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Experimental investigation of the low no/sub x vortex airblast annular combustor
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Johnson, S. M. Biaglow, J. A. Smith, J. M. |
| Copyright Year | 1984 |
| Description | A low oxides of nitrogen vortex airblast annular combustor was evaluated which has attained the goal of 1 gm NO2/kg fuel or less during operation. The experimental combustor test conditions were a nominal inlet-air temperature of 703 K, inlet total pressures between 0.52 to 0.83 MPa, and a constant inlet Mach number of 0.26. Exit temperature pattern factors for all test points were between 0.16 and 0.20 and exit swirl flow angles were 47 degrees at isothermal conditions and 23 degrees during combustion. Oxides of nitrogen did not exceed 1.05 gm NO2/kg fuel at the highest inlet pressure and exhaust temperature tested. Previous correlations have related NOx proportionally to the combustor inlet pressure raised to some exponent. In this experiment, a band of exponents between 0.5 and 1.0 resulted for fuel-air ratios from 0.023 to 0.027 and inlet pressures from 0.52 to 0.83 MPa. |
| File Size | 3533684 |
| Page Count | 15 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19840014499 |
| Archival Resource Key | ark:/13960/t0kt1j21q |
| Language | English |
| Publisher Date | 1984-01-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Propulsion And Power Inlet Temperature Inlet Pressure Vortices Nitrogen Oxides Combustion Chambers Exhaust Emission Fuel-air Ratio Mach Number Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
