Experimental investigation of high-frequency combustion instabilities in liquid rocket engine

2008 ◽  
Vol 62 (1) ◽  
pp. 18-27 ◽  
Author(s):  
F. Richecoeur ◽  
S. Ducruix ◽  
P. Scouflaire ◽  
S. Candel
Keyword(s):  
Experimental Investigation ◽  
High Frequency ◽  
Rocket Engine ◽  
Liquid Rocket Engine ◽  
Combustion Instabilities ◽  
Liquid Rocket

scholarly journals Experimental Investigation of Heat Transfer in a Subscale Liquid Rocket Engine

2019 ◽  
Vol 35 (3) ◽  
pp. 544-551 ◽  
Author(s):  
P. Grenard ◽  
N. Fdida ◽  
L. Vingert ◽  
L. H. Dorey ◽  
L. Selle ◽  
...  
Keyword(s):  
Heat Transfer ◽  
Experimental Investigation ◽  
Rocket Engine ◽  
Liquid Rocket Engine ◽  
Liquid Rocket

scholarly journals Numerical Analysis of Self-Excited Combustion Instabilities in a Small MMH/NTO Liquid Rocket Engine

2020 ◽  
Vol 2020 ◽  
pp. 1-17
Author(s):  
Jianxiu Qin ◽  
Huiqiang Zhang
Keyword(s):  
Droplet Size ◽  
Mass Fraction ◽  
Rocket Engine ◽  
Three Dimensional ◽  
Navier Stokes ◽  
Liquid Rocket Engine ◽  
Combustion Instabilities ◽  
Pressure Oscillations ◽  
Two Phase ◽  
Liquid Rocket

Combustion instabilities in a small MMH/NTO liquid rocket engine used for satellite attitude and course control are numerically investigated. A three-dimensional Navier-Stokes code is developed to simulate two-phase spray combustion for cases with five different droplet Sauter Mean Diameters. As the droplet size increases from 30 microns to 80 microns, pressure oscillations are stronger with larger amplitudes. But an increase of the droplet size in the range of 80 microns to 140 microns indicates a reduction in the amplitudes of pressure oscillations. This trend is the same as the Hewitt criterion. The first tangential (1T) mode and the first longitudinal (1L) mode self-excited combustion instabilities are captured in the 60-micron and 80-micron cases. Abrupt spikes occur in the mass fraction of MMH and coincide with abrupt spikes in the mass fraction of NTO at the downstream regions just adjacent to the impinging points. Thus, local combustible high-dense mixtures are formed, which result in quasiconstant volume combustion and abrupt pressure spikes. The propagation and reflection of pressure waves in the chamber stimulate the combustion instability. When the droplet size is too small or too large, it is difficult to form local high-dense premixtures and combustion is stable in the chamber.

scholarly journals Development of test stand for experimental investigation on of chemical and physical phenomena in Liquid Rocket Engine

2011 ◽  
Vol 3 (2) ◽  
pp. 159-170 ◽  
Author(s):  
Emerson Andrade Santos ◽  
Wilton Fernandes Alves ◽  
André Neves Almeida Prado ◽  
Cristiane Aparecida Martins
Keyword(s):  
Experimental Investigation ◽  
Rocket Engine ◽  
Test Stand ◽  
Liquid Rocket Engine ◽  
Liquid Rocket ◽  
Physical Phenomena
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