Publikationsdatum:
2019-08-14
Beschreibung:
The series/parallel tandem fan engine is evaluated for application in advanced STOVL supersonic fighter aircraft. Options in engine cycle parameters and design of the front fan flow diverter are examined for their effects on engine weight, dimensions, and other factors in integration of the engine with the aircraft. Operation of the engine in high-bypass flow mode during cruise and loiter flight is considered as a means of minimizizng fuel consumption. Engine thrust augmentation by burning in the front fan exhaust is discussed. Achievement of very sort takeoff with vectored thrust in briefly reviewed for tandem fan engine configurations with vectorable front fan nozzles. Examples are given of two aircraft configuration planforms, a delta-canard, and a forward-swept wing, to illustrate the major features. design considerations, and potential performance of the tandem fan installation in each. Full realization of the advantages of tandem fan propulsion are found to depend on careful selection of the aircraft configuration, since integration requirements can strongly influence the engine performance.
Schlagwort(e):
AIRCRAFT PROPULSION AND POWER
Materialart:
NASA-TM-83689
,
E-2140
,
NAS 1.15:83689
,
Joint Propulsion Conf.; Jun 11, 1984 - Jun 13, 1984; Cincinnati, OH; United States
Format:
application/pdf
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