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Low-pressure performance of annular, high-pressure (40 atm) high-temperature (2480 k) combustion system
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Wear, J. D. |
| Copyright Year | 1980 |
| Description | Experimental tests were conducted to develop a combustion system for a 40 atmosphere pressure, 2480 K exhaust gas temperature, turbine cooling facility. The tests were conducted in an existing facility with a maximum pressure capability of 10 atmospheres and where inlet air temperatures as high as 894 K could be attained. Exhaust gas temperatures were as high as 2365 K. Combustion efficiences were about 100 percent over a fuel air ratio range of 0.016 to 0.056. Combustion efficiency decreased at leaner and richer ratios when the inlet air temperature was 589 K. Data are presented that show the effect of fuel air ratio and inlet air temperature on liner metal temperature. Isothermal system pressure loss as a function of diffuser inlet Mach number is also presented. Data included exhaust gas pattern factors; unburned hydrocarbon, carbon monoxide, and oxides of nitrogen emission index values; and smoke numbers. |
| File Size | 1087998 |
| Page Count | 23 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19800023888 |
| Archival Resource Key | ark:/13960/t2d844k0m |
| Language | English |
| Publisher Date | 1980-09-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Propulsion And Power Furnaces Inlet Temperature Exhaust Gases Gas Pressure Fuel Injection Combustion Chambers Isobars Pressure Isothermal Processes Combustion Efficiency Fuel-air Ratio Pressure Gradients 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 |
