryogenic Support System for Airborne Superconducting Generators. In: Timmerhaus, K.D., Snyder, H.A. (eds) Advances in Cryogenic Engineering. Advances in Cryogenic Engineering, vol 35 A. Springer, Boston, MA. https://doi.org/10.1007/978-1-4613-9856-1_39
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DOI: https://doi.org/10.1007/978-1-4613-9856-1_39
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