A method of selecting candidate thermodynamic cycles for the preliminary design of a new turbofan engine for an advanced fighter is described. This technique defines a family of engine cycles consistent in technology, operating limits, and component matching criteria. The cycle variables for the engines are reduced to a matrix of compatible combinations. The engine systems engineer can then select from the matrix of engines, those candidates which most closely meet aircraft performance requirements for further evaluation. It also provides a basis for technology evaluation by comparing the engine matrices created by varying only the technology level. It will show the importance of thrust ratios, design flight Mach number, and airflow schedules for each individual aircraft application in the iteration process to finalize engine selection.
Preliminary design engine thermodynamic cycle selection for advanced fighters
Triebwerksvorentwurf mit Wahl des thermodynamischen Prozesses fuer moderne Kampfflugzeuge
AIAA-Papers ; 1-7
1983
7 Seiten, 15 Bilder
Conference paper
English
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