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Beschreibung
Combustion instability problems have been experienced during nearly every rocket engine development program, characterized by pressure oscillations and release of energy. Several distinct types of instability have been observed, including the high frequency instability or acoustic instability, which is usually suppressed by means of passive control devices. The main purpose of this work was the experimental investigation of Helmholtz resonators and baffles to control acoustic instabilities in combustion chambers. Firstly, cold tests were carried out on full-scale model to analyze the efficiency of resonators. Experimental frequency spectrum data, in excellent agreement with theory, demonstrated the resonator is capable to reduce significantly the SPL amplitude. Afterwards, results of hot tests were compared with cold tests and with theory. The experimental data validated the methodology to design resonators useable to control combustion instabilities. This book provides a step-by-step procedure, which can be helpful to engineers and designers of liquid rocket engines, rocket motors and industrial burners, or anyone else who has already faced acoustic instability problems.
Combustion instability problems have been experienced during nearly every rocket engine development program, characterized by pressure oscillations and release of energy. Several distinct types of instability have been observed, including the high frequency instability or acoustic instability, which is usually suppressed by means of passive control devices. The main purpose of this work was the experimental investigation of Helmholtz resonators and baffles to control acoustic instabilities in combustion chambers. Firstly, cold tests were carried out on full-scale model to analyze the efficiency of resonators. Experimental frequency spectrum data, in excellent agreement with theory, demonstrated the resonator is capable to reduce significantly the SPL amplitude. Afterwards, results of hot tests were compared with cold tests and with theory. The experimental data validated the methodology to design resonators useable to control combustion instabilities. This book provides a step-by-step procedure, which can be helpful to engineers and designers of liquid rocket engines, rocket motors and industrial burners, or anyone else who has already faced acoustic instability problems.
Über den Autor
Doctor of Science in aero & mechanical engineering from ITA, is the Chief of Propulsion Division at Institute of Aeronautics and Space, located in São José dos Campos. He is specialized in liquid rocket engine design from Moscow Aerospace Institute and authored several articles in combustion instability, dynamic modeling and rocket technology.
Details
Erscheinungsjahr: 2010
Fachbereich: Raumfahrttechnik
Genre: Mathematik, Medizin, Naturwissenschaften, Technik
Rubrik: Naturwissenschaften & Technik
Medium: Taschenbuch
Inhalt: 172 S.
ISBN-13: 9783838369921
ISBN-10: 3838369920
Sprache: Englisch
Einband: Kartoniert / Broschiert
Autor: Santana Jr., Avandelino
Hersteller: LAP LAMBERT Academic Publishing
Verantwortliche Person für die EU: preigu GmbH & Co. KG, Lengericher Landstr. 19, D-49078 Osnabrück, mail@preigu.de
Maße: 220 x 150 x 11 mm
Von/Mit: Avandelino Santana Jr.
Erscheinungsdatum: 16.06.2010
Gewicht: 0,274 kg
Artikel-ID: 101042605