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Active combustion control for aircraft gas turbine engines
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Breisacher, Kevin J. Paxson, Daniel E. DeLaat, John C. Saus, Joseph R. |
| Copyright Year | 2000 |
| Description | Lean-burning combustors are susceptible to combustion instabilities. Additionally, due to non-uniformities in the fuel-air mixing and in the combustion process, there typically exist hot areas in the combustor exit plane. These hot areas limit the operating temperature at the turbine inlet and thus constrain performance and efficiency. Finally, it is necessary to optimize the fuel-air ratio and flame temperature throughout the combustor to minimize the production of pollutants. In recent years, there has been considerable activity addressing Active Combustion Control. NASA Glenn Research Center's Active Combustion Control Technology effort aims to demonstrate active control in a realistic environment relevant to aircraft engines. Analysis and experiments are tied to aircraft gas turbine combustors. Considerable progress has been shown in demonstrating technologies for Combustion Instability Control, Pattern Factor Control, and Emissions Minimizing Control. Future plans are to advance the maturity of active combustion control technology to eventual demonstration in an engine environment. |
| File Size | 1004603 |
| File Format | |
| Language | English |
| Publisher Date | 2000-07-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Propulsion And Power Combustion Control Combustion Chemistry Flame Temperature Gas Turbine Engines Combustion Aircraft Engines Combustion Stability Reaction Kinetics Combustion Temperature Combustion Chambers Active Control Fuel Control Fuel-air Ratio Burning Rate Operating Temperature Ntrs Nasa Technical Reports ServerĀ (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |