The fixed geometry for the three combination turbofan-ramjet engines is defined; i.e., the definition of the combustion chamber and flow mixer throat cross-sectional areas from general considerations such as the same ratio between corrected thrust at Mach Number sub zero = 3 and thrust at take-off, without reheat, and optimum efficiency of the mixer-diffuser-pilot burner assembly for minimum bulk. A parametric study performed under sea level static and transonic conditions scanned the whole fan-compressor operating field in order to define the primary exit cross-sectional area. After a configuration was specified, an examination followed of the possible operating fields during supersonic acceleration and of the influence on flight range from the mixer throat-sectional area, primary flow exit sectional area, and turbofan rating. Subsonic flight at various turbofan ratings without heating in the combustion chamber also was studied. The internal flow thermodynamic characteristics -- pressure, temperature, and speed values -- are given for the specified configuration and operation at maximum heating and turbofan ratings. (Author)
Turbofan-Ramjet Engine Studies. Volume III. Calculated Results
1964
282 pages
Report
Keine Angabe
Englisch
Jet & Gas Turbine Engines , Combustion & Ignition , Fluid Mechanics , Turboramjet engines , Combustion chambers , Performance(Engineering) , Nozzle gas flow , Geometry , Transonic flow , Transonic flight , Configuration , Fuel consumption , Turbofan engines , Ramjet engines , Jet mixing flow , Supersonic characteristics , Compressors
Turbofan-Ramjet Engine Studies. Volume VII. Drawings
NTIS | 1964
|CALCULATION AND REGULATION FEATURES OF DUCT-BURNING TURBOFAN ENGINE AT RAMJET MODES
DOAJ | 2020
|