scholarly journals Transient Three-Dimensional Analysis of Side Load in Liquid Rocket Engine Nozzles

2004 ◽  
Author(s):  
Ten-See Wang
Keyword(s):  
Dimensional Analysis ◽  
Rocket Engine ◽  
Three Dimensional ◽  
Liquid Rocket Engine ◽  
Side Load ◽  
Liquid Rocket

Unsteady Side-Load Evolution in a Liquid Rocket Engine Nozzle

2020 ◽  
Vol 57 (2) ◽  
pp. 391-397
Author(s):  
S. B. Verma ◽  
Oskar Haidn
Keyword(s):  
Rocket Engine ◽  
Liquid Rocket Engine ◽  
Side Load ◽  
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.

Stress of a Rocket Turbine under Different Loads Using Finite Element Modeling

2012 ◽  
Vol 232 ◽  
pp. 691-696
Author(s):  
Elhefny Amr ◽  
Guo Zhu Liang
Keyword(s):  
Finite Element ◽  
Rocket Engine ◽  
Three Dimensional ◽  
Fe Analysis ◽  
Liquid Rocket Engine ◽  
Operating Speed ◽  
Thermal Loads ◽  
Liquid Rocket ◽  
Maximum Stresses ◽  
Selection Of

Turbopump unit is a key component of the liquid rocket engine assembly and in this paper stresses of a turbopump turbine are investigated using finite element (FE) analysis. Three-dimensional solid modeling of a group of blades and a sector of the disc was first created on CAD software and subsequently exported to a FE package for analysis. The FE results reveals that the maximum stresses in the blades result from rotational and thermal loads owing to the relatively high operating speed and temperature of the turbine and they are located at the root of the blades. Also, the maximum stresses in the disc result from rotational and thermal loads, but with higher values than those in the blades and they are located at the center of the disc. The result of this study may serve as a guideline in the selection of the materials for both the disc and blades.

Rotordynamic analysis of a high thrust liquid rocket engine fuel (Kerosene) turbopump

2013 ◽  
Vol 26 (1) ◽  
pp. 169-175 ◽  
Author(s):  
Seong Min Jeon ◽  
Hyun Duck Kwak ◽  
Suk Hwan Yoon ◽  
Jinhan Kim
Keyword(s):  
Rocket Engine ◽  
Liquid Rocket Engine ◽  
Engine Fuel ◽  
Liquid Rocket ◽  
High Thrust
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