Solid Rocket Motor Combustion Instabilities:Analysis of the Transition to the First Limit Cycle

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Abstract

A nonlinear multi time-scale analysis of the solid propellant rocket motor transition to the first limit cycle is presented and the motor behavior subsequent to some relevant transition scenarios is investigated. Important physical parameters characterizing the transition to limit cycle are then put in evidence and their cross-effects are studied. The analysis takes into account the effects of acoustic-vorticity-entropy wave coupling, waves steepening, rotational and viscous flow losses due to the steep-fronted waves, energy losses in the steepened state, nonlinear energy pathways and includes the study of the oscillatory energy losses in the nozzle, the unsteady combustion and the combustion chamber geometry changes resulting from the grain regression. The analysis provides evidence that in the investigated instability regions the wave amplitude evolution in the combustion chamber as well as the actual intrinsic motor stability is influenced by the time-history of selected parameter interactions.
Lingua originaleEnglish
Pagine1-16
Numero di pagine16
Stato di pubblicazionePublished - 2009

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combustion stability
rockets
cycles
combustion chambers
energy dissipation
solid rocket propellants
rotational flow
viscous flow
vorticity
nozzles
regression analysis
histories
entropy
acoustics
geometry
interactions
energy

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title = "Solid Rocket Motor Combustion Instabilities:Analysis of the Transition to the First Limit Cycle",
abstract = "A nonlinear multi time-scale analysis of the solid propellant rocket motor transition to the first limit cycle is presented and the motor behavior subsequent to some relevant transition scenarios is investigated. Important physical parameters characterizing the transition to limit cycle are then put in evidence and their cross-effects are studied. The analysis takes into account the effects of acoustic-vorticity-entropy wave coupling, waves steepening, rotational and viscous flow losses due to the steep-fronted waves, energy losses in the steepened state, nonlinear energy pathways and includes the study of the oscillatory energy losses in the nozzle, the unsteady combustion and the combustion chamber geometry changes resulting from the grain regression. The analysis provides evidence that in the investigated instability regions the wave amplitude evolution in the combustion chamber as well as the actual intrinsic motor stability is influenced by the time-history of selected parameter interactions.",
keywords = "Combustion, Cycle, Instabilities, Limit, Motor, Rocket",
author = "Giuseppe Lombardo",
year = "2009",
language = "English",
pages = "1--16",

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TY - CONF

T1 - Solid Rocket Motor Combustion Instabilities:Analysis of the Transition to the First Limit Cycle

AU - Lombardo, Giuseppe

PY - 2009

Y1 - 2009

N2 - A nonlinear multi time-scale analysis of the solid propellant rocket motor transition to the first limit cycle is presented and the motor behavior subsequent to some relevant transition scenarios is investigated. Important physical parameters characterizing the transition to limit cycle are then put in evidence and their cross-effects are studied. The analysis takes into account the effects of acoustic-vorticity-entropy wave coupling, waves steepening, rotational and viscous flow losses due to the steep-fronted waves, energy losses in the steepened state, nonlinear energy pathways and includes the study of the oscillatory energy losses in the nozzle, the unsteady combustion and the combustion chamber geometry changes resulting from the grain regression. The analysis provides evidence that in the investigated instability regions the wave amplitude evolution in the combustion chamber as well as the actual intrinsic motor stability is influenced by the time-history of selected parameter interactions.

AB - A nonlinear multi time-scale analysis of the solid propellant rocket motor transition to the first limit cycle is presented and the motor behavior subsequent to some relevant transition scenarios is investigated. Important physical parameters characterizing the transition to limit cycle are then put in evidence and their cross-effects are studied. The analysis takes into account the effects of acoustic-vorticity-entropy wave coupling, waves steepening, rotational and viscous flow losses due to the steep-fronted waves, energy losses in the steepened state, nonlinear energy pathways and includes the study of the oscillatory energy losses in the nozzle, the unsteady combustion and the combustion chamber geometry changes resulting from the grain regression. The analysis provides evidence that in the investigated instability regions the wave amplitude evolution in the combustion chamber as well as the actual intrinsic motor stability is influenced by the time-history of selected parameter interactions.

KW - Combustion

KW - Cycle

KW - Instabilities

KW - Limit

KW - Motor

KW - Rocket

UR - http://hdl.handle.net/10447/42384

M3 - Other

SP - 1

EP - 16

ER -