On the question of solid-propellant rocket engine design preventing unstable operation in the combustion chamber-Reference-Cited by-同舟云学术

On the question of solid-propellant rocket engine design preventing unstable operation in the combustion chamber

Published:2017-12-30 Issue:4 Volume: Page:63-72
ISSN:2542-0542
Container-title:Journal of «Almaz – Antey» Air and Space Defence Corporation
language:
Short-container-title:Journal of «Almaz – Antey» Air and Space Defence Corporation

Author:

Glebov G. A.¹,Vysotskaya S. A.²

Affiliation:

1. Kazan National Research Technical University named after A. N. Tupolev

2. Joint Stock Company “Kazan Experimental Design Bureau “Soyuz”

Abstract

The paper presents results of a numerical investigation concerning the effect that the flow duct shape and combustion rate equation have on the gas dynamic vortex flow pattern and self-excited pressure oscillations in the combustion chamber of a solid-propellant rocket engine. We provide guidelines on upgrading solid-propellant rocket engines in order to decrease the magnitude of pressure pulses in the case of pulsating combustion.

Publisher

Almaz-Antei Air and Space Defence Corporation

Reference12 articles.

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