Abstract
Vortex driven sustained pressure pulsations in large solid rocket motors (SRMs) present an analytical modeling challenge, particularly when finite limit cycle amplitudes predictions are aimed for. The need for analytical models of these pulsations in SRMs is discussed. Two modelling strategies are reviewed: the energy balance and Culick’s lumped model approach. The lumped model has the advantage that it allows a prediction of the pulsation frequency, while this frequency is an input to the energy balance. A detailed derivation of a lumped model using a Vortex Sound Analogy is given. The analogy is similar to Howe’s vortex sound analogy. However, it contains an extra source term, which proves essential to find the correct acoustic radiation losses at the nozzle. When a volume integral is neglected one recovers a result very similar to the expected results. For a cylindrical combustion chamber this approximation is accurate both for axial and radial gas injection into the combustion chamber. For arbitrary combustion chamber geometry and actual combustion, the accuracy of the approximation has still to be established.
Original language | English |
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Title of host publication | 2018 AIAA/CEAS Aeroacoustics Conference |
Publisher | American Institute of Aeronautics and Astronautics |
ISBN (Print) | 9781624105609 |
DOIs | |
Publication status | Published - 2018 |
Externally published | Yes |
Event | 24th AIAA/CEAS Aeroacoustics Conference 2018 - Atlanta, United States Duration: 25 Jun 2018 → 29 Jun 2018 Conference number: 24 |
Conference
Conference | 24th AIAA/CEAS Aeroacoustics Conference 2018 |
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Abbreviated title | Aeroacoustics 2018 |
Country/Territory | United States |
City | Atlanta |
Period | 25/06/18 → 29/06/18 |
Keywords
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