Implications of distribution voltage configuration on TeDP electrical systems

Abstract

Purpose

This article is aims to inform aircraft propulsion system designers of the implications which fundamental power distribution design assumptions have on the effectiveness and viability of turboelectric distributed propulsion (TeDP) systems. Improvements and challenges associated with selecting alternating or direct current for normal- and superconducting distribution systems are presented. Additionally, for superconducting systems, the benefits of bi-polar DC distribution are discussed, as well as the implications of operating voltage on the mass and efficiency of TeDP grid components.

Design/methodology/approach

The approach to this paper selects several high-level fundamental configuration decisions, which must be made, and it qualitatively discusses potential implications of these decisions.

Findings

Near term TeDP architectures which employ conventionally conducting systems may benefit from alternating current (AC) distribution concepts to eliminate the mass and losses associated with power conversion. Farther term TeDP concepts which employ superconducting technologies may benefit from direct current (DC) distribution to reduce the cryocooling requirements stemming from AC conduction losses. Selecting the operating voltage for superconducting concepts requires a divergence from the present day criteria employed with terrestrial superconducting transmission systems.

Practical implications

The criteria presented in the paper will assist in the early conceptual architecting of TeDP systems.

Originality/value

The governing principles behind the configuration of multi-MW airborne electrical microgrid systems are presently immature. This paper represents a unique look and the motivating principles behind fundamental electrical configuration decisions in the context of TeDP.

Citation

J. Armstrong, M. and A.H. Ross, C. (2014), "Implications of distribution voltage configuration on TeDP electrical systems", Aircraft Engineering and Aerospace Technology, Vol. 86 No. 6, pp. 501-508. https://doi.org/10.1108/AEAT-04-2014-0048