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Investigation of a low nox full-scale annular combustor
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1982 |
| Description | An atmospheric test program was conducted to evaluate a low NOx annular combustor concept suitable for a supersonic, high-altitude aircraft application. The lean premixed combustor, known as the vortex air blast (VAB) concept, was tested as a 22.0-cm diameter model in the early development phases to arrive at basic design and performance criteria. Final demonstration testing was carried out on a full scale combustor of 0.66-m diameter. Variable geometry dilution ports were incorporated to allow operation of the combustor across the range of conditions between idle (T(in) = 422 K, T(out) = 917 K) and cruise (T(in) = 833 K, T(out) - 1778 K). Test results show that the design could meet the program NOx goal of 1.0 g NO2/kg fuel at a one-atmospheric simulated cruise condition. |
| File Size | 7024154 |
| File Format | |
| Language | English |
| Publisher Date | 1982-02-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Propulsion And Power Supersonic Combustion Vaporizing Supersonic Aircraft Gas Turbine Engines Premixing Nitrogen Oxides Combustion Chambers Exhaust Emission Annuli Fuel-air Ratio Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |