ACTA AERONAUTICAET ASTRONAUTICA SINICA >
High pressure combustion experiment for hypergolic propellant unlike doublet injectors
Received date: 2023-08-31
Revised date: 2023-09-14
Accepted date: 2023-10-07
Online published: 2023-10-13
Supported by
National Level Program
To guide the design of thrust chamber injectors for high chamber pressure orbits and attitude control rocket engines， we conduct combustion tests of NTO/MMH unlike doublet injectors at high pressure using the chrome bronze heat sink combustor. The effects of the mixing ratio， ratio of injection orifice diameter， Rupe number， impinging angle and chamber pressure on the characteristic velocity and combustion efficiency are obtained. The results show that， increase in the mixing ratio， ratio of injection orifice diameter， Rupe number or impinging angle leads to initial increase， then constant， and final decrease in the characteristic velocity and combustion efficiency. With the increase of the chamber pressure， the characteristic velocity and combustion efficiency first increase significantly and then remain unchanged. A mixing ratio between 1.71 and 2.31， injection orifice diameter 1.2 and 1.4， Rupe number 0.68 and 1.28， impinging angle 70°and 80°， and chamber pressure over 3 MPa indicate a high combustion efficiency level of 0.97-0.98.
Feng ZHANG , Yi SUN , Shuai SHANG , Baoe YANG . High pressure combustion experiment for hypergolic propellant unlike doublet injectors[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2024 , 45(11) : 529507 -529507 . DOI: 10.7527/S1000-6893.2023.29507
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