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Sensitivity of combustion-acoustic instabilities to boundary conditions for premixed gas turbine combustors
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Darling Sr., Douglas Oyediran, Ayo Radhakrishnan, Krishnan |
| Copyright Year | 1995 |
| Description | Premixed combustors, which are being considered for low NOx engines, are susceptible to instabilities due to feedback between pressure perturbations and combustion. This feedback can cause damaging mechanical vibrations of the system as well as degrade the emissions characteristics and combustion efficiency. In a lean combustor instabilities can also lead to blowout. A model was developed to perform linear combustion-acoustic stability analysis using detailed chemical kinetic mechanisms. The Lewis Kinetics and Sensitivity Analysis Code, LSENS, was used to calculate the sensitivities of the heat release rate to perturbations in density and temperature. In the present work, an assumption was made that the mean flow velocity was small relative to the speed of sound. Results of this model showed the regions of growth of perturbations to be most sensitive to the reflectivity of the boundary when reflectivities were close to unity. |
| File Size | 430987 |
| Page Count | 12 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19950017130 |
| Archival Resource Key | ark:/13960/t3c01407f |
| Language | English |
| Publisher Date | 1995-03-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Propulsion And Power Premixed Flames Acoustic Velocity Boundary Conditions Perturbation Flow Equations Gas Turbines Combustion Stability Reaction Kinetics Flow Velocity Nitrogen Oxides Mathematical Models Combustion Chambers Combustion Efficiency Frequency Stability Heat Transfer Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |