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Turbojet emissions, hydrogen versus jp
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Anderson, D. Grobman, J. Norgren, C. T. |
| Copyright Year | 1973 |
| Description | Preliminary data from an experimental combustor show that the NOx emission index, g(NO2)/Kg fuel, is about three times greater for hydrogen than for JP at simulated cruise conditions. However, if these results are applied to aircraft designed for a given mission, hydrogen's higher heating value enables the aircraft to have a lower gross weight and a lower fuel flow rate so that the NOx emission rate, Kg (NO2)/hr may be reduced about 30 percent compared to JP. Theoretical kinetics calculations indicate that combustors may be designed for hydrogen that could further decrease NOx emissions by taking advantage of hydrogen's wide flammable limits and high burning velocity. |
| File Size | 1777921 |
| Page Count | 23 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19730019072 |
| Archival Resource Key | ark:/13960/t1xd5nt41 |
| Language | English |
| Publisher Date | 1973-01-01 |
| Access Restriction | Open |
| Subject Keyword | Thermodynamics And Combustion Hydrogen Exhaust Gases Combustion Products Nitrogen Oxides Jet Engine Fuels Combustion Efficiency Turbojet Engines Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
