ACOUSTIC CAVITIES DESIGN PROCEDURES

Authors

  • A. Santana Jr. Instituto de Aeronáutica e Espaço Divisão de Sistemas Espaciais
  • M. S. Silva Instituto Tecnológico de Aeronáutica Departamento de Propulsão/ Projetos
  • P. T. Lacava Instituto Tecnológico de Aeronáutica Departamento de Propulsão/ Projetos
  • L. C. S. Góes Instituto Tecnológico de Aeronáutica Departamento de Propulsão/ Projetos

DOI:

https://doi.org/10.5380/reterm.v6i2.61687

Keywords:

combustion instability, liquid propellant rocket engine, instability control in rocket engines

Abstract

Combustion instability is recognized as one of the major problems frequently faced by engineers during the development of either liquid or solid propellant rocket engines. The performance of the engine can be highly affected by these high frequencies instabilities, possibly leading the rocket to an explosion. The main goal while studying combustion chambers instability, either by means of baffles or acoustic absorbers, is to achieve the stability needed using the simplest possible manner. This paper has the purpose of studying combustion chambers instabilities, as well as the design of acoustic absorbers capable of reducing their eigenfrequencies. Damping systems act on the chamber eigenfrequency, which has to be, therefore, previously known.

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Published

2007-12-31

How to Cite

Santana Jr., A., Silva, M. S., Lacava, P. T., & Góes, L. C. S. (2007). ACOUSTIC CAVITIES DESIGN PROCEDURES. Revista De Engenharia Térmica, 6(2), 27–33. https://doi.org/10.5380/reterm.v6i2.61687

Issue

Vol. 6 No. 2 (2007)

Section

Tecnologia/Technology

License

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