A Panel Method for the Hydrodynamic Performance Prediction of a Water-jet and an Inducer

2012 ◽  
Author(s):  
Spyros A. Kinnas ◽  
Shu-Hao Chang ◽  
Alokraj Valsaraj
Keyword(s):  
Performance Prediction ◽  
Present Method ◽  
Rocket Engine ◽  
Water Jet ◽  
Panel Method ◽  
Hydrodynamic Performance ◽  
Jet Pump ◽  
Time Step ◽  
Flow Solver ◽  
Turbo Pump

This paper presents the analyses of the hydrodynamic performance for a marine water-jet propulsor and a rocket engine turbo pump inducer by using a potential flow solver based on a low order panel method. The steady and unsteady fully-wetted and cavitating simulations for the water-jet rotor only problem are investigated and the steady fully-wetted simulation for the inducer is studied in this paper. The convergence studies of rotor averaged cavitating circulation distributions with number of panels on the blade and with different time step sizes are presented in the water-jet case. Finally, the predictions of the hydrodynamic performance for the water-jet pump and the inducer from the present method are validated against existing experimental data or numerical results from RANS solvers.

Performance Prediction of Cavitating Water-Jet Propulsors Using a Viscous/Inviscid Interactive Method

2008 ◽  
Author(s):  
Hong Sun ◽  
Spyros A. Kinnas
Keyword(s):  
Viscous Flow ◽  
Performance Prediction ◽  
Water Jet ◽  
Interaction Method ◽  
Jet Pump ◽  
Interactive Method ◽  
Sheet Cavitation ◽  
Jet Pumps

The authors present a viscous/inviscid interaction method to predict the viscous flow inside water-jet pumps, including the effects of sheet cavitation on the rotor and /or stator blades. The circumferentially averaged interaction between the rotor and the stator is accounted for in an iterative manner. The method is applied in the case of an actual water-jet pump and comparisons of the predicted and the measured rotor torque are presented.

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.

Turbo-pump with isolated two stage impellers for future rocket engine (Trial to drive impellers independently)

2008 ◽  
Vol 17 (1) ◽  
pp. 28-34 ◽  
Author(s):  
Toshiaki Kanemoto ◽  
Makoto Shimojyo ◽  
Ryunosuke Kawashima ◽  
Daisuke Tanaka ◽  
Akira Inagaki ◽  
...  
Keyword(s):  
Rocket Engine ◽  
Two Stage ◽  
Turbo Pump

CFD Calculation of the Flow Through a Water-Jet Pump

2001 ◽  
Author(s):  
Peixin Hu ◽  
◽  
M Zangeneh ◽  
Keyword(s):  
Water Jet ◽  
Jet Pump ◽  
Flow Through

The Development of an Aerodynamic Performance Prediction Tool for Modern Axial Flow Compressor Profiles

2006 ◽  
Author(s):  
Dario Bruna ◽  
Carlo Cravero ◽  
Mark G. Turner
Keyword(s):  
Performance Prediction ◽  
Parametric Design ◽  
Flow Analysis ◽  
Axial Flow ◽  
Navier Stokes ◽  
Flow Angle ◽  
Flow Solver ◽  
Aerodynamic Loss ◽  
Axial Flow Compressor ◽  
Flow Compressor

The development of a computational tool (MP-LOS) for the aerodynamic loss modeling and prediction for axial-flow compressor blade sections is presented in this paper. A state-of-the-art quasi 3-D flow solver, MISES, has been used for the flow analysis on existing airfoil geometries in many working conditions. Different values of inlet flow angle, inlet Mach number, AVDR, Reynolds number and solidity have been chosen to investigate a possible working range. The target is a loss prediction formulation that will be introduced into throughflow or axisymmetric Navier-Stokes codes for the performance prediction of multistage axial flow compressors. The loss coefficient has been correlated to the flow parameters that have shown an influence on the profile loss for the blades under study. The proposed correlation, using the described computational approach, can be extended to any profile family with the aid of any code for the parametric design of blade profiles.

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