Influence on TSPR's flight envelope by turbocharger

DOI

10.2991/eeeis-16.2017.70How to use a DOI?

Keywords

Turbocharged Solid propellant ramjet; Turbocharger; Flight envelope; Temperature limitation; Pressure limitation.

Abstract

In this article, the influence on the flight envelope of turbocharged solid propellant ramjet (TSPR) by turbocharger was studied by TSPR's performance prediction program. By those studies, some conclusions were obtained as follows: (1) to increase the compressor's pressure ratio could only expand the flight envelope in low altitude and low Mach number area, while the key factor to limit the maximum flight altitude and flight Mach number was the temperature limit of compressor impeller material; (2) when the temperature limit of compressor impeller raised from 800K to 1000K, TSPR's maximum latitude and Mach number could be raised from 25.5km and Ma3.57 to 30.7km and Ma 4.1; (3) when the actual turbocharger was introduced, the controlling factors for the maximum latitude and the maximum Mach number would be changed with the raise of the temperature and pressure of the turbocharger's design point, when low pressure and temperature were chosen as the design point the compressor's operating range would be the key factor, and when the high ones were chosen, the temperature limit would be the key factor.

Copyright

© 2017, the Authors. Published by Atlantis Press.

Open Access

This is an open access article distributed under the CC BY-NC license (http://creativecommons.org/licenses/by-nc/4.0/).

Download article (PDF)

TY  - CONF
AU  - Shi-Chang Liu
AU  - Jiang Li
AU  - Xu-Zhao Yang
AU  - Yang Liu
AU  - Kai Liu
PY  - 2016/12
DA  - 2016/12
TI  - Influence on TSPR's flight envelope by turbocharger
BT  - Proceedings of the 2nd Annual International Conference on Electronics, Electrical Engineering and Information Science (EEEIS 2016)
PB  - Atlantis Press
SP  - 567
EP  - 577
SN  - 2352-5401
UR  - https://doi.org/10.2991/eeeis-16.2017.70
DO  - 10.2991/eeeis-16.2017.70
ID  - Liu2016/12
ER  -