Combustion instability is one of the leading factors in limiting the progress and innovations of liquid rocket engines and power plants. Under certain operating conditions, unsteady heat release and acoustic wave interactions can couple and lead to instabilities, such as self-sustaining pressure oscillations, that can lead to reduced combustor performance and potentially hardware damage. In this project, the thermoacoustic effects of controlling the equivalence ratio of a single-element natural gas combustor were modeled and analyzed. The project used Fidelity Pointwise for meshing, ANSYS Fluent for modeling, ERAU VEGA HPC for computing, and MATLAB for acoustic analysis. A numerical model of the Purdue University Continuously Variable Resonance Combustor was created as a two-dimensional, axisymmetric domain and modeled in Fluent with finite rate chemistry and a hybrid RANS/LES approach. The acoustic analysis and power spectral densities were done with a Fast Fourier Transform algorithm.
The dominant frequencies, found to be between 1463 Hz and 1551 Hz, compare well with the experimental result of 1390 Hz, showing that the numerical model captured the primary acoustic modes of the combustor. However, the peak amplitudes of these frequencies were found to be around 3 to 7.5 psi2 /Hz, lower than the experimental result of 24.5 psi2 /Hz. This is potentially due to the reduced-order chemical kinetics, numerical dissipation, and lack of three-dimensional effects. Across three cases of varying equivalence ratios, the dominant frequency modes remained relatively constant, confirming that this characteristic is largely driven by system geometry. The stoichiometric case exhibited the lowest amplitudes, as stoichiometric combustion is typically the most stable and has the most complete heat release. The rich mixture exhibited the highest amplitude as it tends to have more incomplete combustion and slower reaction zones, which allows the unsteady heat release to more easily couple with these pressure oscillations.
","abstract_html":"<p>Combustion instability is one of the leading factors in limiting the progress and innovations of liquid rocket engines and power plants. Under certain operating conditions, unsteady heat release and acoustic wave interactions can couple and lead to instabilities, such as self-sustaining pressure oscillations, that can lead to reduced combustor performance and potentially hardware damage. In this project, the thermoacoustic effects of controlling the equivalence ratio of a single-element natural gas combustor were modeled and analyzed. The project used Fidelity Pointwise for meshing, ANSYS Fluent for modeling, ERAU VEGA HPC for computing, and MATLAB for acoustic analysis. A numerical model of the Purdue University Continuously Variable Resonance Combustor was created as a two-dimensional, axisymmetric domain and modeled in Fluent with finite rate chemistry and a hybrid RANS/LES approach. The acoustic analysis and power spectral densities were done with a Fast Fourier Transform algorithm.</p> <p>The dominant frequencies, found to be between 1463 Hz and 1551 Hz, compare well with the experimental result of 1390 Hz, showing that the numerical model captured the primary acoustic modes of the combustor. However, the peak amplitudes of these frequencies were found to be around 3 to 7.5 psi2 /Hz, lower than the experimental result of 24.5 psi2 /Hz. This is potentially due to the reduced-order chemical kinetics, numerical dissipation, and lack of three-dimensional effects. Across three cases of varying equivalence ratios, the dominant frequency modes remained relatively constant, confirming that this characteristic is largely driven by system geometry. The stoichiometric case exhibited the lowest amplitudes, as stoichiometric combustion is typically the most stable and has the most complete heat release. The rich mixture exhibited the highest amplitude as it tends to have more incomplete combustion and slower reaction zones, which allows the unsteady heat release to more easily couple with these pressure oscillations.</p>","abstract_has_math":false,"creators":["Green, Carter"],"institution":null,"degree_name":"Master of Science in Aerospace Engineering","degree_level":"Thesis - Open Access","degree_discipline":"Aerospace Engineering","degree_department":null,"school":null,"contributors":[],"advisors":[],"committee_chairs":[],"committee_members":[],"year":2026,"date_issued":"2026-04-03T07:00:00Z","date_published":"2026-04-03T07:00:00Z","updated_at":"2026-07-27T19:26:22Z","subjects":["Combustion","Combustion Instability","Thermoacoustics","Acoustics","Methane","Propulsion","Computational Fluid Dynamics","ANSYS Fluent","Power Spectral Density","Equivalence Ratio","Flame Dynamics","Natural Gas Combustor","Finite-rate Chemistry","Hybrid RANS/LES","Turbulent Reacting Flows","Propulsion and Power"],"languages":[],"rights":[],"rights_urls":[],"identifier_entries":[]},"links":{"outbound_url":"https://commons.erau.edu/edt/976","outbound_label":"Repository record","outbound_source":"dc:identifier"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:creator","label":"Author","values":["Green, Carter"]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"thesis:degree_discipline","label":"Discipline","values":["Aerospace Engineering"]},{"key":"thesis:degree_level","label":"Degree Level","values":["Thesis - Open Access"]},{"key":"thesis:degree_name","label":"Degree Name","values":["Master of Science in Aerospace Engineering"]}]},{"id":"subjects_keywords","label":"Subjects and Keywords","entries":[{"key":"dc:subject","label":"Dc Subject","values":["Combustion","Combustion Instability","Thermoacoustics","Acoustics","Methane","Propulsion","Computational Fluid Dynamics","ANSYS Fluent","Power Spectral Density","Equivalence Ratio","Flame Dynamics","Natural Gas Combustor","Finite-rate Chemistry","Hybrid RANS/LES","Turbulent Reacting Flows","Propulsion and Power"]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier","label":"Identifier","values":["https://commons.erau.edu/edt/976"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description.abstract","label":"Abstract","values":["Combustion instability is one of the leading factors in limiting the progress and innovations of liquid rocket engines and power plants. Under certain operating conditions, unsteady heat release and acoustic wave interactions can couple and lead to instabilities, such as self-sustaining pressure oscillations, that can lead to reduced combustor performance and potentially hardware damage. In this project, the thermoacoustic effects of controlling the equivalence ratio of a single-element natural gas combustor were modeled and analyzed. The project used Fidelity Pointwise for meshing, ANSYS Fluent for modeling, ERAU VEGA HPC for computing, and MATLAB for acoustic analysis. A numerical model of the Purdue University Continuously Variable Resonance Combustor was created as a two-dimensional, axisymmetric domain and modeled in Fluent with finite rate chemistry and a hybrid RANS/LES approach. The acoustic analysis and power spectral densities were done with a Fast Fourier Transform algorithm.
The dominant frequencies, found to be between 1463 Hz and 1551 Hz, compare well with the experimental result of 1390 Hz, showing that the numerical model captured the primary acoustic modes of the combustor. However, the peak amplitudes of these frequencies were found to be around 3 to 7.5 psi2 /Hz, lower than the experimental result of 24.5 psi2 /Hz. This is potentially due to the reduced-order chemical kinetics, numerical dissipation, and lack of three-dimensional effects. Across three cases of varying equivalence ratios, the dominant frequency modes remained relatively constant, confirming that this characteristic is largely driven by system geometry. The stoichiometric case exhibited the lowest amplitudes, as stoichiometric combustion is typically the most stable and has the most complete heat release. The rich mixture exhibited the highest amplitude as it tends to have more incomplete combustion and slower reaction zones, which allows the unsteady heat release to more easily couple with these pressure oscillations.
"]},{"key":"dc:title","label":"Title","values":["Thermoacoustic Effects of a Variable Equivalence Ratio in a Single Element Methane Combustor"]}]}],"canonical_facts":{"dc:creator":["Green, Carter"],"dc:description.abstract":["Combustion instability is one of the leading factors in limiting the progress and innovations of liquid rocket engines and power plants. Under certain operating conditions, unsteady heat release and acoustic wave interactions can couple and lead to instabilities, such as self-sustaining pressure oscillations, that can lead to reduced combustor performance and potentially hardware damage. In this project, the thermoacoustic effects of controlling the equivalence ratio of a single-element natural gas combustor were modeled and analyzed. The project used Fidelity Pointwise for meshing, ANSYS Fluent for modeling, ERAU VEGA HPC for computing, and MATLAB for acoustic analysis. A numerical model of the Purdue University Continuously Variable Resonance Combustor was created as a two-dimensional, axisymmetric domain and modeled in Fluent with finite rate chemistry and a hybrid RANS/LES approach. The acoustic analysis and power spectral densities were done with a Fast Fourier Transform algorithm.
The dominant frequencies, found to be between 1463 Hz and 1551 Hz, compare well with the experimental result of 1390 Hz, showing that the numerical model captured the primary acoustic modes of the combustor. However, the peak amplitudes of these frequencies were found to be around 3 to 7.5 psi2 /Hz, lower than the experimental result of 24.5 psi2 /Hz. This is potentially due to the reduced-order chemical kinetics, numerical dissipation, and lack of three-dimensional effects. Across three cases of varying equivalence ratios, the dominant frequency modes remained relatively constant, confirming that this characteristic is largely driven by system geometry. The stoichiometric case exhibited the lowest amplitudes, as stoichiometric combustion is typically the most stable and has the most complete heat release. The rich mixture exhibited the highest amplitude as it tends to have more incomplete combustion and slower reaction zones, which allows the unsteady heat release to more easily couple with these pressure oscillations.
"],"dc:identifier":["https://commons.erau.edu/edt/976"],"dc:subject":["Combustion","Combustion Instability","Thermoacoustics","Acoustics","Methane","Propulsion","Computational Fluid Dynamics","ANSYS Fluent","Power Spectral Density","Equivalence Ratio","Flame Dynamics","Natural Gas Combustor","Finite-rate Chemistry","Hybrid RANS/LES","Turbulent Reacting Flows","Propulsion and Power"],"dc:title":["Thermoacoustic Effects of a Variable Equivalence Ratio in a Single Element Methane Combustor"],"thesis:degree_discipline":["Aerospace Engineering"],"thesis:degree_level":["Thesis - Open Access"],"thesis:degree_name":["Master of Science in Aerospace Engineering"]},"updated_at":"2026-07-27T19:26:22Z"}