The following points, discussed in this paper, should be considered very carefully in all systems contemplating the use of lift engines for VTOL aircraft: (1) The rate of benefit to the aircraft decreases rapidly for engine thrust-to-weight ratios greatly in excess of 20:1; (2) Working relationships are available for use in the aeromechanical design phase of high thrust-to-weight ratio engines; (3) The “installed” thrust-to-weight ratio of lift engines is the most important criterion for evaluation of alternative peripheral equipment design concepts; (4) The reaction control, thrust vectoring, and induction subsystems contribute most of the degradation of lift engine “installed” thrust-to-weight; (5) The rotating cascade concept is the most promising system for deflecting lift engine exhaust flow to achieve both vehicle control and STOL capability; (6) The jetevator, vane deflectors and spherical nozzle concepts are competitive within specified deflection angle ranges; (7) Scoop-type inlets with movable vanes in the upper surface can be devised to alleviate lift engine induction losses; and (8) Significant improvements in the lift engine installed volume can be obtained by optimizing the inlet lip and engine vertical location within the fuselage or engine pod.
Lift Engine Technology
Sae Technical Papers
National Aeronautic Meeting and Production Forum ; 1965
1965-02-01
Aufsatz (Konferenz)
Englisch
Lift engine advanced turbine blade technology
Tema Archiv | 1973
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