Vortex Shedding Influence on Hybrid Rocket Pressure Oscillations and Combustion Efficiency

2016 ◽  
Vol 32 (6) ◽  
pp. 1386-1394 ◽  
Author(s):  
Jérôme Messineo ◽  
Jean-Yves Lestrade ◽  
Jouke Hijlkema ◽  
Jérôme Anthoine
Keyword(s):  
Vortex Shedding ◽  
Combustion Efficiency ◽  
Hybrid Rocket ◽  
Pressure Oscillations

Conceptual Regenerative Nozzle Cooling Design for a Hydroxyl-Terminated Polybutadiene and Oxygen Hybrid Rocket Engine

2017 ◽  
Author(s):  
Luis R. Robles ◽  
Johnny Ho ◽  
Bao Nguyen ◽  
Geoffrey Wagner ◽  
Jeremy Surmi ◽  
...  
Keyword(s):  
Combustion Chamber ◽  
High Temperatures ◽  
Cooling System ◽  
Rocket Engine ◽  
Combustion Efficiency ◽  
Rocket Engines ◽  
Hybrid Rocket ◽  
Gaseous Oxygen ◽  
Rocket Nozzle ◽  
Regenerative Cycle

Regenerative rocket nozzle cooling technology is well developed for liquid fueled rocket engines, but the technology has yet to be widely applied to hybrid rockets. Liquid engines use fuel as coolant, and while the oxidizers typically used in hybrids are not as efficient at conducting heat, the increased renewability of a rocket using regenerative cycle should still make the technology attractive. Due to the high temperatures that permeate throughout a rocket nozzle, most nozzles are predisposed to ablation, supporting the need to implement a nozzle cooling system. This paper presents a proof-of-concept regenerative cooling system for a hybrid engine which uses hydroxyl-terminated polybutadiene (HTPB) as its solid fuel and gaseous oxygen (O2) as its oxidizer, whereby a portion of gaseous oxygen is injected directly into the combustion chamber and another portion is routed up through grooves on the exterior of a copper-chromium nozzle and, afterwards, injected into the combustion chamber. Using O2 as a coolant will significantly lower the temperature of the nozzle which will prevent ablation due to the high temperatures produced by the exhaust. Additional advantages are an increase in combustion efficiency due to the heated O2 being used for combustion and an increased overall efficiency from the regenerative cycle. A computational model is presented, and several experiments are performed using computational fluid dynamics (CFD).

Analysis of Acoustics and Vortex Shedding Interactions in Hybrid Rocket Motors

2014 ◽  
Vol 30 (6) ◽  
pp. 1613-1619 ◽  
Author(s):  
Dario Pastrone ◽  
Lorenzo Casalino ◽  
Carmine Carmicino
Keyword(s):  
Vortex Shedding ◽  
Hybrid Rocket ◽  
Rocket Motors

Combustion Instability Involving Vortex Shedding in Hybrid Rocket Motors

2013 ◽  
Author(s):  
Dario Pastrone ◽  
Lorenzo Casalino ◽  
Marco Codegone ◽  
Carlo Novara ◽  
Carmine Carmicino
Keyword(s):  
Vortex Shedding ◽  
Combustion Instability ◽  
Hybrid Rocket ◽  
Rocket Motors

Numerical Simulation of the Coupling Between Vortex Shedding and Acoustic Field in a Solid Propellant Engine

2003 ◽  
Author(s):  
Fabio Gori ◽  
Riccardo Pecorari ◽  
Marco Mastrapasqua
Keyword(s):  
Numerical Simulation ◽  
Vortex Shedding ◽  
Acoustic Waves ◽  
Solid Propellant ◽  
Solid Rocket Motor ◽  
Pressure Oscillations ◽  
Rocket Motors ◽  
Commercial Code ◽  
Solid Propellant Rocket ◽  
Solid Rocket

The paper investigates the numerical simulation of vortex shedding in the flow field of solid-propellant rocket motors. This phenomenon, resulting from the strong coupling between shear-layer instability and acoustic waves in the chamber, produces thrust and pressure oscillations. Numerical simulations are performed on the combustion chamber of the Ariane 5 MPS P230 (Solid Rocket Motor) with the commercial code Fluent CFD for conditions corresponding to 89 s of combustion time. The objective of the study is to reproduce the pressure oscillations frequencies and magnitudes, to compare the available experimental data and to capture the vortex shedding phenomena.

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