Jet engine inlet-fan system and design method

Details Jet engine inlet-fan system and design method Jet engine inlet-fan system and design method

2005-02-15

2010-12-07

Verdier, Christopher (Department: 3745)

Rotary kinetic fluid motors or pumps

Means, disposition or arrangement for causing supersonic...

C415S914000

Reexamination Certificate

active

07845902

ABSTRACT:
A supersonic aircraft engine axial fan that includes a rotating blade row having blades that receive a supersonic entry flow in the absolute frame and decelerate the flow to a lower supersonic or subsonic velocity exit flow while adding work to the flow to increase stagnation pressure. It is preferred that the lower velocity be subsonic. When the fan is combined with a suitably designed inlet, the propulsion system is compact and lighter in weight than conventional engines for supersonic aircraft.

REFERENCES:
patent: 2975587 (1961-03-01), Rae
patent: 2987878 (1961-06-01), Bogert
patent: 3054255 (1962-09-01), Stratford
patent: 3719428 (1973-03-01), Dettmering
patent: 4123196 (1978-10-01), Prince et al.
patent: 4678398 (1987-07-01), Dodge et al.
patent: 7147426 (2006-12-01), Leblanc et al.
Ahsun, U. et al., “Design of a near-Isentropic Supersonic Inlet Using Active Control” Journal Propulsion and Power, 2005, pp. 292-299, vol. 21.
Wennerstrom, A. J., “Highly Loaded Axial Flow Compressors: History and Current Developments,” Journal of Turbomachinery, 1990, pp. 567-568, vol. 112.

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