scholarly journals Numerical study of operational processes in a GOx-kerosene rocket engine with liquid film cooling

2020 ◽  
Vol 9 (2) ◽  
pp. 132-141
Author(s):  
Evgenij A. Strokach ◽  
Igor N. Borovik ◽  
Vladimir G. Bazarov ◽  
Oscar J. Haidn
Keyword(s):  
Liquid Film ◽  
Film Cooling ◽  
Numerical Study ◽  
Rocket Engine ◽  
Operational Processes

Numerical study of liquid film cooling along an inclined plate

1993 ◽  
Vol 28 (4) ◽  
pp. 233-241 ◽  
Author(s):  
Wei-Mon Yan ◽  
Chyi-Yeou Soong
Keyword(s):  
Liquid Film ◽  
Film Cooling ◽  
Numerical Study ◽  
Inclined Plate

Numerical Study on Liquid-Film Cooling at High Pressure

2010 ◽  
Vol 58 (3) ◽  
pp. 163-186 ◽  
Author(s):  
H. W. Zhang ◽  
Y. L. He ◽  
W. Q. Tao
Keyword(s):  
High Pressure ◽  
Liquid Film ◽  
Film Cooling ◽  
Numerical Study

scholarly journals Effect of the MoSi2 coating on operational reliability of bipropellant rocket engine

2021 ◽  
Vol 260 ◽  
pp. 03003
Author(s):  
Kun Cai ◽  
Zhen Zhang ◽  
Na Wang ◽  
Yu Hu ◽  
Fengshan Wang
Keyword(s):  
High Temperature ◽  
Liquid Film ◽  
Film Cooling ◽  
Thermal Cycle ◽  
High Speed ◽  
Rocket Engine ◽  
Operational Reliability ◽  
Rocket Engines ◽  
Self Healing ◽  
Mosi2 Coating

This present study investigated the MoSi2 coating and its effect on reliability of bipropellant rocket engine. This coating is developed to protect the chamber substrate material form oxidization under hightemperature oxidative circumstance as bipropellant engine works. The multilayer structure of the MoSi2 coating shows excellent high-temperature and thermal-cycle resistance. Its characteristic of self-healing leads to the good performance under the long-time steady working condition for rocket engines. A 25000-seconds firing test was conducted to testify the performance of MoSi2 coating under high temperature above 1400℃. In addition, the influence of coating surface morphology on liquid film cooling was fully discussed in experiment and simulation. High-speed microscopy camera was used to study the effects of Weber number on the spreading and lasting of cooling liquid-film. the simulative comparison was conducted by OpenFOAM to present different transfer-heat modes, when a droplet impinges on the high-temperature surface of MoSi2 coating. All results show that higher smoothness of the coating is suitable for liquid-film cooling, strengthening liquid film spread and heat transfer. Moreover, scanning electron microscope (SEM) was used to study the effect of Mo layer residue on the coating thermal-cycle profermance. The test results indicates that Mo layer residue significantly cause penetrating cracks of the coating and then weaken the self-healing of the coating at downstream of throat. Therefore, it is important to strictly control the thickness of Mo layer by means of matching Mo target in ion plating. Thus after properly prolonging the infiltration time, Mo layer can be silicified completely without residue.

Experimental and numerical study of supersonic film cooling

AIAA Journal ◽  
1998 ◽  
Vol 36 ◽  
pp. 915-923 ◽  
Author(s):  
B. Aupoix ◽  
A. Mignosi ◽  
S. Viala ◽  
F. Bouvier ◽  
R. Gaillard
Keyword(s):  
Film Cooling ◽  
Numerical Study

ROCKET ENGINE WITH CONTINUOUSLY ROTATING LIQUID-FILM DETONATION

2019 ◽  
Author(s):  
S.M. FROLOV ◽  
◽  
I.O. SHAMSHIN ◽  
V.S. AKSENOV ◽  
I.A. SADYKOV ◽  
...  
Keyword(s):  
Liquid Film ◽  
Rocket Engine ◽  
Rotating Liquid

A study into the feasibility of using the oxygen-hydrocarbon engine 11D58M as a basis for development of a high-performance multifunctional gas-generatorless rocket engine with oxygen cooling

2019 ◽  
pp. 67-80
Author(s):  
Boris A. Sokolov ◽  
Nikolay N. Tupitsyn
Keyword(s):  
Film Cooling ◽  
High Performance ◽  
Rocket Engine ◽  
Hydrocarbon Fuel ◽  
Gas Generator ◽  
Automatic Equipment ◽  
The Us ◽  
Upper Stage ◽  
Pump Assembly ◽  
Turbo Pump

The paper presents results of engineering studies and research and development efforts at RSC Energia to analyze and prove the feasibility of using the mass-produced oxygen-hydrocarbon engine 11D58M with 8.5 ton-force thrust as a basis for development of a high-performance multifunctional rocket engine with oxygen cooling and 5 ton-force thrust, which is optimal for upper stages (US), embodying a system that does not include a gas generator. The multi-functionality of the engine implies including in it additional units supporting some functions that are important for US, such as feeding propellant from US tanks to the engine after flying in zero gravity, autonomous control of the engine automatic equipment to support its firing, shutdown, adjustments during burn and emergency protection in case of off-nominal operation, as well as generating torques for controlling the US attitude and stabilizing it during coasting, etc. Replacing conventional engine chamber cooling that uses high-boiling hydrocarbon fuel with the innovative oxygen cooling makes it possible to get rid of the internal film cooling circuits and eliminate their attendant losses of fuel, while the use of the oxygen gasified in the cooling circuit of the chamber to drive the turbo pump assembly permits to design an engine that does not have a gas generator. Key words: Multifunctional rocket engine, oxygen cooling, gas-generatorless design, upper stage.

scholarly journals Dynamics of Single Droplet Splashing on Liquid Film by Coupling FVM with VOF

Processes ◽  
2021 ◽  
Vol 9 (5) ◽  
pp. 841
Author(s):  
Yuzhen Jin ◽  
Huang Zhou ◽  
Linhang Zhu ◽  
Zeqing Li
Keyword(s):  
Liquid Film ◽  
Weber Number ◽  
Stokes Equations ◽  
Numerical Study ◽  
Three Dimensional ◽  
Navier Stokes ◽  
Single Droplet ◽  
Navier Stokes Equations ◽  
Volume Method ◽  
The Relationship

A three-dimensional numerical study of a single droplet splashing vertically on a liquid film is presented. The numerical method is based on the finite volume method (FVM) of Navier–Stokes equations coupled with the volume of fluid (VOF) method, and the adaptive local mesh refinement technology is adopted. It enables the liquid–gas interface to be tracked more accurately, and to be less computationally expensive. The relationship between the diameter of the free rim, the height of the crown with different numbers of collision Weber, and the thickness of the liquid film is explored. The results indicate that the crown height increases as the Weber number increases, and the diameter of the crown rim is inversely proportional to the collision Weber number. It can also be concluded that the dimensionless height of the crown decreases with the increase in the thickness of the dimensionless liquid film, which has little effect on the diameter of the crown rim during its growth.

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