Rocket Engine with Continuous Detonation Combustion of the Natural Gas–Oxygen Propellant System

Rocket Engine with Continuous Detonation Combustion of the Natural Gas–Oxygen Propellant System In a demonstrator of a detonation rocket engine (DRE) using the natural gas–oxygen propellant system, a high (270 s) specific impulse at sea level at a low (32 atm) mean combustor pressure was experimentally obtained for the first time. Comparison of these characteristics with the respective ones (263 s and 61 atm) of the well-known Russian RD 170-A liquid-propellant rocket engine using deflagration combustion of the kerosene–oxygen propellant system showed that the specific impulse at sea level in the DRE is close to that in the deflagration-combustion engine but is produced at half as high a mean combustor pressure. This indicates that the energy efficiency of detonation combustion exceeds that of deflagration combustion, and that there is room to improve the weight–size characteristics of the turbopump unit in the DRE. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Doklady Physical Chemistry Springer Journals

Rocket Engine with Continuous Detonation Combustion of the Natural Gas–Oxygen Propellant System

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Publisher
Pleiades Publishing
Copyright
Copyright © 2018 by Pleiades Publishing, Ltd.
Subject
Chemistry; Physical Chemistry
ISSN
0012-5016
eISSN
1608-3121
D.O.I.
10.1134/S001250161802001X
Publisher site
See Article on Publisher Site

Abstract

In a demonstrator of a detonation rocket engine (DRE) using the natural gas–oxygen propellant system, a high (270 s) specific impulse at sea level at a low (32 atm) mean combustor pressure was experimentally obtained for the first time. Comparison of these characteristics with the respective ones (263 s and 61 atm) of the well-known Russian RD 170-A liquid-propellant rocket engine using deflagration combustion of the kerosene–oxygen propellant system showed that the specific impulse at sea level in the DRE is close to that in the deflagration-combustion engine but is produced at half as high a mean combustor pressure. This indicates that the energy efficiency of detonation combustion exceeds that of deflagration combustion, and that there is room to improve the weight–size characteristics of the turbopump unit in the DRE.

Journal

Doklady Physical ChemistrySpringer Journals

Published: Mar 14, 2018

References

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