Modeling of the Break-Up of Liquid Oxygen Droplets for Application in a Cryogenic Rocket Engine Simulation Code

2002 ◽  
Author(s):  
Emmanuel Bodele ◽  
Iskender Gokalp ◽  
Stephan Zurback ◽  
Didier Saucereau
Keyword(s):  
Rocket Engine ◽  
Liquid Oxygen ◽  
Simulation Code ◽  
Engine Simulation ◽  
Break Up

Critical Suction Peformance Test of Turbopump Assembly for a Liquid-Propellant Rocket Engine

2018 ◽  
Author(s):  
Hang Gi Lee ◽  
Ju Hyun Shin ◽  
Suk Hwan Yoon ◽  
Dae Jin Kim ◽  
Jun Hwan Bae ◽  
...  
Keyword(s):  
Liquid Nitrogen ◽  
Performance Test ◽  
Rocket Engine ◽  
Lightweight Design ◽  
Cavitation Number ◽  
Inlet Pressure ◽  
Liquid Oxygen ◽  
Pump Failure ◽  
Critical Cavitation ◽  
Suction Performance

This study investigates the behavior of a turbopump assembly during critical cavitation of the propellant pumps in the upper rocket engine of the Korea Space Launch Vehicle-II. Turbopumps operate under conditions involving low pressure at the pump inlet and high rotational speeds to allow for a lightweight design. This severe environment can easily cause cavitation to occur in the pump. This cavitation can then cause the pump operation to fail. As the cavitation number in the pump decreases below the critical point, the pump fails to operate. There is concern regarding the behavior of the turbopump assembly arising from pump failure due to cavitation. It is necessary to verify the problems that may occur if the turbopump assembly operates under extreme conditions, such like the critical cavitation. This study performed tests to investigate the breakdown of pumps in the turbopump assembly. Tests were conducted with liquid nitrogen, water, and high-pressure air instead of the mediums used during actual operation of liquid oxygen, kerosene, and hot gas. The turbopump was tested at the design point of 27,000 rpm, while the inlet pressure of each pump was controlled to approach the critical cavitation number. The turbine power output was maintained during the tests. The results show that the breakdown point of the oxidizer pump using liquid nitrogen, which is a cryogenic medium, occurred at a lower cavitation number than during an individual component suction performance test using water. The fuel pump using water, meanwhile, experiences breakdown at similar cavitation numbers in both tests. As the breakdown of the pump occurs, the power required by that pump decreases, and the rotational speed of the turbopump increases. Compared with individual pump suction performance tests, this breakdown test can be used to determine the limit of the propellant inlet pressure of the turbopump and to characterize the behavior of the turbopump assembly when a breakdown occurs. Vibrations were also analyzed for tests at a high cavitation number and at the critical cavitation number. The vibration increased with breakdown and notable frequencies were analyzed.

Infrared radiation characteristics of liquid oxygen/kerosene rocket engine plume with different number of nozzles

2019 ◽  
Vol 52 (3-4) ◽  
pp. 159-167
Author(s):  
Hong-Hua Cai ◽  
Wan-Sheng Nie ◽  
Ling-Yu Su ◽  
Tian-yi Shi ◽  
Kang-Kang Guo
Keyword(s):  
Infrared Radiation ◽  
Rocket Engine ◽  
Liquid Oxygen ◽  
Radiation Characteristics

A Computational Model for the Study of Gas Turbine Combustor Dynamics

1999 ◽  
Vol 121 (2) ◽  
pp. 243-248 ◽  
Author(s):  
D. M. Costura ◽  
P. B. Lawless ◽  
S. H. Fankel
Keyword(s):  
Gas Turbine ◽  
Mass Conservation ◽  
Single Step ◽  
Combustion Model ◽  
Reacting Flow ◽  
Gas Turbine Combustor ◽  
Splitting Algorithm ◽  
Simulation Code ◽  
One Dimensional ◽  
Engine Simulation

A dynamic combustor model is developed for inclusion into a one-dimensional full gas turbine engine simulation code. A flux-difference splitting algorithm is used to numerically integrate the quasi-one-dimensional Euler equations, supplemented with species mass conservation equations. The combustion model involves a single-step, global finite-rate chemistry scheme with a temperature-dependent activation energy. Source terms are used to account for mass bleed and mass injection, with additional capabilities to handle momentum and energy sources and sinks. Numerical results for cold and reacting flow for a can-type gas turbine combustor are presented. Comparisons with experimental data from this combustor are also made.

A model for combustor dynamics for inclusion in a dynamic gas turbine engine simulation code

1997 ◽  
Author(s):  
David Costura ◽  
Tomas Velez ◽  
Patrick Lawless ◽  
Steven Frankel ◽  
David Costura ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Simulation Code ◽  
Turbine Engine ◽  
Engine Simulation

Development of a Regeneratively Cooled Low Pressure Liquid Oxygen and Liquid Methane Rocket Engine

2018 ◽  
Author(s):  
Ethan Sichler ◽  
Eric Gonzalez ◽  
Jesus D. Montes ◽  
Richard Picard ◽  
Frank O. Chandler
Keyword(s):  
Rocket Engine ◽  
Low Pressure ◽  
Liquid Oxygen ◽  
Liquid Methane

scholarly journals Analytical viscous flow model and test validation of a swirl injector for rocket engine application

2019 ◽  
Author(s):  
G. Fiore ◽  
C. Bach ◽  
J. Sieder ◽  
M. Tajmar
Keyword(s):  
Flow Model ◽  
Rocket Engine ◽  
High Viscosity ◽  
Liquid Oxygen ◽  
Fluid Viscosity ◽  
Prediction Errors ◽  
Viscous Effects ◽  
Swirl Injector ◽  
Close Form

The generally adopted flow model inside a swirl injector, widely used injection concept for propulsive applications, relies upon the hypothesis of ideal flow neglecting the fluid viscosity effects. This model showed significant prediction errors with relatively high viscosity propellants, often leading to the need of an experimental characterization of the injection elements. In this paper, an analytical approach is presented, which includes the effects of viscous diffusion on the injector performance leading to a close form flow solution. The built model is thus experimentally validated testing a liquid oxygen (LOx) and an ethanol injector: the good agreement between the model and the experimental results leads to the construction of the injectors operational maps describing the injector behavior even in the presence of viscous effects.

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